A study of NACA and NASA published information of pertinence in the design of light aircraft. Volume 2 - Aerodynamics and aerodynamic loads

NASA CR- 1485 A STUDY OF NACA AND NASA PUBLISHED INFORMATION OF PERTINENCE IN THE DESIGN OF LIGHT AIRCRAFT Volume II - Aerodynamics and Aerodynamic Loads Part I - Aerodynamics By James C. Williams III and Delbert C. Summey Part II - Aerodynamic Loads By John N. Perkins Distribution of this report is provided in the interest of information exchange. Responsibility for the contents resides in the author or organization that prepared it.

Prepared under Contract No. 1-7265 by DEPARTMENT OF MECHANICAL AND AEROSPACE ENGINEERING NORTH CAROLINA STATE UNIVERSITY Raleigh, N.C.

for Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and Technical Information Springfield, Virginia 22151 - Price $3.00

Table of Contents Page General Introduction ........................... I A Study of the NACA/NASA Reports on Aerodynamics Applicable to Light Aircraft ..........................

NACA Technical Notes NASA Memorandum (Memo) NASA Technical Notes NACA Technical Reports NASA Technical Reports NACA Wartime Reports NACA Research Memorandum NACA Technical Memorandum NAS_ Technical Translation iii

TABLEOF CONTENTS (continued)

Page

NASATechnical Memorandum

A Study of NACA and NASA Literature on the Calculation of

AerodynamicLoads Having Application to Light Aircraft

NACA Technical Notes

NASA Memorandum (Memo)

NASATechnical Notes

NACA Technical Reports

NASA Technical Reports

NACA Wartime Reports

NACA Research Memorandum

NACA Technical Memorandum

NASATechnical Translation

iv

TABLE OF CONTENTS (continued) Page NASA Technical Memorandum v GENERAL INTRODUCTION Individuals in the National Aeronautics and Space Administration have long felt that much of the agency's research, although orginally performed in support of military and commercial transport programs, has not been applied as completely as it might have been to general aviation activity, particularly as the flight speed of these aircraft reached regions in which military and cormnercial transport aircraft have operated during the past twenty-nine years.

NASA has also recognized that general aviation manufacturing concerns are quite small compared to the usual aerospace manufacturer; they do not have the large engineering staffs to adapt new technology rapidly, but operate more nearly like the majority of American manufacturing concerns where evolutionary changes rather than revolutionary changes are the order of the day. As a result, technical information contained in NASA files must be specially processed to make it really useful to such firms. As orginally conceived, the vehicle for this transfer would be a modern, step-by-step design manual.

Another difficulty faced by the general aviation industry is the lack of young engineering talent with an appreciation of and interest in the industry's problems. This is a result of the almost exclusive attention to the problems of supersonic and space flight which has been characteristic of American aeronautical education for the past 15 years. Younger faculty, for the most part, are not familiar with the problems of light aircraft design and so fail to motivate students to consider this field.

As a way of aiding the general aviation industry in this area as well as with technical information, NASA contracted with North Carolina State University to have a group of younger faculty and students conduct a survey of all NACA and NASA-generated work since 1940 to identify technical information of potential use in a light aircraft design manual. Five faculty members of the Department of Mechanical and Aerospace Engineering participated in the program. Each was assisted by two Aerospace Engineering seniors who also were given special sections of the regular senior work in Aerospace Engineering of direct pertinence to light aircraft.

Dr. James C. Williams and Delbert C. Summey were responsible for reviewing the work in aerodynamics and were assisted by Mr. Edwin Seiglar.

Dr. John N. Perkins was responsible for reviewing the work in air loads and was assisted by Mr. Donald Knepper and Mr. William Rickard.

Dr. Clifford J. Moore reviewed the work on propulsion systems analysis and was assited by Mr. Donald Gray and Mr. Johnny Logan.

Mr. Dennis M. Phillips reviewed the work in performance, stability and control, and flight safety and was assisted by Mr. Robert Pitts and Mr. Paul Ho.

Dr. Frederick O. Smetanawas responsible for reviewing the work in

construction analysis, materials, and techniques and was assisted by Mr. Hudson

Guthrie and Mr. Frank Davis. Dr. Smetanaalso acted as Principal Investigator

on the project.

The majority of the work began 1 June 1968. The students devoted

approximately 30 hours a week each for the 13 weeks of the summerand 8 hours

per week during the fall semester to the project. Faculty commitmentwas

approximately 1/4 time during the summerand 2/5 time during the fall semester.

The students performed the majority of the actual documentreviews after

being instructed as to the type of information desired. The faculty also

provided guidance when pertinence of a particular report was questioned or the

treatment was too advanced. Beginning in late fall, the faculty members

carried out an analysis of the reviews in their areas of cognizance to

(i) identify those of most probably interest in the development of a design

manual, (2) define the state of the art in each area, and (3) identify those

areas particularly well-treated or requiring additional research. The body of

this report contains the results of the analysis relating to structural design.

The individaul reviews are reproduced in the appendix. Volume II treats aero-

dynamics and aerodynamic loads while Volume III is concerned with propulsion

systems, propellers, performance calculation, stability and control, and

flight safety.

It will be recognized that the assignment of a "not applicable" label to

a particular report is a judgment decision; the standards for making such

assignments inevitably vary somewhatfrom day to day and from individual to

individual. There is also the tendency on the part of any reviewer to become

more critical of the value of a report to a particular project as his

experience and the number of reports he has reviewed increases. Since the

present review began with the earliest documents, this discrimination is

applied more noticeably in the later documents. Additionally, it seemsto be

inevitable that in the process of assigning reports to the various groups and

individuals for review someare reviewed twice and others not at all.

Although an effort was madeto correct such deficiencies, someundoubtedly

remain. For these and others, the reader's indulgence is requested.

No attempt has been madeto have the analyses prepared by the faculty

conform to a single style. This would have been difficult because all were

prepared simultaneously; but more importantly, the various topics were found

to have been given different emphasis with time and to vary widely in depth.

Consequently, each faculty member was asked to adopt that style which seemed

most appropriate to the material being covered.

The number of documents to be examinedwas on the order of i0,000. A

simple calculation will show that on the average less than 30 minutes could

be allotted to each report. Even if one discounts the 30%-40% which were

considered not applicable, the time available for review was still not large.

It is a fact, also, that the rate of generation has increased markedly during

the last nine years. However, since an in-depth index of all current NASA-

generated documentshas been available for computer searching since 1962 and

since current reports are more likely to be familiar to the working engineer,

major emphasis was placed on those reports produced prior to 1962

GENERAL CONCLUSIONS

Five faculty members,assisted by ten undergraduate students, of the

Department of Mechanical and Aerospace Engineering at North Carolina State

University have reviewed the NACA/NASA-generated literature published since

1940 for information of possible pertinence to the design of light aircraft.

On the basis of these reviews, it is concluded that:

i. There is a wealth of structural design information available

which, if incorporated intelligently in light aircraft construction, could result in improved structural efficiency.

2. To apply this information in the most effective fashion possible,

computer programs which have modest time requirements and which specify

the material gauges, the stiffener configuration and the stiffener

spacing when supplied with the body shape desired and the loading

expected must be developed.

3. The information available on propulsion subsystems is adequate for

design purposes but requires careful and complete assembly and must be

accompaniedby detailed instructions for it to be used effectively.

4. There are adequate, although, complex, theoretical methods available

for calculating aerodynamic wing loads.

5. More sophisticated theoretical methods making use of high-speed

computers need to be developed for the calculation of aerodynamic loads

on tail surfaces.

6. There is insufficient accurate information available on hinge

momentsto construct reliable design charts.

7. Information on gust load experiences and spectral distribution is in

need of updating to permit structural designs suited to the varied

utilization of light aircraft.

8. Information on landing gear loads appears to be adequate.

9. Flutter information, while limited, appears to be suitable for

development of adequate design criteria.

i0. There is a lack of data on body aerodynamics and wing-body and

tail-body interference effects; otherwise, there appears to be suffi-

cient information in the NACA/NASA literature to compile and prepare a

design manual suitable for use in the aerodynamic design of personal-

type aircraft.

ii. Refined performance calculation procedures which permit the attain-

ment of instantaneously optimum flight paths and which are suitable for

use with light aircraft are available. Their utilization could be

increased through machine evaluation.

12. Generally-accepted, yet detailed criteria for the stability and

control characteristics of light aircraft do not now exist, although

there is a wealth of data from which such criteria can probably be

constructed.

13. Recent high horsepower propellers have been designed using copious

data obtained during the late 1940's. This permits performance improve-

ments over the pre-1943 data used to design current light aircraft

propellers.

14. Insufficient attention has been given to fixing quantitatively the

combination of aerodynamic, propulsion, and structural parameters which

are required for a really safe-to-fly light airplane, although much of

the basic data from which such determinations can be madealready exists.

PARTI

A STUDY OF THENACA/NASA REPORTS ONAERODYNAMICS

APPLICABLE TO LIGHTAIRCRAFT

by

JamesC. Williams III and Delbert C. Summey

Introduction As noted in the general introduction the objective of the present study was two-fold: (i) to determine the nature and extent of information appli- cable to the design of personal type aircraft which is available in the published NACA/NASA literature dating from 1940 to present, (2) to involve undergraduate students at the university level in this project in order to teach them more about personal type aircraft design and to stimulate their interest in this type aircraft. It was also pointed out in the general introduction that these objectives were accomplished by having the students search through all the NACA/NASA literature, dating from 1940, and for each publication which they felt applicable make out an "Abstract Card" contain- ing the pertinent bibliographical data plus a short abstract of the informa- tion contained in the report.

Reports having to do with compressibility effects, supersonic flow, very viscous flow, hydrodynamics, wind tunnel corrections, very large air- craft, helicopters, and high-altitude flight were excluded and marked not applicable, since the interest here is personal-type aircraft. Also, due to the large volume of reports in the area of aerodynamics, some applicable reports were assigned to the not applicable list because of similar informa- tion covered in other reports. Since many reports were superseded an attempt was made to review the same data only once. It is felt that in general thig attempt was successful.

In the case of the field of aerodynamics it became clear, early in the program, that the information in the NACA/NASA literature _n aerodynamics could be grouped into eight broad categories: (i) data on wing aerodynamics, (2) data on airfoil characteristics, (3) data on high lift devices, (4) data on ailerons, (5) data on boundary layer control, 46) data on body aerodynamics, (7) data on tail aerodynamics, and (8) miscellaneous data. Even with such broad categorization it was not always clear into which category a specific NACA or NASA document should fall, for example, it was not uncommon to find cases where ailerons and flaps (high lift devices) were tested together or where boundary layer control was tested together with flaps and/or ailerons.

Nevertheless such an arbitrary and bro_d division of the aerodynamics has been made.

For the information in the field of _erodynamics the preliminary screen- ing and categorization referred to above was followed by another, hopefully more thorough, screening by the faculty member involved. This second screen- ing process isolated those report8 which shauld be pertinent to the field of

personal type airplane design and categorized them into the eight broad subjects

mentioned above. The title, authors, and student abstracts are presented in

the appendix for each report mentioned in the subject listing. It should be

noted that although a single report may contain information dealing with more

than one category, the report was assigned to the category to which the faculty

memberfelt it was most applicable. The appendix also contains a title list-

ing with authors and dates of those reports dealing with aerodynamics which

were found "not applicable" for all the reasons noted above to light aircraft.

In each group, the reports are listed chronologically by series. The table

below gives the initial and final number of the reports in each group by series.

Not Applicable App licab le

First NACA Technical Note 745 749

3871 4408

Last NACA Technical Note

2-5-59E I0-I-58E

First NASA Memorandum (Memo)

2-5-59E 7-9-59A

Last NASA Memorandum (Memo)

D-85 D-8

First NASA Technical Note

D-339 D-2650

Last NASA Technical Note

688 681

First NACA Technical Report

1370 1389

Last NACA Technical Report

R-139 R-I

First NASATechnical Report

R-139 R-148

Last NASA Technical Report

A-5 A-6

First NACA Wartime Report

None E-56 L-7 L-I None W-I A-92 A-94

Last NACA _T_rtimeReport

None E- 280 L-784 L-781 None W-108 ATB24 A6G22

First NACA ResearchMemorandum

L56JI9 L58G29

Last NACA Research Memorandum

961 921

First NACA Technical Memorandum

1206 1300

Last NACA Technical Memorandum

None F-2

First NASA Technical Translation

None F-84

Last NASA Technical Translation

None X-8

First NASA Technical Memorandum

None X-652

Last NASA Technical Memorandum

I0 It is believed that through the use of the subject listing and the appendix,

the reader may rapidly identify reports in the field of aerodynamics which

would be useful to him.

It is realized that both the categorization and the interpretation of the

important contents of the reports are subject to the experience and the biases

of the writer. Every effort has been made, however, to remove the influence

of these factors and to makethe subject listing as objective as possible. It

is hoped that the reader will find it so.

Present Status of Information on Aerodynamics The production of a subject listing for the information on aerodynamics contained in the NACA/NASA literature dating from 1940 does not, in itself, determine whether or not there is sufficient data available in this literature for creating a design manual suitable for use in the design of personal type aircraft. The data from the period prior to 1940 would be a necessary part of any aerodynamic design manual. As a matter of fact, it appears that the quan- tity of NACA data applicable to the design of personal type aircraft may have reached a peak sometime in the later 1930's or in the early 1940's. After that time the quantity of data of this type seems to continue to decline. In the late 1940's and early 1950's the emphasis appears to have shifted to supersonic and later to hypersonic flow. This emphasis seems to continue even today. It therefore appears that the information covered in the present study may not truly indicate the quantity of information available for a design manual for the design of personal type aircraft. Nevertheless an attempt will be made here to indicate the areas where sufficient data seems to be available as well as the areas where additional information is necessary.

Aerodynamic data on wings including the effects of taper, twist, warping and variation in spanwise distribution of airfoil section seems to be adequate.

In the period dating from 1940 to present, we hsve listed approximately 30 reports in this area and there are undoubtably more published prior to 1940.

The data on airfoil section characteristics also appears to be adequate. We have list approximately 50 reports in this area under the subject "Airfoil Data". In addition there is a very large body of similar data published prior to 1940. There will continue to be developments in airfoil characteristics and development of new special-purpose airfoils. The data available todate, however, represents an extremely large volume of data on the aerodynamic charac- teristics of a large number of basic airfoil shapes.

The quantity of data on basic high lift and control devices, various types of flaps, spoilers, slots, slats, and various schemes of boundary layer control, seems to be adequate. In the subject listing there are listed approximately 80 reports on these devices with another 30 reports on boundary layer control.

Again it would seem logical that there is additional data of this type published prior to 1940.

ii

Sufficient data also seemsto be available in the area of ailerons. In

this area we have listed approximately 30 reports.

In the case of tail aerodynamics, the data available seemsto be adequate.

In the subject listing there are approximately 30 reports listed. Two of these,

NACA TN 1291 and NACA TR 688, are of special interest. NACA TN 1291 presents

basic data on 19 isolated tail surfaces while TR 1291 presents basic data on

another 17 different tail surfaces. This type of data should be ideal for

design purposes. Here again there is probably additional data available in

the period prior to 1940.

The two areas where there seemsto be a lack of data are those of body

aerodynamics and wing-body or tail-body interference. Possibly there is

additional data available in this area in the period prior to 1940. It would

appear, however, that there is a need for additional information in these areas

both for the basic understanding of the problem and to provide basic data for

the designer.

In general then, we conclude that, including the data published prior

to 1940, there is probably sufficient data available in the NACA/NASA litera-

ture to compile and prepare a design manual suitable for use in the aerodynamic

design of personal type aircraft.

Aerodynamics of Winss There were many reports found which dealt with aerodynamics of wings and wing loads. The reports which were considered to be most valuable to a study of light aircraft are listed below.

NACA Technical Notes: 855, 1151, 1212, 1269, 1270, 1422, 1677, 1696, 1703, 1946, 2353, 2440, 2445, 2753, 2776, 2908, 3324 NASA Technical Notes: D-85, D-339 NACA Technical Reports: 703, 800, 1176 NASA Technical Reports: R-139 NACA Wartime Reports: L-145, L-271, L-311, L-332, L-406 NACA Technical Memoranda: 961, 988, 1095, 1129, 1146 In addition to the above reports which are more or less general in nature, there are several reports, mainly wartime reports, which deal in some way with the aerodynamics of wings on specific airplanes. These reports are as follows: NACA Technical Notes: 1061, 1407 NACA Wartime Reports: A-5, L-86, L-94, L-98, L-615 Airfoil Data A large number of the reports dealing with aerodynamics fell under the category of Aerodynamic Data. Some of the reports which were indicative of the Airfoil Data reports are given below.

NACA Technical Notes: 1044, 1299, 1304, 1368, 1591, 1773, 1894, 1923, 1945, 1998, 2074, 2177, 2228, 2235, 2251, 2338, 2465, 2502, 2998, 3172, 3244 NACA Technical Reports: 708, 722, 824, 833, 903 A-87, L-46, L-82, L-138, L-139, L-156, L-319, L-345, NACA Wartime Reports: L-450, L-452, L-507, L-532, L-560, L-659, L-661, L-784 NACA Research Memoranda: L8B02, L8L08 NACA Technical Memorandum: 1127 There also three NACA Wartime Reports which refer ro certain airfoil sections in relation to specific airplanes. These reports are as follows: L-534, L-629, L-681.

High Lift Devices The reports listed below are primarily concerned with the topic of high lift devices. These reports investigate such things as slats, slots, various flaps and spoilers and give a good cross section of data on high lift devices.

NACA Technical Notes: 761, 763, 796, 945, iii0, 1167, 1191, 1248, 1277, 1352, 1463, 1517, 1545, 1574, 1579, 1590, 1624, 1674, 2080, 2404, 3007, 3129, 3174 NACA Technical Reports: 689, 706, 718, 723, 942 A-80, A-92, L-7, L-41, L-56, L-128, L-134, L-140, L-261, NACA Wartime Reports: L-415, L-441, L-449, L-469, L-481, L-493, L-574, L-665, L-693, L-697 In addition to the Wartime Reports mentioned above, the NACA undertook a systema- tic investigation of control surface characteristics and published the results in a series of Wartime Reports. Those reports along w_th similar Research Memoranda and Technical Memoranda are as follows: L-47, L-175, L-196, L-215, L-290, L-301, L-314, L-355, NACA Wartime Reports: L-366, L-377, L-378, L-380, L-447, L-448, L-454, L-511, L-666, L-668

NACA Research Memoranda: L8K22, L9B23, L9E27

NACA Technical Memoranda: 1108, 1206

In addition to the reports listed above which are more or less of general

interest, there are several reports, mainly Wartime Reports, which cover

rather specific problems or are related to specific airplanes. These

reports are as follows:

NACA Technical Notes: 1236, 1296

NACA Wartime Reports: L-250, L-437, L-506, L-544, L-677, L-701, L-704,

L-708, L-746, L-769

Ailerons Reports dealing with ailerons and aileron control forces were felt to be very important to light aircraft,and the reports listed below seem to give sufficient data on ailerons: NACA Technical Notes: 1085, 1099, 1386, 1431, 1582, 1802, 1872 NACA Technical Report: 803 NACA Wartime Reports: A-18, A-54, A-55, L-31, L-105, L-151, L-171, L-172, L-178, L-228, L-242, L-262, L-317, L-325, L-337, L-374, L-375, L-376, L-420, L-421, L-431, L-432, L-433, L-435, L-470, L-480, L-513, L-526, L-644, L-651, L-777 Boundary Layer Control Thirty-one reports discussing boundary layer control were felt applicable to light aircraft. These reports discussed both blowing and suction as a con- trol mechanism and usually discussed the effective drag coefficient due to the power required to operate the boundary layer control.

NACA Technical Notes: 1007, 1071, 1292, 1293, 1395, 1597, 1631, 1683, 1741, 1905, 1961, 2041, 2112, 2143, 2149, 2405, 2644, 2796, 2847, 3285, 3369 NASA Memorandum (Memo): 2-5-59E NASA Technical Note: D-309 NACA Technical Report: 1276, 1370 NACA Wartime Reports: L-209, L-521

NACA Research Memoranda: L7LI5, L9A20

NACA Technical Memoranda: 974, 1167

Bodies Only a few applicable _eports dealt with body aerodynamics thus indicating a lack of data. The reports reviewed are listed below: NACA Technical Notes: 812, 1087, 3057 NACA Technical Reports: 730, 750 NACA Wartime Reports: L-489, L-509 NACA Research Memorandum: L56JI9 Nacelles The Wartime Reports were found to contain the most data on nacelles and air scoops as can be seen from the listing below. Although there were many Wartime Reports dealing with this topic more information is needed in discus- sing light aircraft nacelles.

NACA Technical Note: 1593 NACA Technical Report: 950 NACA Wartime Reports: L-II5, L-229, L-275, L-279, L-300, L-331, L-407, L-428, L-695, L-696, L-698, L-747 In addition to the above reports on nacelles and air scoops, there are five Wartime Reports having to do with cowlings on the XP-42 airplane.

NACA Wartime Reports: L-241, L-243, L-285, L-383, L-613 Aerodynamics of Tail Surfaces The thirty reports given below were felt sufficient to cover the topic of tail aerodynamics.

NACA Technical Notes: 778, 804, 815, 1074, 1228, 1291, 1337, 1369, 2495 NACA Technical Report: NACA Wartime Reports: L-186, L-212, L-260

NACA ResearchMemoranda: A7F25, A7K24, A8BII, A8H30,A8J21

There are also a number of reports, mainly Wartime Reports which cover rather

specific problems or are related to specific airplanes. These reports are

listed below:

NACA Technical Notes: 1139, 1377, 1763

NACA Wartime Reports: L-60, L-122_ L-397, L-440, L-516, L-573, L-702, L-736,

L-779

Miscellaneous Several reports were reviewed which could not be classified into one of the seven topics above but which maybe valuable to light aircraft design.

These reports are listed under miscellaneous aerodynamics and deal with such topics as fuel tank aerodynamics, landing gear drag, and ground effect.

NACA Technical Notes: 788, 1317, 2061, 2525, 2676, 3126 NACA Technical Report: L-752 NACA Wartime Report: A7B24 NACA Research Memorandum:

APPENDIX NACA Technical Notes Dealing with Aerodynamics and Judged Applicable to Light Aircraft TN 745 TEST OF A GUST ALLEVIATING FLAP IN THE GUST TUNNEL_ Philip Donely and C. C. Shufflebarger_ January 1940 Tests were made in the NACA gust tunnel to determine the effective- ness of a long-period dynamically overbalanced flap in reducing airplane accelerations in the normal direction due to atmospheric gusts. The gust alleviating flap was attached to the wing by means of 12 pivot and socket bearings. At each hinge an arm 1.2 inches long supported a 0.27 ounce weight in the wing of the model. The overbalance of the weight was counteracted by a coiled spring at each hinge. Small disks were used for damping. The flap displacement would be a direct function of vertical displace- ment increments.

Tests were made for gust gradient distances of I and 8 chord lengths with the gust flap both fixed and free. There was one velocity_ one gust velocity_ and one wing loading.

The flap effectiveness was defined as the percentage reduction in maximum acceleration increment due to the flap.

Results i. The flap was relatively ineffective for sharp gusts but effectiveness tended to increase as the gradient distance increased.

a. A 3% effectiveness was achieved for sharp edge gust.

b. 38-40% for a gust with gradient distance of eight chord lengths.

c. Sharp gust is seldom encountered in flight.

d. More effective in smoothing out small bumps than large ones.

2. A theoretical calculation was made using acceleration incre- ments to find gust lengths and it compared closely with the experi- mental results.

3. The flap tends to reduce the pitch of an airplane in the gust.

Major Conclusions I. A device which maintains constant wing lift tends to reduce the maneuverability of the airplane.

2. The flap was good for a gust with a gradient distance of at least 8 chord lengths.

3. The flap was poor for a sharp gust (gradient distance of i chord length).

4. The flaps tended to reduce the longitudinal stability of the airplane.

TN PRESSURE-DISTRIBUTION INVESTIGATION OF AN NACA 0009 AIRFOIL WITH AN 80-PERCENT-CHORD PLAIN FLAP AND THREE TABS_ Milton B. Ames_ Jr._ and Richard I. Sears_ May 1940 Pressure distribution tests of an NACA 0009 airfoil with an 80% chord plain flap and three plain tabs of I0-20_ and 30-percent chord length mounted serially was studied for use as a vertical or horizontal stabilizer. The hinges were completely sealed so that pressure readings along hinge lines were on the high_ or struc- turally conservativ% side.

This airfoil was investigated with the angle of attack from -14½o to i0½ ° at 5 ° increments. For each angle of attack_ the flap was deflected 0°_ i0o_ 20°_ 30 ° down. And for each of these changes_ each tab was deflected 0°_ J I0°_ _ 20o_ and ! 30o. Because of the large amounts of data_ only that for the 20% chord tab was mainly presented.

Because the hinges were sealed_ the highest pressures occur at the hinge line. Also the highest pressure increments occur here.

When tab and flap are both deflected_ peak load values occur at both hinge axes with resultant pressure acting in the same direc- tion. If flap and tab are deflected in opposite directions_ peak pressure increments still occur at the hinge lines_ but the resul- tant pressures act in opposite directions.

The airfoil normal force coefficient was changed by 52% which was the maximum change. The stall of the flap generally occurred at a deflection of about 20 ° for low angles of attack and about 5o for high angles of attack.

The coefficient of moment about the flap hinge axis varied linearly with flap deflection. As the deflection increased_ the tab effectiveness decreased. The incremental data obtained for this report is believed to be applicable to other conventional airfoils of approximately the same shape and size.

TN 763 WIND TUNNEL INVESTIGATION OF TWO AIRFOILS WITH 25-PERCENT-CHORD GWINN AND PLAIN FLAPS_ Milton B. Ames_ Jr._ May 1940 Force tests were made on two airfoil sections with flaps: I. NACA23018 airfoil with Gwi_nflaps with a chord of 25%the overall chord.

2. NACA23015 airfoil with plain flaps with a 25%chord also.

GWINN FLAPS- Essentially a flat plate mounted at a point very near the trailing edge of the wing. In neutral position it extends past the trailing edge of the basic wing resulting in an increased over- all chord and wing area.

PLAINFLAP- The plain flaps used had the sameoverall chord_ span_ aspect ratio_ and approximate maximumthickness as the Gwinn flap.

_lual for both cases Gwinn Flap Plain Flap Purpose - to determine relative merits of the Gwinn and ordinary plain flaps as high lift devices.

Test conditions: Pressure - 16.37 psf - dynamic Speed - 80 mph Reynolds No. - 609_000 Test procedure - to determine lift 3 drag_ and pitching moment for different deflections throughout an angle-of-attack range from -12 ° to beyond stall.

Corrections: i. For tunnel effects to change aspect ratio to 6 in free air.

2. Standard jet boundary corrections were applied.

3. Effects of supporting strut on aerodynamic co- efficient of models.

Gwinn Flap Results CL plotted against angle of attack varied regularly with flap deflection except at 30 ° deflection.

a. Irregularities may be characteristic of airfoil and flap combination.

b. May be scale effects.

2. Maximum CL value at deflection angle of 60 ° with C L _ 2.3.

3. Maximum L/D = 18.6 at deflection angle of 0°.

.

The change in pitching moment (Cm) with flap deflection was similar to a conventional flap in that C was normal with flap deflection, m(alCl) a. Upward deflection gave stalling moment.

b. Downward deflection gave diving moment.

Plain Flap Results i. CL curve plotted against angle of attack was irregular at 30 ° deflection.

2. Maximum CL was at deflection angle of 60 °.

3. Maximum L/D was 19.4 at deflection angle of 0 o.

Comparing Results i.

For a plot of C D against CL: a. For CL from -0.15 to 0.66 (high speed and cruising speed ranges) plain flap had lower drag.

b. Minimum C D for plain flap was 0.0095 at deflection of 0 °.

c. Minimum CD for Gwinn flap was 0.0107 at deflection of -2 ° .

d. Maximum C L for @winn flap was 2.03 at deflection of 60 ° .

e. Maximum CL for plain flap was 2.00 at deflection of 60 ° .

f. Plain flap had lower C D for values of CL through 0.70 for deflection of -i0 ° to 5° .

g. At CL = 1.00 Gwinn flap had lower drag coefficient.

2. Increments of CLmax caused by incremental deflections is greater for plain flaps although the Gwinn flap had a slightly higher value of CLmax for the same deflections.

3. The plain flap has the higher speed-range ratio whether the flap is neutral_ deflected at 60 ° or at CL = 0.2 where C D is a minimum.

4. A steeper gliding angle could be obtained with plain flap deflection of 60 ° than with a Gwinn flap.

Major Conclusions i. Considering speed range-ratio plain flap is best.

2. For CL of 0.7 or less the plain flap had the lower drag coeffi- cient.

3. For CL of more than 0.7 the Gwinn flap had a lower drag coeffi- cient.

TN 778 NOTES ON THE STALLING OF VERTICAL TAlL SURFACES AND ON FIN DESIGN_ F. L. Thompson and R. R. Gilruth_ October 1940 A discussion was presented on the stalling and stability of vertical tail surfaces. The test was for a twin engine airplane with various tail configurations. The problems arose with rudders from sideslipping. During a sideslip_ a rudder can stall causing the craft to lose yaw stability_ and_ in fact_ go through a transi- tion of rudder moment. This transition is a reversal force needed for rudder movement so that to neutralize the rudder_ force must be applied to it in the neutralizing direction instead of merely releasing the original force. If a force is not available for this_ differential power must be used. If a sideslip is gradual_ then the stall can be felt approaching as a reduction in pedal pressure.

The angle of sideslip was also found to be proportional to the speed of the airplane_ lateral component of force capable of the craft_ and angle of bank. Fairly large angles of sideslip can result from low angles of bank. As a result a true spin may accrue.

By adding a fixed fin to the twin vertical stabilizer tail_ it was found that much higher lateral stability existed and that greater rudder deflections were needed for the same amount of yaw.

Because of aerodynamic refinements_ fuselages are becoming more unstable about the yaw axis. Therefore an index to the size fin needed for an airplane can be set up by the relation £Sf/D2L where = tail length_ Sf = fin area_ D = max. fuselage diameter_ L = length of fuselage.

£Sf For this airplane h_ 0.5. It would appear that smaller values of the factor will suffice for airplanes equipped with dorsal fins or those in which the afterbody of the fuselage is shaped in such a way that the unstable moments are not retained at large angles of yaw.

DRAG DETERMINATIONS OF THE FORWARD COMPONENT OF A TRICYCLE LANDING TN 788 GEAR_ Hubert N. Harmon_ December 1940 Purpose - to determine the drag of the front-wheel arrangements of several types of tricycle landing gear.

The landing gear tested can be classified as non-retracted and partially retracted types.

3. 4.

U

Four types of gear models: I. Unfaired wheel and fork_ 2. Strut faired landing gear_ 3. Wheel-spat_ single strut type with complete fairings_ 4. Trouser typ% complete fairing.

The gears were tested in 4 positions.

The fuselage was set at zero pitch and there were four fuselage positions of the wheel mount_ A_ B_ C_ and D progressively moving from the front of the fuselage toward the rear. The total length of the wheel strut is given as a function of wheel diameters.

Results i. Nonretracted landing gear in order of decreasing drag were i_ 2_ 4_ 3. One exception was found at position c with a 1.16 diameter extension where gear 2 was lower in drag than number i.

2. Partially retracted landing gear in order of decreasing drag: a. Landing gear in streamline fairing with cap off.

b. Unfaired landing gear a_one (i).

c. Landing gear in streamline fairing with cap on.

_-- retracted where the landing gear in streamline fairing is 3. The drag of the unfaired landing gear in the streamline fairing with the cap on is much lower than that of the nonretracted landing gears extended more than 1.25 wheel diameters_ but the unfaired gear alone must be retracted almost 0.5 wheel diameters before its drag is reduced to that of the best nonretracted gear.

4. The general trend was an increased drag with increased exten- sio% but drag of gear (3) remains fairly constant with increased extension.

5. The drag of each gear either does not change or initially in- creases as the landing gear is moved to a more rearward position.

Conclusions i. Drag changes very little with either longitudinal location or wheel extension for the landing gear with the lowest drag.

2. The lowest drag landing gear was a completely faired gear of the wheel spat_ single strut type.

3. The wheel of the unfaired retractable landing gear was at least one-half retracted into the fuselage before the drag became less than that of the best nonretracted landing gear.

TN 796 DETERMINATION OF CONTROL-SURFACE CHARACTERISTICS FROM NACA PLAIN- FLAP AND TAB DATA_ Milton B. Ames_ Jr._ and Richard I. Sears_ February 1941 The data from several previous NACA pressure distribution investi- gations of plain flaps and tabs have been used to construct charts suitable for use in the design of control surfaces. The experi- mentally determined variation of aerodynamic parameters with flap chord and tab chord are presented in chart form. A discussion of the basic equations of thin airfoil theory and the development of a number of additional equations that are helpful in tail design are presented in the appendices. The procedure for applying the data is described and a sample problem of tail design is carried out.

TN 804 WIND-TUNNEL INVESTIGATION OF THEEFFECT OF VERTICAL POSITION OF THEWING ONTHESIDEFLOW IN THEREGION OF THEVERTICAL TAIL_ Isidore G. Recant and Arthur R. Wallac% April 1941 An investigation is madeof the air flow at the tail of a mono- plane model to determine the reason for the change in vertical- tail effectiveness when the vertical position of the wing is changed.

It had been found previously that the vertical-tail effectiveness was increased considerably when the wing was moved from a high wing position to a low wing position. To determine the reason for this change tests were conducted on both low wing and high wing models (samemodel with wing displaced) in the NACA7' by i0' wind tunnel. Measurementswere madeof the dynamic pressure and flow angularity in the vicinity of the vertical-tail. Tests were made with a 0.2c split flap both in the neutral position and deflected 60 o .

qoo = 16.37 psf V_ _ 80 mph Re = 609_000 based on i0 inch chord Reef f = 975_000 (Turbulence factor = 1.6) = 0 o = -50_ 0_ 50 The dynamic pressure at the vertical-tail station was increased when the wing was in the low wing configuration and was increased even further when the flap was deflected. The increase in dynamic pressure at the vertical-tail station was not_ however_ sufficient to account for the increased effectiveness of the vertical-tail.

The flow deflection in the vicinity of the vertical-tail (sidewash angle) was found to be the major reason for increased effective- ness of the tail. The major contribution to sidewash comes from the body and from the body wing interference.

TN 812 MINIMUM INDUCED DRAG IN WING-FUSELAGE INTERFERENCE_ Perry A.

Pepper_ September 1941 From a general theorem based on Prandtl's theory of the lifting line_ a method is devised to determine the minimum induced drag of airfoils in the proximity of ideal internal boundaries. The theorem is applied for the case of an ideal wing-fuselage combination consisting of a lifting line intersecting an in- finitely long circular cylindrical fuselage to determine the effect of wing height on the minimum induced drag. This general theorem solves the problem of minimum induced drag for the most general case in which any number of wings of any front elevation and any number of ideal fuselages are admitted.

In this analysis_ the airfoil is regarded as a lifting line_ weak loading is assumed. The Kutta-Joukowski law for finite air- foils was derived.

R F = circulation L = pU _ Fdx p = density L U = free stream velocity Here L and R represent the left and right edges of the vortex sheet. Also the expression for the induced drag for a finite wing only is derived using conservation of momentum of forces.

Thus = velocity (no fuselage) potential - x _x By In order to treat the wing-fuselage interference_ the fuselage was considered to be a circular cylinder of infinite length. In this case for wing-fuselage interference the expression for the lift was This lift consists of two parts--a lift on the wings and a lift on the fuselage. The lift on the fuselage is assumed to be in- duced by the presence of the wings.

The minimum induced drag for a given lift was desired for the wing- fuselage interference. The following theorem was produced for the general case mentioned before of any wing and any fuselage.

Theorem: The analytic function_ f(z)_ which minimizes the induced drag with given lift and satisfies the boundary condition% is the sum of two analytic functions: one is the flow function of the downward potential flow about the fuselage boundary_ the other is the flow function of the upward potential flow about the entire bounding contour_ % consisting of the fuselage cross section and the trace of the vortex sheet_ where the two flows have equal and opposite velocities at infinity.

The simple relation below was derived for the minimum drag for a given lift: C D. - L 2V c is a real positive constant with the dimensions of velocity c << V. Also the general velocity vector (_x_y_ _z) is propor- tional to c.

The results from experiment do not confirm the results of this theoretical analysis because of the presence of a boundary layer in the actual experiment.

The references referred to in the report are as follows: i. Munk_ Max M.: The Minimum Induced Drag of Airfoils.

Rep. No. 121_ NACA_ 1921.

2. Lennertz_ J.: On the Mutual Reaction of Wing and Body.

TM No. 400_ NACA, 1927.

TN 815 COMPARISON OF VEE-TYPE AND CONVENTIONAL TAlL SURFACES IN COMBINA- TION WITH FUSELAGE AND WING IN THE VARIABLE-DENSITY TUNNEL_ Harry Greenberg_ July 1941 A comparison is made of the pitching moments and yawing moments of a vee-type tail and a conventional type tail. The tests were conducted in the NACA Variable-Density tunnel. Measurements were made on both types of tail in the presence of both a body and a wing-body combination. The Reynolds number for the tests was approximately 8x10 _ (effective Reynolds No.).

It was found that: i. The ratio of pitching moment of the vee-tail to the pitching moment of the conventional tail was 0.71.

2. The ratio of yawing moment to pitching moment of the vee-type tail surface was 0.3.

3. The ratio of yawing moment to pitching moment of the conven- tional tail surface was 0.48.

A simple method is presented for calculating the yawing-moment to pitching-moment ratio in the report.

It was also noted that the presence of a fuselage reduced the measured moments to 15-25% of the values calculated without fuse- lage interference.

A METHOD FOR DETERMINING THE CAMBER AND TWIST OF A SURFACE TO TN 855 SUPPORT A GIVEN DISTRIBUTION OF LIFT_ Doris Cohen_ August 1942 A theoretical method is described in which camber and twist of an arbitrary plan form_ required to support a given distribution of lift_ may be determined. The lifting surface and wake are replaced by the distribution of vortices in a plane.

Vortex pattern is obtained by integrating the chordwise pressure distribution back from the leading edge at several stations along span. Circulation r was shown to be proportional to the integral.

Linearly connecting the points where the values of the integral are equal defines the vortex lines.

In the replacement of a lifting surface by a vortex sheet_ assump- tion madethat pressure increments due to the presence of an airfoil in the stream are equal and opposite on upper and lower surfaces as in a thi% flat plate at small angle of attack. Substitution is still admissible in calculation of lift when thickness is not negligible because the difference between velocities on upper and lower surfaces at any position_ and not magnitude of each increment_ determines lift at that point.

The pressures on the surfaces are: V = free stream velocity Pupper = ½ p(V2 + 2Vuupper) V = componentnormal to V on u surface of wing Similarly Plower = p(v2 + 2Vulower) Resulting lift per unit area is then the difference in pressure P = ½ p2(Vuupper - Vulower) = pV(uu - u2) (i) Derivation of equivalent vortex pattern follows directly from equation (i). If ds represents the element of circulation around a small length ds_ parallel to V over which uu and u2 may be consid- ered constant_ the following relation holds: (2) dsF = (uu - u2) ds from which equation (i) is: 5F AP = _V_F _F Thus the lift is proportional to or the cross-stream component of vorticity.

Consider a narrow strip parallel to the leading edge and varying in width for _ &Pds to be constant along the strip. This strip would represent a vortex element of strength _ APds. These elements could be defined in the same way to lie one behind the other. From equa- tion (3) I r APds = F o p-V In order to satisfy the Kutta conditions_ there can be no pressure difference across the trailing edg% these lines must leave the wing parallel to the stream velocityj as shown by eqn. (3). The drawing of these contour lines from the integral of the pressure distribution is the first step of the procedure for finding the camber and twist of the lifting surface.

Determination of induced vertical velocities: To obtain the vertical velocity_ or downwash_ w_ over the vortex pattern described_ the Biot-Savart equation is integrated. A point P is chosen and the section between two radii from this point is used. The angle between the radii is d_ and the area used is dr wide at a distance r. These radii cut off a vortex element of length dz with a strength - _F/Dr dr. The downwash at P is then: 1 1 _F dr dz sin_ (5) = angle between vortex dw - 4_ 2 Dr element and radius r but dz sin _ = rd_ and 1 DF drd_ (6) dw = - 4_r Dr The downwash is then oo 2_ w = f f I _F d_dr (7) - 4rrr 5r O O By using Liebniz's rul% this integration is reduced to a graphical procedure. In evaluating w_ circles are drawn on the vortex pat- tern_ the values of F are _lotted as a function of _/2_ and are also a function of r-(F = F(r)) or co 1 d_ dr (8) w = -_ 2--f O For the evaluation of equation (8)_ first plot _ against r which will approach an asymptote.

The downwash due to a curve of The load curve is a typical one.

the general form n --F = a - a r (n > i) at r O n is given by 3O a n n-i n-i n W _- -- (r B - rA ) The where rA and r B are the end values of r for the interval.

downwash for the first section is then w(1) = (2a2r ° + 4/3 a4ro3) The curve is made up of more than one part; the first of which goes to r : r o at an inflection point or somewhat ahead of it.

The part of the curve immediately following r = r o has a critical effect on the value of the downwash and numerical integration must be used along with division of the curve. The intervals must also be taken in a geometric rather than arithmetic progression of which the abscissas are ro; kro3 k2ro; etc._ with the value of k between i and z depending upon interval size. The downwash w(ll) is now calculated to find the contribution of section II. The last abscissa is the new starting point; and the value of k is slightly larger, w(lll) is found to where the difference between curve and asymptote is small; then a w(IV) is found from there to infinity by analytic methods.

The downwash is then (at P) equal to w(1) and w(ll)_ and w(lll) and w(IV). The eqn.: 2_ d _ rd_ O dr dr w(o) : 4_(r-o) is thus recognized as the ordinary formula for the induced normal velocity with the load expressed in the form of a definite integral and suggests that the first integration was equivalent to concen- trating all vorticity around each circle at a single point at the distance r along an infinite line from P. The loaded line of the curve drawn_ except for the I/2_ factor introduced_ may be consid- ered to be equivalent to the original lifting surface.

TN 1007 BOUNDARY-LAYER-CONTROL TESTS OF TWO WINGS IN THE LANGLEY PROPELLER- RESEARCH TUNNEL_ Hugh B. Freeman_ January 1946 Suction and pressure slots were used on two airfoils to examine lift coefficients possible as function of slot position; power necessary_ angle of attack_ and flap angle. Speed range 40 - 80 mph.

I. Stub Wing - 6.5' span; 5.5' chord_ max thickness = 0.30% fitted with large end plates for better ARef f.

a. CLmax= 3.2 suction slot at 0.54 chord blower drag coefficient = 0.07 b. CLmax 3.2 pressure slot at 0.42c blower drag several times greater than a.

C.

Conclusion - A single large suction slot near the mid-chord is more effective than any multiple slot arrange- ment_ when all slots receive same suction.

II. NACA 2415 Wing. AR = 6. Chord = 2.56'. Suction only used thickness 0.15 chord. Unflapped_ plain 0.3 chord flap_ zap flap (0.25c).

a. With no flap or zap flap_ best location of suction slots was between 0.ii and 0.20 chord from leading edge.

C_a x = 2.6_ 3.2 respectively. Ideal blower drag coefficient =0.3.

b.

For plain flap, least power required vs highest CLmax was obtained when slot was on flap just behind hinge. Angles of attack for CLmax were in a more practical range than on the plain wing.

Co For plain flap, slot locations near flap hinge were effec- tive in obtaining high lift-curve slope and flap effective- ness_ but leading edge slots are more effective in main- taining flow at high angles of attack.

d, For plain wing_ slot at 0.91 chord caused an appreciable increase in L/D, which includes blower drag.

Work on this repor t was conducted at Langley in 1935 in the pro- peller-research tunnel. Note the low test air speed, 40 mph (except take-off = 80 mph). This speed was used to keep large ratios of wing pressure to dynamic pressure within limitations of blower power available. The graphs which were given are necessary to inter-relate all variables.

TN 1044 EFFECT OF MACH AND REYNOLDS NUMBERS ON MAXIMUM LIFT COEFFICIENT_ John R. Spreiter and Paul J. Steffen, March 1946 A compilation has been made of maximum-lift-coefficient (CLmax) data in flight with six pursuit type airplanes employing conven- tional and low-drag airfoils. This data_ which covers Mach 0.15 to 0.72 and Reynolds numbers (Re) from 4.4xi06 to 19.5xi06 has been analyzed with pertinent model and airfoil data obtained in several wind tunnels.

Whenthe effects of the Mach numberwere considered as well as those of Reynolds number_good correlation was found between flight and wind-tunnel data_ providing buffeting did not prevent the attainment of CLmax;and if so_ CLmaxappeared to be related to the lift-curve slope. Data indicated that CLmax was affected by Machnumbers greater than 0.15. Distinct differences existed between the effects of Machand Reynolds nL_bers on CLmaxin the sub-critical and super-critical Mach number regions. For the sub- critical Mach number region_ CLmax obtainable in flight decreased steadily with increasing Machnumber. For super-critical region_ as Machnumber increased_ CLmaxof NACA conventional airfoils con- tinued to diminish as at sub-critical Mach numbers_while that of NACAlow-drag airfoils reached a minimumat a Machnumber between 0.40 and 0.55 and then began increasing until secondary peak values were reached at a Machnumber between 0.60 and 0.66. For the sub-critical Mach numberregion_ effects of Re on CLmax decreased progressively with increasing Math number_becomingzero at M = 0.55. The critical Re increased almost linearly with Mach number.

TN 1061 WIND-TUNNEL INVESTIGATION OF EFFECT OFWING LOCATION_ POWER_ AND FLAPDEFLECTION ONEFFECTIVE DIHEDRAL OF A TYPICALSINGLE-ENGINE FIGHTER-AIRPLANE MODEL WITHTAlL REMOVED_ Warren A. Tucker_ May Whentests were madeboth a high and low wing were tested, Tests were madewithout flaps_ with a full-span slotted flap having a 25%wing chord_ and with a 0.40c full-span double slotted flap.

All tests were madewith the propeller windmilling and with power on. The tail was removed. The model was a 1/5 scale of the Curtiss P-36A.

There was a decrease in effective dihedral when moving from the high wing model to the low wing model due to the flow around the fuselage.

The adverse effects of lowering a wing appeared to be increased for the power on condition for all flap positions.

There was a greater adverse effect of power on the low-wing model.

The slip stream affects the dihedral effect in two ways.

Reasons i. An increased dynamic pressure_ increased lift over the part of the wing in the slip stream. For yawing_ the center of pressure for the added lift due to the slip stream lies somewhere on the trailing wing_ therefore giving an unfavorable rolling moment.

2. Increased dynamic pressure increases fuselage interference which has been discussed.

The model with double slotted flap was not tested at a lift coeffi- cient low enough to permit the determination of the effect of this flap on effective dihedral.

Flap deflection seemsunfavorable for both wing locations and for both power conditions.

Flap deflection appears to have a slightly greater adverse effect on the low-wing than on the high wing model. Tail-on tests of the samemodel have showeda small opposite effect.

There seemedto be no definite variation of the effect of flap deflection with lift coefficient.

TN i071 WINDTUNNEL INVESTIGATION OF BOUNDARY-LAYER CONTROL BY SUCTION ON THENACA653-418 _ a = 1.0 AIRFOIL SECTION WITHA 0.29-AIRFOIL- CHORD DOUBLE SLOTTED FLAP_John N. Quin% Jr._ June 1946 An NACA653-418 airfoil was tested in the low-turbulence tunnels at Langley. The airfoil had a suction slot at 0.45 chord. Reynolds numbers tested were 1.9_ 3.4_ 6.0xlO 6. Suction coefficient range - Q) from 0 to 0.040 (CQ UoCb Results and Conclusions I. Max CL = 4.16_ Flap 6 = 65°_ R.N. = 3.4xi06_ CQ = 0.040 Flap 6 = 0°_ CQ = 0.040_ R.N. = 3.4xi06_ Max C L = 2.5 2. Without suction Max CL = 1.5 at 6 = 0°_ CLmax = 3.51 at 6 = 65 ° 3. Max CL was still increasing for flow coefficient at highest CQ used.

4. At flap 6 = 65°_ R.N. appears to have little effect on CLmax for flow coefficients greater than 0.012.

5. At CQ = 0.024_ R.N. = 1.9xi06_ Flap 6 = 65°_ leading edge roughness (carborundum particles) reduced CLmax from 3.88 to 3.16. For CQ = 0_ roughness reduced CLmax from 3.11 to 2.84.

6. Angle of attack for CLmax at any combination of flap angle_ R.N._ and CO was within 3° of angle of attack for CLmax at R.N. = 6xl0d_ 6 = 0°_ CQ = 0.

TN I0 74 TESTS OFA FULL-SCALE HORIZONTAL TAIL SURFACE IN THELANGLEY 16- FOOTHIGH-SPEED TUNNEL_ Carl F. Schueller_ Peter F. Korycinski_ and H. Kurt Strass_ May 1946 Tests were conducted to determine the aerodynamic characteristics of a full-scale semispanhorizontal tail surface. The tests were carried out to M = 0.7 except when maximum loads were reached at lower speeds.

Increasing the Mach number from 0.2 to 0.7 resulted in a marked increase (-0.0015 to -0.0032) in the rate of change of the hinge- momentcoefficient with elevator deflectio% (Ch6)_ a small in- crease (0.0025 to 0.0027) in the rate of change of hinge-moment coefficient with angle of attack_ (Ch_ _ and an appreciable loss (0.51 to 0.34) in elevator effectiveness. The loss in elevator effectiveness is believed to be because the gap was unsealed.

The desired value of hinge-momentcoefficient for elevator deflec- tion of -0.0015 and hinge-moment coefficient for angle of attack of 0.0 could be obtained by having a modified blunt nose and cusped contour behind the hinge line of the elvevator. This modi- fication also removed the aerodynamic hysteresis of the elevator.

Trailing edge strips of i/8-inch diameter and 24%span length on the metal elevator reduced the value of Ch_ = 0.0020 to 0.0_ but with an accompanyingincrease in Ch6 from -0.0015 and -0.0040 at M = 0.35.

.O8 .O6 Ch .04 ch .02 !

! !

0 .2 .4 .6 M TN 1085 FLIGHTTESTS OF EXPERIMENTAL BEVELED-TRAILING-EDGE FRISEAILERONS ONA FIGHTER AIRPLANE_ R. Fabian Goranson_July 1946 Purpose - To examine aileron effectiveness by measuring individual aileron hinge moments_aileron rolling effectiveness_ Pb/2V_ and stick-force characteristics were measured in abrupt aileron rolls over an equivalent-airspeed range from approximately 109 to 276 miles per hour.

Chordwise and spanwise gaps were sealed with doped fabric.

The scatter in hinge momentand stick-force data is attributed to the friction in the control system.

Aileron deflection range 22° - 24½ ° for large deflection test.

Aileron deflection range ± 14° for small deflection range.

Small Deflection (± 14°) Under conditions of steady maximum rolling velocity_ the aileron trim angles indicated that the ailerons floated downwardand the downwarddeflections increased as the speed was increased. This effective droop increased the slope of the stick force curve or gave it an unfavorable gradient. With gaps unsealed the tendency to droop was decreased.

For approximately equal increments of stick deflection the incre- ments of the downgoing-aileron angle decreased as deflection in- creased_ where as increments of up-going aileron angle increased.

Large Deflection (220-24½ ° ) The odd result of stick-force gradient with aileron deflection decreased as speed was increased_ was obtained.

At 202 mph the right aileron stalled between -23 ° and -24 ° .

Smooth but rapid increases in hinge moments were found at high up deflections of the left aileron.

For the large-deflection tests the tabs were deflected downward 5° .

The large deflection tests were terminated at the relatively low speed of 202 mph because the elastic control system would cause dangerous overbalance at high speeds.

Elasticity in the control system adversely affected the aileron control forces by increasing the stick-force gradient through the small deflection range and causing overbalance at large deflections.

Conc lus ions i. The experimental ailerons provided linear variation of rolling moment with deflections from -24½ ° to 22 ° .

2. The ailerons provided a sufficient degree of balance to obtain a range of aileron deflection of ± 24 ° with a stick force of 32 pounds at 202 mph s the highest test speed s when a rigid control system is used.

3. With the test-airplane control system s the stick force gradient was heavy at small deflections and the ailerons were overbalanced at large deflections.

4. With a control system flexibility equal to that of the system of the experimental fighter plan% the aileron stick forces would be unsatisfactory at a speed of 300 mph and more.

5. Small protuberances on the leading edge of the balance area of the Frise ailerons may cause overbalance or premature stalling of the balance on the up-deflected aileron.

6. Extending the aileron 18" on the outboard end would increase the aileron rolling effectiveness 20%.

TN 1087 LANGLEY FULL-SCALE-TUNNEL INVESTIGATION OF THE FUSELAGE BOUNDARY LAYER ON A TYPICAL FIGHTER AIRPLANE WITH A SINGLE LIQUID-COOLED ENGINE_ K. R. Czarnecki and Jerome Pasamanick_ June 1946 Purpose - To determine the thickness and shape of profile of the boundary layer at various locations on the fuselage of a typical monoplane fighter airplane with a single liquid-cooled engine.

Model was investigated without a propeller over angle-of-attack ranges from -1.7 ° to 4.8 ° (dive condition to maximum rate of climb condition). A full-scale model was used. No ducts or tail surfaces were used. Tunnel airspeed was 63 mph. The Reynolds number was 3_200_000 based on mean geometric chord.

E iD ,C IB A OA = 14.9% fuselage OB = 32.6% fuselage OC = 49.4% fuselage OD = 61.0% fuselage l I I I I O OE = 81.6% fuselage Pressure measurements were taken on top_ bottom and both sides independently to avoid tandem effects of other measuring devices.

The boundary layer ahead of B (leading edge of wing) never exceeded i"_ but after B 6 increased quickly and was affected by pressure gradient.

The amount of air that must be removed to insure effective inlet performance per unit slot length should not exceed VS*_ where V = local velocity outside boundary layer and 6* = displacement thickness of boundary layer.

Increasing the angle of attack gave a larger 6* on top but a small 6* on the bottom.

The boundary layer on top of the canopy was very thin.

Reasons: i. Some of it swept off to the sides of the windshield.

2. The pressure gradient was favorable over windshield and canopy.

A maximum value of 6* of nearly 1.2 inches was obtained at the most rearward station_ E.

H is the boundary layer shape parameter = 6*/momentum thickness of boundary layer. Therefore H is an indication of turbulence. H increased slightly toward the rear of the fuselage. Variation of H with angle of attack was small. Since from various past test separa- tion has occurred at H values between 1.8 and 2.6_ separation does not occur on this fuselage because the average H value for all stations was 1.3 - 1.4.

Conclusions I. Maximum displacement thickness of boundary layer was 1.2 inches at E.

2. Favorable pressure gradient over the windshield-canopy combina- tion thinned the boundary layer on top of the canopy.

3. The adverse pressure gradient in wing fuselage juncture greatly increased the displacement thickness toward the rear of the juncture.

4. Separation did not occur.

TN 1099 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATIQN OF SEALED 0.22-AIRFOIL- CHORD INTERNALLY BALANCED AILERONS OF DIFFERENT CONTOUR ON AN NACA 65(112)-213 AIRFOIL_ Albert L. Braslow_ July 1946 A two-dimensional wind-tunnel investigation was made of an NACA 65(112)-213 airfoil with two different sealed_ internally balanced ailerons. One was a regular airfoil section and the other modified so the cusp near the trailing edge was partly eliminated.

It was found that modifying the aileron increased the effectiveness at small deflection angles (< ± i0) and decreased the effectiveness at larger angles. It also caused the rate of change of aileron section hinge-moment coefficient with both section angle of attack and aileron deflection to increase positively. With ailerons neutral_ there was about a nine percent increase in section C L for the modified_ but there was no appreciable change in the section drag coefficient_ rate of change of section C L with section angle of attack_ and airfoil critical Machnumber.

TN Iii0 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OFAN APPROXIMATELY 14-PERCENT-THICK NACA 66-SERIES-TYPE AIRFOIL SECTION WITHA DOUBLE SLOTTED FLAP_Albert L. Braslow and Laurence K. Lofti% Jr._ August 1946 A two-dimensional wind-tunnel investigation was madeto develop a double slotted flap on an approximately 14%thick modified NACA 66 series airfoil section. Tests were madeon a 24 inch chord model formed by a straight-line fairing between a modified NACA66(215) - 214 root section and a modified NACA65(112)-213 tip section.

Only a single pivot point could be used because of the actual wing structure so the optimumpivot point was sought along with best vane positioning and size on the 0.23 chord flap.

A point at 82.27% chord behind the leading edge and 14.67%chord be- low the airfoil chord line was used as the pivot point. As the Reynolds numbersvaried from 2.3xi06 to 6xI06_ the CLmaxincreased_ but from 6x106 to 9xi06_ it did not increase. A CLmaxof 3.0 was obtained with a flap deflection of 55° using a vane of 0.0854 air- foil chord length.

L.E.

Airfoil Chord Line To --77.63%¢ 44.25 ° This vane with the configuration shown had higher coefficients of lift and was less sensitive to changes in vane position and deflection.

TN 1139 FLIGHT TEST OF AN ALL-MOVABLE HORIZONTAL TAlL WITH GEARED UNBALANCING TABS ON THE CURTIS XP-42 AIRPLANE_ Harold F. Kleckner_ October 1946 Initial tests were reported in reference one when the all-movable horizontal tail on the Curtiss XP-42 had a servotab control arrangement. The servotab gave near-zero variations in stick force with elevator angle which gave pilots a better chance to pull out of dives_ but the elevator control with servotab was found unsatisfactory because the light stick forces madethe pilot feel uneasy in handling the plane. This report examines the use of a stick connected directly to the tail with geared unbalancing tabs. The new tail was all-movable.

Once centering springs and friction had been added_all test pilots agreed that the all-movable tail was a satisfactory longi- tudinal control (like a good elevator).

Whenthe all movable tail was comparedto a fixed stabilizer tail of the P-36A the all-movable tail was found to have a higher stability possibly due to the fact that the fuselage gaps were partly sealed on the all-movable tail.

Elevator control in turning flight_ sideslips_ stalls_ landing_ and triming were found to be satisfactory. The elevator control in take-off was not as good in the all-movable tail as for a con- ventional tail thus the all-movable tail provides more control for a tricycle landing gear since a higher speed is required for take- off.

The all-movable tail is capable of developing a greater downward tail load in landing. A reduction in tail area is possible with the all-movable tail if more forward positions of center of gravity are used.

Spin recovery for the all-movable tail is expected to take place with ailerons and rudder only because the forces on the stick in spin are too great for the pilot to handle. After recovery the normal control will resume.

For comparable tail sizes the all-movable tail would appear to offer no advantage over a conventional tail in regard to control characteristics at speeds approaching that for which severe com- pressibility effects occur.

Conclusions i. The unsatisfactory control present in the all-movable tail with servotab was removedwhen the pilot's stick was connected directly to elevator and when geared unbalancing tabs were used.

2. Springs between tabs and elevators brought about longitudinal stability.

3. It was found necessary to restrict the maximum down-elevator deflection to 6° in order to eliminate powerful nose-down pitching momentsin take-off.

4. Stick centering springs were required to increase stick forces in landing.

5. With an all-movable tail reduced in area 35%below that of the conventional fixed-stabilizer tail_ the airplane would have satis- factory characteristics over the sametotal center-of-gravity range.

6. For an all-movable tail, spin control would have to be provided by rudder and aileron action because of the tail stalling.

7. There is no inherent aerodynamic advantage or disadvantage of the all-movable tail over a conventional elevator and fixed stabilizer of comparable size at Mach numbers below those for which severe compressibility effects are encountered.

TN 1151 SUMMARY OF DRAG CHARACTERISTICS OF PRACTICAL-CONSTRUCTION WING SECTIONS_ John H. Quinn, Jr., January 1947 The effects of surface roughness_ surface waviness_ compressive load_ and de-icers on the drag characteristics of a practical- construction wing section were considered and evaluated. These surface conditions generally included the original condition as received from the manufacturer and a numberof improved conditions obtained by glazing, sanding, painting, or by a combination of these processes. The airfoils were both the NACA230- and 6- series sections.

The improved conditions were obtained by one or more of the follow- ing finishing procedures.

i. Camouflage painted - painted with synthetic-enamel camouflage paint.

2. Sanded- paint specks and other similar excrescences removed.

3. Glazed - nicks, dimples around rivets_ and seamswere filled with putty and sanded.

4. Painted - painted with gray primer surfacer and sanded with No. 320 carborundumpaper.

5. Faired - rebuilding surface to reduce the number and size of large surface irregularities.

Mach numberswere no greater than 0.2.

Surface Roughness When spar joints and similar surface irregularities occurred in a region of normally laminar flow, the section drag coefficient of several NACA6-series airfoil sections as received ranged from 0.0062 to 0.0086. A combination of improvement in surface smooth- ness obtained by glazing_ painting_ or minor refairing reduced these drag coefficients by an amount from 0.0022 to 0.0035.

Elimination of minor surface roughness by local glazing and paint- ing helped to maintain these values of the section drag coefficient over a rather large range of Reynolds numbers. Glazing and painting these models did not eliminate the adverse effects of surface unfairness or waviness where it existed although it usually lessened it.

Surface Waviness It was possible to calculate with reasonable accuracy the variation of section drag coefficients with Reynolds number for two smooth NACA 6-series airfoil models on which the surface waviness had been reduced beyond the point where an effect was noticeable on drag.

The improvements in surface smoothnessand waviness brought about by glazing_ painting_ and minor refairing was in most cases suffi- cient to reduce the drags of unfinished practical-construction wings to values closely approaching those for a fair and smooth airfoil model of corresponding section_ at least at Reynolds numbers up to approximately 20x10 6.

Compressive Loads Slight permanent set of the wing skin or rivets caused by compres- sive loads produced little or no adverse effects on the drag char- acteristics of two wing sections designed to retain true contours under flight loads.

De-Icers The drags of airfoil sections increased considerably by the addi- tion of leading edge de-icer boots_ but the difference in drag usually associated with the airfoil sections of different series are masked for thickness ratios of approximately 15 percent.

TN 1167 PRESSURE DISTRIBUTIONS AND FORCE TESTS OF AN NACA 65-210 AIRFOIL SECTION WITH A 50-PERCENT-CHORD FLAP_ Milton M. Klein_ January 1947 Pressure distributions and force measurements were made at low Mach numbers and high Reynolds numbers on an NACA 65-210 airfoil employing a 50% chord plain flap. The tests were run with deflec- tions of 0o_ 4°_ 7°_ and i0 °. It was found that considerable re- duction of the drag coefficients above the low-drag range of the plain airfoil may be effected by the use of small deflections of a large-chord flap. The variations of maximum lift_ minimum drag_ and pitching moment at minimum drag with flap deflection were nearly linear within the range of flap deflections tested. Also_ reason- ably accurate values of the angle of zero lift and the pitching momentcoefficient for airfoils with large-chord flaps may be obtained from thin-airfoil theory.

,010-[ _1.6 CLmax CDmin .006 1_/__1"2 CMc/_ -.1 atC_ -112_ I Drag -"_._.___..__ 2 4 6 8 10 Flap Deflection, degrees TN 1191 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF 4 TYPES OF HIGH-LIFT FLAP ON AN NACA 65-210 AIRFOIL SECTION_ Jones F. Cahill_ February Tests for aerodynamic characteristics of NACA 65-210 airfoil with 4 flap configurations: 25% chord single slot-flap with trailing edge of slot lip at 843 903 and 97.5% chord 3 and 31.2% chord double slotted flap. CLmax = 2.47 for single flaps 3 CLmax = 2.73 for double flaps.

As flap deflection increased 3 optimum position for the flap was close to the upper lip of the slot. CLmax was very sensitive to small movements of flap. CLmax increased with Reynolds numbers from 2x10 6 to 6xi06_ then decreased. Roughness of the wing caused a decrease in CLmax except for large flap deflections. Pitching moment increments caused by flap deflection were higher (&C L const) for double slotted flap than for the single slotted flap with shortest slot lip3 but were about same as the single slotted flap with medium slot lip. Loss in CL caused by trimming loads on tail did not change the relative effectiveness of flaps.

A 24" chord model of the NACA 65-210 airfoil section equipped with 3 single slotted flaps having various slot-lip extensions and with a double slotted flap was tested to develop flap configurations for maximum lift. The maximum lift coefficient (CLmax) with each of the single slotted flaps was about 2.47 and the double slotted flap was 2.73 at Re = 6x106.

As flap deflection increased_ the optimum position of flap became closer to the upper slot lip and the sensitivity to small flap movements increased.

In all cases_ C_a x was increased by increases in Reynolds number (Re) in the range from 2xlO 6 to 4 or 6xl0r_ but some cases indicated that CLmax tended to drop above 4 or 6x10 O Reynolds numbers. The decrement in maximum lift caused by standard roughness decreased as the flap deflection was increased and at the higher deflections was approximately the same as the decrement obtained with the plain airfoil.

Pitching moment increments caused by flap deflection were higher at a constant value of lift increment for the double slotted flap than for the single slotted flap with the shortest slot-lip extension but were approximately equal to the pitching moment increments for the single slotted flap with the intermediate slot-lip extension.

The loss i% lift coefficient caused by trimming loads on the tail did not change the relative effectiveness of the flaps.

TN 1212 EFFECT OF REFLEX CAMBER ON THE AERODYNAMIC CHARACTERISTICS OF A HIGHLY TAPERED MODERATELY SWEPT-BACK WING AT REYNOLDS NUMBERS UP TO 8_000_000_ D. William Conner_ March 1947 Tests were conducted in the Langley 19-ft pressure tunnel on two highly tapered_ moderately swept-back wings of identical plan form. One of the wings was of NACA 6-series symmetrical airfoil sections and the other wing incorporated the same basic airfoil sections but had cambered and reflexed mean lines. The Reynolds Number Range was 3_000_000 - 8_000_000. The wings were tested without flaps_ control surfaces_ landing gear_ nacelles_ or other protuberances.

Density of air - 0.0052 slugs per ft 3 Dynamic pressure - 20 - 145 psf Mach No. - 0.08 -- 0.21 Angle of attack - from below zero lift to beyond the stall Lift_ drag_ pitching moment_ profile drag_ and stalling character- istics were measured.

The leading edge of each wing with roughness applied was also tested.

For the 2 airfoils the shape of the lift curves were similar as was the CLmax for untrimmed condition.

The stall patterns were also similar. The addition of camber slightly delayed the beginning of stall_ but once started it proceeded more rapidly than on the symmetric wing.

With wing smooth_ the profile-drag coefficient at C L = 0.2 in- creased with increasing Reynolds number. The profile drag tests were in good agreement. Adding cambermovedthe neutral point in the low-drag range of lift coefficient ahead about 2%of the mean aerodynamic chord.

.020 .016, Symmetrical / CDo .o,2: Wing -_ / .008 .004 - I I I I ' I I , -0.2 0.2 0.6 1.0 CL Near maximum lift the pitching moment coefficient was more positive for the cambered wing than for the symmetrical wing by an amount that varied both with lift and Reynolds number.

Any drag benefit shown by adding camber disappeared with roughness applied.

The comparative values of drag coefficient for C L > 0.3 were less for the symmetrical wing than for the cambered wing thus indicating the need for maintaining a smooth surface in order that the benefit of a camber mean line may be utilized.

With wing smooth - maximum lift coefficient increases with increasing Reynolds number With wing rough - maximum lift independent of Reynolds number With the wings both smooth and rough s increasing the Reynolds number did not noticeably affect the pitching moment of the wings at low values of lift coefficient.

Application of roughness had a destabilizing influence on both wings.

TN 1228 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF A IO.7-PERCENT-THICK SYMMETRICAL TAlL SECTION WITH A 0.40 AIRFOIL-CHORD CONTROL SURFACE AND A 0.20 CONTROL-SURFACE-CHORD TAB_ Albert L. Braslow_ June 1947 An investigation was made of a 10.7% thick symmetrical tail section equipped with a flat-side 0.40 airfoil-chord flap having a 0.333 flap-chord overhang and a plain 0.20 flap-chord tab.

Sealing the tab nose gap generally increased the flap lift effec- tiveness and tab hinge-moment effectiveness. Sealing the flap gap increased the rate of change of section C L with both angle of attack and flap deflection_ negatively increased the rate of change of flap section hinge-moment coefficient (Chf) with both section angle of attack (do) and flap deflection (6f) at a 0 ° angle of attack and 8f; eliminated sharp irregularities in the variation of Chf with do; and greatly reduced all but the minimum values of section drag coefficient at all flap deflections tested.

Sudden decreases of lift and large increases of flap and tab hinge moment occurred through a limited range of angle of attack when the flap was deflected beyond the angle at which the flap leading edge departed from the airfoil contour.

The effectiveness of the tab in reducing flap-hinge moments was large up to a tab deflection of i0 ° but decreased appreciably at larger deflections of the tab.

TN 1236 DRAG TESTS OF AN NACA 65(215)-I14_ a = 1.0 PRACTICAL-CONSTRUCTION AIRFOIL SECTION EQUIPPED WITH A 0.295-AIRFOIL-CHORD SLOTTED FLAP_ John H. Quin% Jr._ April 1947 Drag tests of the NACA 65(215)-114 _ a = 1.0 practical construction airfoil section gave the following results: In the "as received condition"_ at a CL = 0.i_ the model had a minimum drag coefficient (CDmin) of 0.0041 at a Reynolds number of 12x106 (Re = 12xi06). At this point the C D started increasing with Re to a value of 0.0055 at Re = 48xi0 6.

Using production finishing procedure reduced the CDmin to 0.0039 for Re = 12x106 to 20x106 but C D increased to 0.0055 up to Re = 62xi06 and then remained constant to Re = 80x106. Fairing a rather sharp wave at .2 chord on both surfaces reduced CDminto 0.0038 for Re = 10xl06 to 20x10 6 and then increased to C D = 0.0049 at Re = 40x106. Waxing the model seemedto have no effects. With production finish_ a 4° flap deflection of the slotted flap increased CDminfrom 0.0039 to 0.0046 at Re = 16x10 6. The center of the low- drag range of CL'S was increased from 0.08 to 0.18 by the flap deflection. Sealing the gap on the lower surface had no effect on the C D at a C L = 0.i_ but reduced the low drag-range of CL'S from 0.3 to 0.2. The C D at C L = 0.22 was 0.0044 for the gap-sealed condition_ or 0.0003 less than that for the gap-open condition at the same C L.

TN 1248 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS OF PLAIN ANDBALANCED FLAPS WITH SEVERAL TRAILING-EDGE ANGLES ONAN NACA 0009 TAPERED SEMISPAN WING_H. Page Hoggard_ Jr._ and Elizabeth G. McKinney_April 1947 Purpose - to determine the aerodynamic characteristics of an NACA 0009 tapered semispanwing equipped with a plain and balanced flap having three different included angles at the trailing edge.

A comparison was madebetween both calculated lift and hinge moment coefficients with the experimental value. The effects of overhang_ gap_ and trailing-edge angle were also found.

Three flaps of the sameplan form but with different included angles at the trailing edge were used. Each flap was tested with gap open and gap sealed with impregnated fabric. The flaps were 30%chord.

Two Models Tested Plain Flap Overhang dynamic pressure = 13 psf air velocity = 72 mph effective Reynolds no. = 2_700_000 Lift Effects i. With gap sealed_ an increase in overhand had small and irregu- lar effects on CL at constant _ and usually increased (_)C L where 6 = flap deflection angle. With gap open a decrease in (CL) _ was formed by increasing overhand while (_)CL_v Hinge Moment C L = hinge moment coefficient I. Decreasing the balance chord_ decreasing the beveled-trailing- edge angl% and_ in general_ sealing the gap of the flap nose made _C h _C h values of (_-_) and (_) become more negative.

2. Increases in'trailing-edge angle tended to decrease slightly _C h the effect of the overhang on (_--F_)but to increase the effect on _C L vv _C L (_). Ref. 9 describes the opposite effect for (_).

3. The bevel seems to decrease the effectiveness of overhang.

The break in the airfoil surface before the overhang increases the effectiveness of the bevel. Therefore the affects of overhang on hinge moment coefficients varied.

Drag i. Drag was approximately constant for small C L and small 6.

2. At large deflections the lift decreased with an increase of the trailing-edge angle for approximately the same amount of drag.

Pitching Moment Coefficient i. Increasing the angle at the trailing edge moved the aerodynamic centers due to angle of attack and flap deflection forward.

Differences between the measured values of the lift and hinge- moment parameters and values calculated from two-dimensional data by lifting-surface theory wer% in general_ no greater than the difference between the measured values for wings of the same aspect ratio but with different chord distributions.

METHOD FOR CALCULATING WING CHARACTERISTICS BY LIFTING-LINE THEORY TN 1269 USING NONLINEAR SECTION LIFT DATA_ James C. Sivells and Robert H.

Neely (Superseded by Report 865)_ April 1947 A method is developed and presented for determining the aerodynamic characteristics of wings using nonlinear section lift data. The method is based on lifting line theory and is therefore subject to the limitations of this theory_ i.e. the present method should not be expected to give very good results for wings of low aspect ratio or large sweep.

The method expresses the lift distribution in terms of a trigono- metric series and this trigonometric series is then introduced fnto the expression for the induced angle of attack. The problem of determining the induced angle of attack then becomesone of determining the coefficients in the trigonometric series.

The problem of determining the lift distribution becomesone of successive approximation. One assumesa lift distribution based on two-dimensional data. Using this lift distribution the induced angle of attack is calculated. Using this induced angle of attack a new lift distribution is calculated using the non- linear section data. The procedure is repeated until the lift distribution becomesconstant.

The procedure is applied to several wings and the results are comparedwith experimental results. This comparison indicates that the procedure gives good results in the cases tried.

TN 1270 EXPERIMENTAL ANDCALCULATED CHARACTERISTICS OF SEVERALNACA 44- SERIES WINGS WITHASPECT RATIOS OF 8_ i0_ AND12 ANDTAPER RATIOS OF 2.5 AND3.5_ Robert H. Neely_ ThomasV. Bollech_ Gertrude C.

Westrick_ and Robert R. Graham_ May 1947 The aerodynamic characteristics of seven unswept tapered wings were determined by calculation from two.dimensional data and by wind- tunnel tests in order to demonstrate the accuracy of the calcula- tions and to showsomeof the effects of aspect rati% taper rati% and root thickness-chord ratio. On the basis of comparisons made at equal values of Reynolds number_it was found that reasonable agreementwas obtained between calculated and experimental wing force and momentcoefficient characteristics. The method of calculation which allowed the use of nonlinear section lift curves gave better agreement with experiment at high angles of attack than did the method which assumedlinear lift curves. The two methods of calculation gave different spanwise lift distributions at maximum lift because of the twist in the wing.

The values of maximumlift-drag-ratio (L/D)max of the smooth wings increased with increasing aspect ratio throughout the range investi- gated (Re = 1.5 to 7.0xi06_ M = 0.06 to 0.25_ _ = -4 ° to stall) in spite of the increased drag of the thicker root sections associated with the higher aspect ratios. The values of (L/D)max for the rough wings of taper ratio 3.5 indicated the same trend; however_ the values for the wings of taper ratio 2.5 showedno gain when the aspect ratio was increased from I0 to 12_ apparently because of the larger increment of profile drag due to roughness on the thicker root sections of the aspect ratio = 12 wings. The decrement in (L/D)max due to roughness was considerably greater than the incre- ment due to changing the aspect ratio through the entire range investigated.

The CLmax decreased with increasing aspect ratio mainly because of the associated increase in root thickness-chord ratio.

TN 1277 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF THENACA 641-012 AIRFOIL EQUIPPED WITHTWO TYPES OFLEADING-EDGE FLAP_Felicien F.

Fullmer_ Jr._ May 1947 An investigation was madein the Langley two-dimensional low-turbu- lence pressure tunnel to determine the characteristics of leading edge flaps used as high-lift devices. The investigation_ con- ducted at a Reynolds numberof 6.0xi06_ included tests of two 10-percent-chord leading-edge flaps_ one intended to slide forward along the upper surface and the other hinged near the leading edge on the lower surface of an NACA 641-012 airfoil_ with and without a 20-percent-chord trailing-edge split flap. Section lift char- acteristics and lift characteristics with leading edge roughness for the optimum flap arrangements were shown.

Tunnel corrections were madefor _o_ CL_and Cmc/4.

Lift Characteristics i. The leading-edge flap is believed to produce increases in CLmaxand in the angle of attack for CLmax by reducing the magni- tude of the pressure peaks and the magnitude of the adverse pres- sure gradient usually associated with the flow conditions near maximum lift of the plain section.

2. The effect of the leading-edge flap at angles of attack well below those for maximum lift is to act as a spoiler on the lower surface of the airfoil and thus cause a large reduction in lift.

3. The maximum section lift coefficient increments for the opti- mumupper- and lower-surface leading-edge flap arrangements on the plain airfoil were 0.43 and 0.12_ respectively. The angle of attack increments were 4° and 1.4° .

4. The highest section lift coefficient 2.98 was obtained with the leading edge flap and the trailing-edge split flap.

5. The lower-surface leading-edge flap installation was less sensitive to leading-edge roughness than the upper-surface leading- edge flap arrangement.

TN 1291 COLLECTION ANDANALYSIS OFWIND-TUNNEL DATA ONTHECHARACTERISTICS OF ISOLATED TAlL SURFACES WITHANDWITHOUT ENDPLATES_ William R.

Bates_ May 1947 The aerodynamic characteristics of 19 isolated tail surfaces have been determined by wind-tunnel tests and tests have also been made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. The data from these tests have been collected and analyzed.

THIS REPORT WOULD BE EXCELLENT FORTHEDESIGN OF A FLIGHTMANUAL.

It contains drawing and charts for different tail surfaces with and without end plates.

Electrical strain gages were used to measure hinge moments.

Dynamic pressure = 13 psf (most) Velocity = 72 mph (most tests) RN(effective ) varied from 278_000 to 653_000 Tests were madeby varying the angle of attack with several fixed elevator settings.

Jet boundary corrections were applied to lift and angle of attack while the lift was corrected for tears caused by the model support strut and fork.

Equation for theoretical computation of lift curve slope AR 2_ CL_= 0.1095 ARE + 2 for this airfoil CL_ - 57.3 e where AR = aspect ratio_ E = effective edge-velocity correction e factor.

The slope of the lift curve was predicted within 10%for all the models by use of the lifting-surface-theory equations.

The increase in lift-curve slope provided by tip located double end plates was shown to be dependent upon the square root of the area of the end plate divided by the airfoil span.

The hinge.momentparameters of elevators with cut-outs could not be predicted accurately. For elevators with no cut-outs_ about 55%of the calculated values of the rate of change of hinge- momentcoefficient with angle of attack and about 65%of the calculated values of the rate of change of hinge-moment coeffi- cient with flap deflection were within i O.0010 of the measured value.

TN 1292 INVESTIGATION OF SUCTION-SLOT SHAPES FORCONTROLLING A TURBULENT BOUNDARY LAYER_ Kenneth Pierpoint_ June 1947 Tests were madeon three types of boundary layer-control suction slots to determine the effects of quantity of air removed_inlet geometry_ and slot internal geometry on the effectiveness of the slot. The tests were conducted on the side wall of a two- dimensional diffuser where the turbulent boundary layer has a shape parameter of 1.8 and a displacement thickness of 0.85 inches_ = 25 000 Re_ _ .

It was found that: The characteristics of the boundary layer downstreanfof the slot are determined only by the quantity of air removed provided the slot has rounded edges.

Nearly maximum effectiveness is obtained when the rate of air flow through the slot is equal to the air flow which would pass at free stream velocity through an area equal to the displacement thickness times the span.

Total pressure loss through the slot may be appreciably reduced by rounding the inlet edges_ inclining the slot and slightly diverging the walls. Slot width is also important in slot effec- tiveness.

TN 1293 TESTS OF THENACA641A212AIRFOIL SECTION WITHA SLAT_A DOUBLE SLOTTED FLAP_ANDA BOUNDARY-LAYER CONTROL BY SUCTION_ John H.

Quinn_ Jr._ May 1947 An investigation has been conducted of the NACA641A212airfoil section equipped with a leading-edge slat_ a double slotted flap_ and a boundary-layer-control suction slot at 0.40 chord to determine the maximum lift coefficients attainable with these high-lift devices alone and in conjunction with one another. The tests were madeover a range of RN from 1.0xl06 to 6.0x106. The effects of boundary-layer suction on the maximum lift coefficient were determined for a range of flow coefficient CQfrom 0 to 0.03_ where the flow coefficient is defined as the ratio of the quantity rate of air flow through the suction slot to the product of the wing area an_ free-stream velocity. Atmospheric pressure was used.

Results i. The maximum lift coefficient and the minimum drag coefficient increased as the suction slot was moved toward the leading edge.

Plain Airfoil Characteristics (RN = 1.0xl06) i. Maximum lift coefficient increased steadily as flow coeffi- cient increased.

2. The minimum profile drag coefficient decreased as flow coeffi- cient increased.

3. An appreciable decrease in CDmin was obtained by increasing the R N from l.OxlO 6 to 3.0El06.

4. Leading edge roughness gave large increase to C D.

Airfoil with Slot Extended i. The maximum lift coefficient increased rather slowly as the slot was moved forward of the airfoil leading edge until a maxi- mum value was reached.

2. With the leading-edge slot in its optimum position_ increasing the flow coefficient from 0 to 0.030 increased the CLmax from 1.86 to 2.46 at a R N = 3.0x106.

3. Increasing the RN decreased the maximum CL attainable with leading-edge slot.

Airfoil with Double Slotted Flap i. Increasing the flow coefficient from 0 to 0.030 with the double slotted flap increased CLmax from 2.82 to 3.12.

2. Increasing R N increased CLmax.

The leading-edge slot and double slotted flap combined produced a CLmax of 3.86 for a 0.03 flow coefficient while only 3.30 for a flow coefficient of 0.

For all combinations of high-lift devices tested_ the decrease in CLmax produced by roughness at R N = 6.0xlO 6 and a flow coefficient of 0.025 was less than that caused by roughness on the corresponding configuration without boundary layer control.

TN 1296 WIND TUNNEL INVESTIGATION OF THE EFFECTS OF SURFACE-COVERING DISTORTION ON THE CHARACTERISTICS OF A FLAP HAVING UNDISTORTED CONTOUR MAINTAINED FOR VARIOUS DISTANCES AHEAD OF THE TRAILING EDGE_ Thomas A. Toll_ M. J. Queijo and Jack Brewer_ May 1947 Wind tunnel tests were made on a modified 651-012 airfoil having a 30-percent airfoil-chord flap with contours simulating various distorted surface-covering shapes to determine the practicability of reducing the effects of distortion by maintaining the undis- torted contour over a small part of the flap chord near the trailing edge. The tests were carried out at Mach numbers of from 0.2 to 0.4 with corresponding Reynolds numbers of from 2_845_000 to 5_380_000. The effects of transition location and of flap gap were also investigated.

It was found that: The effects of surface-covering distortion on lift characteristics are small when compared to the effects of distortion on hinge- moment characteristics.

Approximately 75 percent of the effects of distortion on stick forces can be eliminated by maintaining the undistorted flap contour over the rear 20%of the flap chord.

Whenthe flap has been thickened by distortio% opening the gap at the flap nose or placing transition strips near the airfoil leading edge generally causes the variations of hinge-moment co_ efficient with angle of attack and with flap deflection to become less negative. Opening the gap generally has the opposite effect if distortion consists of a decrease in flap thickness.

The effect of varying the Machnumber over the range0.2! Moo< 0.4 on the hinge momentcharacteristics is very small_ provided the undistorted contour is maintained over the rear 20%of the flap chord.

TN 1299 EFFECTS OFMACH NUMBER ANDREYNOLDS NUMBER ONTHEMAXIMUM LIFT COEFFICIENT OFA WING OF NACA 230-SERIES AIRFOIL SECTIONS_ G. Chester Furlong and JamesE. Fitzpatrick_ May 1947 The effects of Machnumber and Reynolds number on the maximum lift coefficient of a wing of NACA230-series airfoil sections are presented. The ranges of Mach number for the wind-tunnel tests were from 0.i0 to 0.35 and from 0.08 to 0.27; the corresponding Reynolds numberranges were from i_530_000 to 4_530_000and from 2_450,000 to 7_880_000_respectively. The wing was tested with full-span and partial-span flaps deflected 60° and without flaps.

Leading-edge roughness tests were made. Somechordwise pressure- distribution measurementswere made for all flap configurations of the model.

Results i. The peak values of maximum C L are determined by a critical Mach number which is attained by relatively low free-stream Mach numbers (0.2 for the flaps-deflected configurations and 0.25 to 0.30 for the flaps-retracted configurations).

2. The values of maximum lift coefficient are increased when the Reynolds number is increased but the critical pressure coefficient (Mcr) to be reached at lower free-stream Mach numbers.

3. After the critical pressure coefficient has been reached_ the value of CLmax is appreciably reduced by further increases in Mach numbers and there is an indication that the effect of Reynolds number on the maximum lift becomes markedly reduced.

4. The value of CLmax before the critical pressure coefficient is reached is almost entirely dependent on Reynolds number_ but Mach number effect should not be forgotten.

2.4.

2.4' P:33psi Z2, _ 2.2.

E E .J U U 2.O 2,0 ¸ ',,,_P =14.7 psi 1.8 t o I I 1.8 I , , i .I .2 .3 .4 2 4 6 8 Mo Ro x 10 6 TN 1304 WIND-TUNNEL INVESTIGATION OF THE BOUNDARY LAYER AND WAKE AND THEIR RELATION TO AIRFOIL CHARACTERISTICS - NACA 651-012 AIRFOIL WITH A TRUE CONTOUR FLAP AND A BEVELED-TRAILING-EDGE FLAP_ Robert A.

Mendelsohn_ June 1947 An NACA 651-012 airfoil was tested which had a true contour flap and a beveled-trailing-edge flap to determine lift_ drag_ hinge moment_ boundary layer_ and wake characteristics. Lift and hinge- moment data were presented for various angles of attack and flap angles_ and a limited amount of drag and pressure-distribution data was given. Measured velocity static-pressure profiles at various positions on the airfoil and behind the trailing edge were presented. Theoretical boundary-layer parameters_ computed from measured pressure distributions_ were compared with the values determined from velocity profiles.

For boundary-layer_ wake_ and static pressure tests; dynamic pressure = 24.9 psf_ V = 99 mph_ RN = 3.60xi06 For hinge moment_ drag_ and lift tests; dynamic pressure = 39.7 psf_ V = 125 mph_ RN = 4.64xi06 Tunnel corrections were applied only to the angle-of-attack_ hinge-moment_ lift_ and drag data.

Results i. The static-pressure gradient through the boundary layer may be large in regions where the airfoil has a small radius of curvature.

2. A static-pressure rise at the vertical position of minimum wake velocity for some section just behind the trailing edge was shown to exist.

3. For increase in angle of attack and flap deflection_ the pres- sure rise behind the trailing edge was shown to increase.

4. Methods for more accurately predicting the boundary layer in the region near the trailing edge appear to be necessary before satisfactory estimations of hinge momentsfrom calculated boundary layers may be made.

5. In equations which relate the profile drag to the measured boundary-layer or wake characteristics near the trailing edge the static pressure gradient should be taken into account.

TN 1317 WIND-TUNNEL INVESTIGATION OF THEEFFECT OFWING-TIPFUELTANKS ON CHARACTERISTICS OF UNSWEPT WINGS IN STEADY ROLL_Harry E. Murray and Evalyn G. Wells_ June 1947 The investigation included the determination of damping in roll_ aileron effectiveness_ and lateral maneuverability of a tapered and of a rectangular wing. Two tank sizes and two tank locations_ which were believed to be representative of tank installations used in 1947. The tanks were attached to the wings in the out and the down locations.

dynamic pressure = 64.3 psf Reynolds number 940_000 - rectangular wing; I_000_000 tapered wing No jet-boundary corrections were applied to the data_ however_ corrections were estimated for both the rolling momentand the angle of attack.

Results For all tanks an approximately linear variation of rolling-moment coefficient with pb/2V was seen.

Effect of Wing-Tip Fuel Tanks on the Damping Moment i. The effect of tanks on coefficient of damping in rolling in- creases with the size of the tanks and is greater for the tank out position.

E - 0A 0_. -0.5' n oc: 0 _,_k Out $ L _, , .Oi ; U .02 t .06 Tank diameter/Wing span 2. The large tanks in the out location increase the coefficient of damping in rolling about 44 percent at small angles of attack.

larcj_,, tanl_s down small tanks out small tanks down O _C L It was found that (_-_) due to aileron deflection generally in- creased with the addition of tanks; for large tanks the increase was about 16 percent.

If motion is held to rolling and transient effects are neglected then the maneuverability decreased with increasing tank size be- cause the damping in roll increased faster with tank size than does the aileron effectiveness.

Generally the effect of the tanks increased with tank size and was generally greater for tanks mounted out on the tips than for tanks under.

TN 1337 EFFECT OF HORIZONTAL-TAIL POSITION ON THE HINGE MOMENTS OF AN UNBALANCED RUDDER IN ATTITUDES SIMULATING SPIN CONDITIONS_ Ralph W. Ston% Jr._ and Sanger M. Burk_ Jr._ June 1947 Hinge moment measurements were made on an unbalanced rudder of a rectangular vertical tail for six positions of the horizontal tail. The hinge moment measurements were supplemented by lift tests to determine the airflow about the vertical tail. The results were based on the rudder-pedal forces.

Tail Positions I ]I ]]I low-forward low-outer low- rearward high-forward high-center high- rearward The elevator and rudder chords were 33.3 percent chord of airfoil chord.

The elevator and rudder had no aerodynamic balanc% but the rudder was mass balanced so that no moment would be exerted on the strain gage due to rudder weight.

dynamic pressure = 2.66 psf angle of attack range 0 ° - 90 ° yaw range 30 ° - -30 ° No tunnel corrections because of large tunnel and small models.

Rudder Hinge Moments i. In general_ the high forward positions of the horizontal tail (IV) led to the highest values of rudder hinge-moment coefficient_ whereas the low rearward position (III) led to the lowest values.

BC h 2. The slope _8--_-- rudder deflection was not greatly affected by angle the installation of the horizontal tail on the vertical tail or by the various positions of the horizontal tail at low and moderate angles of attack but decreased negatively an appreciable amount at high angles of attack (60° and 80°) which simulate the conditions for very flat spins.

3. The direct effect of shielding of the rudder by the horizontal tail in the normal spinning range of angle of attack is to change the values _Ch/_ _ where _ is the yaw angle.

For planes in the light airplane category it was found that for any deflections the rudder-pedal forces did not exceed 140 pounds and therefore should be well within the capabilities of the pilot.

For heavier airplanes the rudder may require some form of balance.

TN 1352 WIND-TUNNEL INVESTIGATION OF SPLIT TRAILING-EDGE LIFT AND TRIM FLAPS ON A TAPERED WING WITH 23 ° SWEEPBACK_ William Letko and David Feigenbaum_ July 1947 Force tests were run and pressure distributions measured in a wind- tunnel investigation to determine the effects of the size and hinge location of lift and trim flaps on the lift and pitching- moment characteristics of a semispan tapered wing with a quarter- chord sweepback of 23 ° . The flaps tested were split flaps with chords of i0_ 20_ 30_ and 40% chord. The spans of the lift flaps were 20_ 40_ 60_ and 80% and full span. The trim tab spans were i0_ 20_ 40_ and 60% of wing span.

It was found that the maximum lift coefficient of the wing may be increased by about 0.5 without changing the pitching moment about the aerodynamic center by the use of split trailing-edge lift and trim flaps.

Certain lift-flap configurations were self trimming (i.e. lift flaps that produced no increment in pitching moment a_o_t the aerodynamic center)_ and with some of these configurations the maximum lift coefficient of the wing might be increased by 0.4.

Also increments in maximum lift coefficient of the order 0.5 might be obtained by the use of trim flaps. The wing had greater static longitudinal stability with the flaps deflected_ especially for larger flaps.

The chord of the trim flaps used had a negligible effect on the net lift coefficients attainable_ although the use of a large- chord trim flap meant that a smaller span was required. Using a trim flap with the hinge axis moved back to the trailing-edge allowed slightly greater lift increments to be obtained.

The increment in trimmed lift coefficient produced by the lift flap increased with flap chord at a flap span of about 50% of the wing span.

Moving the hinge axis of the lift flaps forward increased the lift-coefficient increment attainable at a i0 o angle of attack with self trin_ning flaps_ however_ the greatest increment in maximum lift coefficient attainable with the self-trimming lift flaps occurred when the flaps were hinged about the 70%chord line.

TN 1368 THEORETICAL ANDEXPERIMENTAL DATAFORA NUMBER OFNACA 6A-SERIES AIRFOIL SECTlONST"Laurence K. Loftin 7 Jr._ (Superseded by Report 903)7 July 1947 The NACA 6A-series airfoil sections were designed to eliminate the trailing edge cusp which is characteristic of the NACA6-series basic thickness forms having the position of minimumpressure at 307 407 and 50 percent chord with thickness ratios varying from 6 percent to 15 percent. Also present are data for a meanline designed to maintain straight sides on the camberedsections.

The 6-series airfoils have a very thin trailing-edge portion which leads to structural design difficulty. To overcome the difficul- ties the trailing-edge cusp was removedand the sides of the air- foil sections were madestraight from approximately 80 percent chord to the trailing edge.

The 7 models tested in the wind tunnel were: NACA 63A010 NACA 63A210 NACA 64A010 NACA 64A2107NACA641A212 _ NACA642A215 NACA 64A410 Lift_ drags and quarter-chord pitching-moment coefficients were found at Reynoldsnumbersof 3xi067 6x106_ and 9x106. Measurements were madewith roughness applied at Reynolds number = 6xlO6. A split flap test was madeat Reynolds number = 6x106.

Results i. The section minimum drag and maximum lift are approximately the same for both series.

2. The lift-curve slopes of smooth NACA 6A-series airfoil sec- tions appear to be essentially independent of airfoil thickness ratio 7 contrasting the trend of the 6-series sections. Leading edge roughness causes the lift-curve slope to decrease with in- creasing airfoil thickness ratio for 6A-series sections.

3. The section angles of zero lift of NACA 6A-series airfoil sec- tions are slightly more negative than those of comparable 6-series sections.

4. The section i/4-chord pitching momentcoefficients of NACA 6A- series airfoil sections are slightly more negative than those of comparable 6-series sections. The position of the aerodynamic center is essentially independent of airfoil thickness ratio for 6A-series sections.

TN 1369 EFFECT OF GEOMETRIC DIHEDRAL ONTHEAERODYNAMIC CHARACTERISTICS OF TWO ISOLATED VEE-TAIL SURFACES_ Robert O. Schad% July 1947 Force tests of two-isolated vee-tail surfaces with various amounts of dihedral were made to provide an experimental verification of a simplified vee-tail theory and the results presented were found to be in good agreement with calculations of NACA ACRNo. L5A03.

The tails had aspect ratios of 3.70 (taper ratio = 0.39) and 5.55 (taper ratio = 0.56) and were tested with dihedral angles of 0° to 50° and 0° to 59o_ respectively.

In general_ the agreement between the calculated data and the experimental data was good except at high dihedral angles where interference between the two panels of the vee-tail occurs. The data also showedthat at high dihedral angles_ the vee-tail is more effective in pitch and less effective in sideslip than the calculations indicate. Also lower measured effectiveness in side- slip than the calculations indicates it is found at the high dihedral angles.

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o 3'0

Angle of Dihodral TN 1377 WIND-TUNNEL INVESTIGATION OF UNSHIELDED HORN BALANCES ON A HORI- ZONTAL TAlL SURFACE_ John G. Lowry and Stewart M. Crandall_ July A wind-tunnel investigation was conducted to determine the charac- teristics of unshielded horn balances on the aerodynamic character- istics of a 0.5-scale model of the left horizontal tail surface of a torpedo bomber (gross wt - 12_910 Ibs_ 490 ft 2 wing; 111.5 ft2 hor. tail). Control characteristics for the airplane were esti- mated from the wind-tunnel data and compared with flight data.

The variation of hinge-moment coefficient with angle of attack and with elevator deflection caused by a change in the siz% of the unshielded horn was approximately a linear function of the ratio of horn area momentto elevator area moment. The lift parameters were not affected appreciably by changes in the size of the horn or by the surface modifications introduced.

Very close agreement between the control-force characteristics of the airplane as determined from flight data and characteristics estimated from wind-tunnel data was obtained when the airplane surface irregularities were simulated on the model.

-- _Wind ,-Horn Chse -_o4- Area -.008- Tail Tail Horn Area Moment Elevator Area Moment Increasing Horn Area --_ TN 1386 WIND-TUNNEL INVESTIGATION OF DROOPED AILERONS ON A 16-PERCENT- THICK LOW-DRAG AIRFOIL_ Ralph W. Holtzclaw and Jules B. Dods_ Jr._ August 1947 A wind-tunnel investigation was conducted to determine the prac- ticability of the drooped-aileron-type lateral-control device on NACA low-drag airfoils. Section aerodynamic characteristics of an NACA 66(215)-216(a=.6) airfoil with an aileron normal profile and with an aileron of straight-sided profile with a modified nose shape were presented for various aileron locations_ hinge centers_ and aerodynamic balances.

Two 0.25-chord ailerons were tested_ one of normal profil% and one of straight-sided profile with a modified nose shape. Various amounts of aerodynamic balance and several drooped positions were investigated. The results were applied to the estimation of lateral-control characteristics of three hypothetical airplanes of widely different sizes.

The c__ c__ c were corrected for tunnel effects but no corrections cI m were applied for hinge moments.

dynamic pressure = 50 psf Reynolds number = 5. ixl06 Mach number = 0.19 Results i. Drooped ailerons can be applied to airplanes as a satisfactory lateral-control devic% as shown by calculations of the lateral- control characteristics of three airplanes of span ranging from 45 feet to 141 feet.

2. The adverse yaw due to full aileron deflection would not be so great as to produce excessive angles of sideslip (rudder locked)_ or so great as to render the rudder incapable of trin_ning the air- plane to zero sideslip.

3. The profile of the drooped aileron of the type tested is criti- cal as evidenced by the nonlinear hinge-moment characteristics of the normal-profile aileron.

4. The effectiveness of the drooped aileron is seriously reduced when the aileron is positioned for minimum drag rather than maxi- mum lift.

TN 1395 WIND-TUNNEL INVESTIGATION OF THE NACA 654-421 AIRFOIL SECTION WITH A DOUBLE SLOTTED FLAP AND BOUNDARY-LAYER CONTROL BY SUCTION_ John H. Quin% Jr._ July 1947 An investigation was conducted of the NACA 654-421 airfoil section with a boundary layer control slot at 0.45 airfoil chord and a 0.32-airfoil-chord double slotted flap.

Generally_ between Reynolds numbers of 1.0xlO 6 and 2o2xi06 and over a range of the flow coefficient from 0 to 0.3_ increasing the Reynolds number tended to increase the maximum lift coefficient below a flow coefficient of 0.015 and tended to decrease the maximum lift coefficient (CLmax) between flow coefficients of 0.015 and 0.030. Greater increases in the CLmax were obtained through boundary-layer control with the flap retracted than with the flap deflected and with the airfoil in the smooth condition than with the airfoil in the rough condition, in the smooth condition at a Reynolds number of 2.2xi06_ increasing the flow coefficient from 0 to 0.015 increased the CLmax from 1.22 to 2.44 with the flap re- tracted and from 3.07 to 3.81 with the flap deflected. Little increase in CLmax for the airfoil with flap deflected was found between flow coefficients of 0.015 and 0.030.

With the flap retracted_ increasing the flow coefficient decreased the minimumsection drag coefficient and maintained low drag co- efficients to high CL'S. The drag coefficients equivalent to the boundary-layer-control power were greater than the reduction ob- tained_ at least over the range of C L for which the drag was measuredwithout boundary-layer-control.

A COMPARISON OF£LIGHT-TEST RESULTS ONA SCOUT-BOMBER AIRPLANE TN 1407 WITH4.7 ° ANDWITHi0 ° GEOMETRIC DIHEDRAL IN THEWING OUTER PANELS_ Charles M. Forsyth and William E. Gray_ Jr._ August 1947 A flight investigation of a scout-bomber airplane with 4.7o and i0 o geometric dihedral in the wing outer panels has been conducted in order to obtain flight-test results pertaining to the upper limit of the wing-dihedral angle for satisfactory handling quali- ties. Satisfactory handling qualities is defined as the rolling momentdue to sideslip shall never be so great that a reversal of rolling velocity due to aileron yaw occurs during rudder fixed aileron rolls and that the control-free lateral oscillations shall dampto 1/2 amplitude in 2 cycles• The airplane tested was a two-plac% midwing_ single-engine scout- bomber.

Comparable test results for both dihedral configurations were presented of data taken from steady sideslips_ rudder-fixed aileron rolls_ rudder kicks_ control-free lateral oscillations and rapid 180 ° turns.

Results i. For the same airspeed and aileron deflection the maximum value of rolling velocity was slightly less for i0 ° dihedral than 4.7 ° .

2. The rolling velocity decreased more rapidly for the plane with i0 o dihedral.

3. Rolling velocity for i0 ° dihedral plane approached zero but never reached it for low-speed rolls.

4. The effective dihedral was calculated from this formula: 2 _CL _pb _ = sideslip angle ( _ (_vV _(_6a_ b = span (57 • 3) _p_ _ _._ " V = time airspeed _T where 6a = total aileron Fef f = bC L deflection _-_/ r F = dihedral < of isolated wing p = rolling velocity The flight and wind-tunnel values of the variation of measured effective dihedral with theoretical effective dihedral showed fair agreement.

5. The rudder kicks with i0 ° geometric dihedral showed the largest variation of rolling velocity with rudder deflection.

6. For the plane with 4.7 ° geometric dihedral the number of cycles for the oscillations to damp to 1/2 amplitude was slightly less with a i0 o dihedral.

7. With both dihedral configurations_ the airplane possessed positive stick-fixed effective dihedral in all conditions tested.

8. As far as meeting the required specifications_ the i0 ° dihedral is acceptable_ but a slight increase in geometric dihedral above the i0 ° might cause a reversal of rolling velocity in rudder-fixed aileron rolls.

TN 1422 EXPERIMENTAL AND CALCULATED CHARACTERISTICS OF THREE WINGS OF NACA 64-210 AND 65-210 AIRFOIL SECTIONS WITH AND WITHOUT 2° WASHOUT_ James C. Sivells_ August 1947 The report studied experimentally and analytically the characteris- tics of the 64-210 and 65-210 airfoils. The parameters studied (section and washout) affected only CL_ zero-lift angl% and stall.

RN = 4.4xI06_ M = 0.17_ Tunnel Pressurized to 34 psi Effect of Section 64-210 had 10% larger CLmax but lower (CL/C_max than 65-210.

Stall of 64-210 began farther inboard and was more sudden_ but 64-210 exhibited less tip stall.

Effect of Washout (Wing-Twist about .25c Line) Addition of 2 ° washout increased _CL= 0 slightly but had little effect on stall except moving it slightly inboard. Larger angles of washout are necessary for significant changes in stall.

TN 1431 INVESTIGATION OF THE AILERON AND TAB OF A SPRING-TAB LATERAL- CONTROL SYSTEM IN THE LANGLEY 19-FOOT PRESSURE TUNNEL_ Owen J.

Deters and Robert T. Russell_ September 1947 Tests of a partial-span model of a large bomber-type airplane were conducted to provide data on the aerodynamic characteristics of the aileron-tab arrangement and of the wing. The aileron-tab arrange- ment included a 20-percent constant percentage-chord aileron having a 54-percent internally sealed aerodynamic balance and a constant- chord tab of approximately 26-percent of the average aileron chord over the span of the tab. Tests were madeto determine the roiling- moment_yawing-moment_and hinge-moment characteristics of the aileron and tab and the effect of midchord wing slots on the char- acteristics of the wing and aileron and tab.

The airfoil sections were the NACA 63(420)-422 at the root_ and at the tip the NACA63(420)-517. The wing model had a 2° dihedral and 2° aerodynamic washout.

dynamic pressure = 105 psf; RN= 8_900_000; MachNo. = 0.18 varied from -4° thru maximum lift; aileron deflection -24° - 17°; tab deflection -20° _ 20° .

Tare corrections were made.

Results i. The effect of opening the slots was as follows: At large angles of attack the C L increased, the C D decreased for a given CL_ and the pitching momentcurve slope becamemore negative.

At small _ the C L was reduced_ the C D for given C L was reduced and slope of pitching momentcurve becameless negative.

2. With slots closed the stall enveloped the aileron before maxi- mumlift was reached and progressed inboard for all flap configura- tions.

3. Opening the slots caused rough and stalled flow over the aileron at low angles of attack_ but at high angles of attack the flow over the aileron was considerably improved over that with slots closed.

4. At high angles of attack the aileron had a large tendency to float upward.

5. With flaps deflected_ the ailerons produced a slightly smaller adverse yawing-momentcoefficient_ an increase in rolling-moment coefficient at negative deflections_ and a decrease at positive deflections.

6. The effect of opening the slot was to impair the hinge-moment characteristics at low angles of attack and to reduce the negative aileron hinge_momentcoefficients at a given angle of attack.

7. At small positive aileron deflections_ the tab was stalled at negative tab deflections in excess of I0° at low angles of attack and at negative tab deflections in excess of 15° at high angles of attack.

TN 1463 INVESTIGATION OFNACA65(112)AIII (APPROX.) AIRFOIL WITH0.35- CHORD SLOTTED FLAPAT REYNOLDS NUMBERS UP TO 25 MILLION_S. F.

Racisz_ October 1947 An investigation of thin airfoil with high lift flap at high Reynolds number to simulate conditions of modern high speed commercial craft was madeto determine the highest maximum lift configurations (idea configurations).

Conclusions Increasing Reynolds number (RN) from 2.4xi06 to 9.0xlO 6 decreased flap angle for (CL)ma x from 45° to 35° or 40° (both give samevalue).

Increasing RNmovedoptimum flap position slightly up and back.

Increasing RNaffects CLmaxand flap position very slightly_ but CLmaxis very sensitive to flap position. Increasing RN delays stall to a higher angle of attack. Lift coefficient increases with RN to 18.0x10 6 then falls off with flap retracted. With flap extended_ peak is at 13.0x106.

TN 1517 WIND-TUNNEL INVESTIGATION OF AN NACA 0009 AIRFOIL WITH 0.25- AND 0.50-AIRFOIL-CHORD PLAIN FLAPS TESTED INDEPENDENTLY AND IN COM- BINATION_ M. Leroy Spearman_ March 1948 Tests were made to determine aerodynamic characteristics. The model had a 2' chord and 4' span. The two flaps tested had nose gaps of 0.005c in width. Flap hinge moments were measured by electrical strain gages. Hinge moment and lift were the two important parameters.

dynamic pressure = 13 psf velocity = 71 mph RN(eff ) = 2.58xi06 The model completely spanned the test section.

All tests were made through an angle-of-attack range from zero to negative stall and from zero to positive stall.

An experimentally determined tunnel correction was applied to the lift.

Results i. The lift curves are fairly linear through 6 of 20 ° for the 0.25c flap and 15 ° for the 0.5c flap.

2. Airfoil stall is accompanied by a rapid increase in hinge- moment coefficient. Airflow separation over the flaps causes the hinge-moment curves to becomenon-linear and sometimes to reverse slop e.

3. Sealing the gaps provided a negative increase in _Ch/_ and _Ch/D6 for both flaps.

4. Whenboth flaps were used together the lift-effectiveness parameter _/J_6. for each flap was less for the flaps independent- ly because of a C L decreased due to a reduction in rigidity.

5. For either flap the hinge momentcaused by deflection_ _Ch/_6 is slightly less when the flaps are used in combination than _en used independently.

6. Theoretical calculations were in close agreement with experi- mental results.

1°6" 1,2" 0.5c, _=10 ° 0.8- _0.25c. 6=10 ° 0,4" n O_ - 0.4 -0.8" Gaps Sealed -16 - 8 0 8 1 6 24 o< WIND-TUNNEL INVESTIGATION OF SEVEN THIN NACA AIRFOIL SECTIONS TO TN 1545 DETERMINE OPTIMUM DOUBLE-SLOTTED-FLAP CONFIGURATIONS_ Jones Cahill and Stanley F. Racisz_ April 1948 The purpose of this experiment was to determine the optimum double- slotted-flap configuration for the seven airfoils tested: NACA 63-210_ 64-208_ 64-210_ 641-212_ 65-210_ 66-210_ and 1410. The airfoils were equipped with a 25%chord main flap and a 7.5% chord fore flap. The 66-210 and 64-208 airfoil sections were also tested with a 10%chord and a 5.6% chord fore flap_ respectively. Lift measurementswere madeat a Reynolds number of 2.4xi06 and up to 9.0x106. The section pitching-moment characteristics and the effect of leading edge roughness on the lift characteristics were measured for each of the airfoil sections at a Reynolds number of 6.0xi06 for a double-slotted-flap position close to the ideal which also allowed the double slotted flap to be retracted as a unit into the wing contour (optimum). The maximum freestream Mach number attained during any of these tests was less than 0.18.

Results i. The optimum fore-flap positions for these airfoils were gen- erally about i percent chord forward and 2 percent chord below the slot lip.

2. For the airfoil section with either a split or double slotted flap_ the maximum section lift coefficient decreased as the posi- tion of minimumpressure was moved to the rear and as the airfoil thickness was decreased to 8%chord.

3. In all cases_ the maximum section lift coefficient increased appreciably as Reynolds numberwas increased from 2.4xi06 to 6.0xi06_ but decreased slightly or remained constant for a further increase in Reynolds number.

4. Increasing the fore flap chord provided increases in the maxi- mumsection lift coefficient of the 64-208 and 66-210 sections with double slotted flaps.

5. The ratio of increment of section pitching momentcoefficient to increment of section lift coefficient at a section angle of A% attack of 0°_ (A--_--) = 0°_ based on the total chord of the airfoil _v L o with the double slotted flap extended was approximately the same as that obtained for the airfoil with the split flap.

6. An unstable pitching-moment break is encountered at the stall for each of the airfoils when equipped with the double slotted flaps and seems to be peculiar to double slotted flaps.

WIND-TUNNEL INVESTIGATION OF THE BOUNDARY LAYER ON AN NACA 0009 TN 1574 AIRFOIL HAVING 0.25- AND 0.50-AIRFOIL CHORD PLAIN SEALED FLAPS_ Jack D. Brewer and Josephine F. Polhamus_ April 1948 The tests were madeto define as thoroughly as possible the char- acteristics of two of the configurations used in a comprehensive investigation of control-surface characteristics and also to pro- vide additional data for comparison with previous boundary-layer analyses. The model had a 2 foot chord and completely spanned the test section. Boundary-layer profil_s were measured by two pressure mice (one on upper surfacej one on lower surface).

dynamic pressure = 16.2 psf_ V = 79.6 mph test RN= 1.49xI06_ turbulence factor = 1.93 The flaps were tested as only one flap existed at a time. Tunnel corrections were applied for the angle of attack. A correction for the effective center location was applied to the mice-tube heights.

Conversion to profiles based on the free-stream velocity was obtained by multiplying the given velocity ratio by the factor K P-P or K = (I-P) ½ where p = o where K = u/u ° qo Many graphs were sketched showing the velocity distributions. No major results were given since obtaining the data was the chief objective in this report.

TN 1579 INVESTIGATION IN THE LANGLEY 19-FOOT PRESSURE TUNNEL OF TWO WINGS OF NACA 65-210 AIRFOIL SECTIONS WITH VARIOUS TYPE FLAPS_ James C. Sivells and Stanley H. Spooner (Superseded by Report 942)_ May 1948 The purpose was to determine the maximum lift and stalling char- acteristics of two thin wings equipped with several type flaps.

Both wings had zero sweep_ an aspect ratio of 9_ and a ratio of root to tip chord of 2.5. The results are as follows: i. At a Reynolds number of 4_400_400 maximum lift coefficients of 2.48 and'2.76_ respectively_ were obtained with NACA 65-210 and 64-210 wing with full span double slotted flaps. These values are approximately 205 percent of the flap neutral values of 1.21 and 1.35 for the respective wings.

2. Addition of the fuselage or the leading-edge roughness caused reductions of 0.i to 0.3 in the maximum lift coefficients of the wings.

3. Increases in maximum lift coefficient was found with increases in Reynolds numbers below 4_400_000. Above this valu% the test Mach number was high enough so that the effects of compressibility appeared to be a contributing factor in causing maximum lift co- efficients to increase less rapidly or to decrease with increasing Reynolds number.

4. The stall of the NACA 64-210 wing was somewhatmore abrupt but slightly farther inboard than that of the NACA65-210 wing.

The fuselage caused the stall to begin inboard near the wing- fuselage junction.

TN 1582 WIND-TUNNEL INVESTIGATION OF EFFECTS OFFORWARD MOVEMENTS OF TRANSITION ONSECTION CHARACTERISTICS OFA LOW-DRAG AIRFOIL WITHA 0.24-CHORD SEALED PLAIN AILERON_ Stanley F. Racisz and Jones F.

Cahill_ May 1948 An investigation was conducted to determine the effects of forward movementsof transition on the section characteristics of a 12% thick low-drag airfoil section with a 0.24-chord sealed plain aileron. Tests were conducted at a Reynolds number of 14x106 and the transition was alternately at the leading edge and at 30% chord.

With the transition at either leading edge or at 30%chord_ it was found that the aileron effectiveness decreased. The negative rate of change of aileron section hinge-moment coefficient with section angle of attack and with aileron deflection decreased; the absolute value of the aileron section hinge-momentparameter relat- ing hinge momentin steady roll to aileron deflection and angle of attack increased; and the rate of change of section lift coeffi- cient with section angle of attack decreased by not more than 3%.

Shifting the transition from 50%chord to 30%generally caused larger changes in the aileron characteristics than those caused by shifting the transition from 30%to the leading edge.

Leading-edge roughness decreased the maximum section lift coeffi- cient by about 0.3; whereas roughness at 0.30 chord had no signifi- cant effect on the maximum section lift coefficient throughout most of the range of aileron deflection tested.

TN 1590 INVESTIGATION OF AN APPROXIMATELY 0.178-CHORD-THICK NACA6-SERIES- TYPEAIRFOIL SECTION EQUIPPED WITHSEALED INTERNALLY BALANCED 0.20- CHORD AILERONS ANDWITHA 0.05-CHORD TAB_Fioravante Visconti_ May 1948 An investigation was madeon an approximately 0.178-chord-thick NACA6-series-airfoil section equipped with 0.20-chord ailerons and with a 0.05-chord tab. The results show that increasing the true-contour aileron profile thickness to form a straight-sided aileron would cause: i) no real effects on the aileron section effectiveness_ 2) a positive increase in the rate of change of aileron section hinge-moment coefficient with both section angle of attack and aileron deflection_ 3) little change at low aileron deflection and a decrease at high aileron deflection of the hinge moment_4) a slight decrease in change of lift coefficient with angle of attack_ and 5) little effect on the maximum C L and C D through the low-drag range for neutral aileron.

Increasing the true-contour aileron sealed internal-balance chord from 0 up to 5]% of aileron chord did not cause the rate of change of aileron section hinge-moments with aileron deflection to become positive and would have a relatively smaller effect on the rate of change of aileron section hinge moments with section angle of attack.

The effectiveness of the tab in reducing the aileron section hinge moments was large at low angles of attack and lower aileron deflec- tions but decreased appreciably at high aileron deflections. At the higher angles of attack the tab effectiveness varied incon- sistently with aileron deflection.

TN 1591 AERODYNAMIC CHARACTERISTICS OF A NUMBER OF MODIFIED NACA FOUR-DIGIT- SERIES AIRFOIL SECTIONS_ Laurence K. Loftin_ Jr._ and Kenneth S.

Cohen_ June 1948 Theoretical pressure distributions were calculated and the experi- mental aerodynamic characteristics determined at low speeds for some NACA four-digit-series airfoil sections modified for high- speed applications. The studies were made at Reynolds numbers (Re) of 3xi06_ 6xi06_ and 9xlO 6. Flap effectiveness was tested at Re = 6x106.

The maximum lift characteristics of the airfoil sections having normal size leading-edge radii and a maximum thickness of 12% chord located at 40% chord very closely approximated by those of NACA 64-series low-drag sections of corresponding thickness and camber.

The CLmax'S of the 10% thick airfoils with one-quarter normal size leading-edge radii and maximum thickness located at 40% and 50% chord were about 35% lower than those of smooth NACA 64-series sec- tions of corresponding thickness and camber. For airfoils equipped with 20% chord split flaps deflected 60°_ the maximum lift of the airfoils with one-quarter normal-size leading-edge radii more nearly approached that of NACA 64-series airfoils. Roughness had no appreciable effect upon the maximum lift of these airfoils.

The CDmin'S of the airfoils with maximum thickness at 40% chord and normal-size leading-edge radii were higher than those of the corresponding NACA 64-series sections. Reducing the leading-edge radius to one-quarter normal size and moving the position of maximum thickness to 40 and 50% chord caused the minimum drag coefficients to be reduced to values about the same as those for corresponding NACA 64- and 66-series sections_ respectively.

Increases in the trailing-edge angle resulting from rearward movement of the position of maximum thickness caused sharp de- creases in the lift-curve slope and pronounced forward movements of the aerodynamic center.

TN 1593 EFFECTS OF NACELLE POSITION ON WING-NACELLE INTERFERENCE_ Charles H. McLellan and John I. Cangelosi The interference effects between an airfoil of high critical speed with no sweepback and a nacelle of high critical speed mounted in various positions with respect to the wing were investigated at Mach numbers up to 0.7 and an angle of attack up to 2.5 ° . An NACA 65-210 airfoil section was used.

The problem of obtaining a wing-nacelle combination which has good high speed characteristics is greatly simplified by the adoption of components which_ by themselves 3 have good high speed character- istics.

The low nacelle position with the nose of the nacelle 0.66 chord ahead of the wing leading edge_ with the upper surface of the wing tangent to the top of the nacelle lin% and with the nacelle center line parallel to the wing chord line gave a reasonable compromise between loss of lift and late drag rise. Moving the nacelle for- ward from the low position with the nacelle nose 0.66 chord ahead of the wing leading edge had little effect on the drag but increased the loss in lift. The nacelle in the most rearward position increased the lift slightly.

The local high negative peak pressures which occurred on the upper surface of the wing fillets for the low nacelle positions could be removed at positive angles by drooping the leading edge of the wing adjacent to the nacelle_ however_ the removal of these peaks had no noticeable effect on the lift and drag characteristics and usually caused peaks on the under surface at small negative _'s.

TN 1597 ANALYSIS OF THE EFFECTS OF BOUNDARY-LAYER CONTROL ON THE TAKE-OFF PERFORMANCE CHARACTERISTICS OF A LIAISON-TYPE AIRPLANE_ Elmer A.

Horton and John H. Quinn_ Jr._ June 1948 An analysis was made of the take-off characteristics of liaison_ type aircraft with and without boundary-layer control capable of carrying a payload of 1500 pounds and operating from small make- shift runways.

The addition of boundary-layer control does not reduce the ab- solute minimum total take-off distance which is obtained with a low wing loading and a moderately low aspect ratio. The effec- tiveness of boundary layer control in reducing the total take-off distance for a given maximum speed improved with increasing aspect ratio and_ for wing loadings of I0 pounds per square foot or more and an aspect ratio of I0 or more_ the addition of boundary layer control (BLC) results in a decrease in the total take-off distance.

For a given maximum speed the ground run was reduced for all con- figurations by the use of BLC. This reduction was negligible for an aspect ratio of 5 but was from I0 to 30%for aspect ratios of I0 to 15.

For a given maximum speed_ the use of BLCresulted in a reduction in stalling speed of 20 to 25%for all configurations. A reduction in the weight of the BLCequipment would result in an appreciable decrease in the total take-off and ground run distances but would give a negligible decrease in stalling speed.

The optimumhorsepower loading for minimumtake-off distance was found to approximately 8.5 to 9.0 pounds per horsepower for the conventional and BLCairplanes_ respectively.

TN 1624 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF AN NACA 64-009 AIR- FOIL EQUIPPED WITHTWO TYPES OFLEADING-EDGE FLAP_F. F. Fullmer_ Jr._ June 1948 An investigation was madeto determine the effect of leading-edge flaps on the CLmax of an NACA64-009 airfoil and to comparethe results with data obtained from previous tests of similarly shaped flaps on an NACA 641-012 airfoil (NACA TNNo. 1277). The investi- gation included tests of two lO-percent-chord leading-edge flaps_ one intended to slide forward along the upper surface and the other hinged at the center of the airfoil leading-edge radius and deflect- ing from the lower surface. The flaps were tested on the plain airfoil and on the airfoil with a trailing-edge split flap deflected 60° .

Results i. The leading-edge flap produces the greater part of the in- creases in CLmax and in _ for CLmax by reducing the magnitude of the pressure peaks and the adverse pressure gradient usually asso- ciated with the flow conditions near maximum lift.

2. The increments in CLmaxand d° due to deflection of the lower- surface leading-edge flap on the plain a_rfoil were not so large as those obtained with the upper-surface leading-edge flap.

3. The addition of either leading-edge flap caused the pitching- momentcoefficients to increase negatively with increasing lift coefficient until the angle of attack was approximated high enough for the flap to becomeeffective.

4. The increments in pitching-moment coefficients which were obtained from the addition of either of the leading-edge flaps are relatively small in comparison with the increments resulting from deflection of the conventional split trailing-edge flap.

5. The upper-surface leading-edge flap was equally as good_with regard to the effect of surface roughness.

TN 1631 WIND-TUNNEL INVESTIGATION OFBOUNDARY-LAYER CONTROL BY SUCTION ONNACA 655-424 AIRFOIL WITHDOUBLE SLOTTED FLAP_Stanley F.

Racisz and John H. Quinn_ Jr._ June 1948 An investigation has been conducted at Reynolds numbers (RN) ranging from l. OxlO 6 to 6.0xlO 6 in the Langley 2-D low-turbulence tunnels to determine the effectiveness of boundary-layer control by suction and of suction-slot location in increasing the maximum lift and decreasing the drag of the NACA655-424 airfoil section equipped with a double slotted flap. Tests were madeof the model with a suction slot at 0.45c and a suction slot at 0.65c. Measurements were madeto determine the section lift_ drag_ and internal pressure- loss characteristics for flow coefficients ranging from 0 to 0.03 for the airfoil with the flap extended and retracted_ with and without leading-edge roughness.

The low maximum lift and high drag of thick airfoil sections are caused primarily by separation of the turbulent boundary layer.

Results i. The suction slot helped to maintain a linear variation of section lift coefficient with section angle of attack for a more extensive angle-of-attack range; thus_ the maximum section C L is increased.

2. The maximum section lift coefficient of the airfoil in the smooth condition at a RNof 6°0x106 was 1.4 with the flap retracted; deflecting the flap increased the lift coefficient to 3.4_ and boundary-layer control at 0.65c increased it to 4.2.

3. At the sameflow coefficient_ the increase in the maximum section lift coefficient was about twice as much for the flap- retracted configuration as that for the flap-deflected configura_ tion.

4. The maximum section lift coefficients obtained by the use of boundary-layer control at a RN= 6.0x106 with the flap deflected were generally higher for the configuration with the suction slot at 0.65c than that for 0.45c.

5. The maximum section L/D ratio with flap retracted and leading- edge roughness went from 30 to 74 at RN= 6.0x106 and that for the smooth model was increased from 116 to 160 by using a boundary-layer control slot at 0.65 chord.

TN 1674 ESTIMATION OF EFFECTIVENESS OFFLAP-TYPE CONTROLS ONSWEPTBACK WINGS_ John G. Lowry and Leslie E. Schneiter_ August 1948 An analysis was madeof the low-speed lift_ rolling_ and pitching characteristics of. flap-type controls on a series of swept back wings_ and methods are presented for estimating these character- istics. The methods developed are essentially modifications of the existing methods used in estimating the effectiveness of flap- type controls on unswept wings. A model was tested essentially unswept (6.3 °) and at sweepangles of 30°_ 40o_ and 51.3° . Mach Number= 0.12 and RNof about 1.55xi06 for 6.3° swept wing and 2.2xi0 6 for the 51.3° swept wing.

_C L rolling moment C L = (_u KIK _6c°s2A Method i. - _6 - effectiveness = CL6 parameter The subscript u indicates the value of CL/A_ for a wing of aspect ratio 6.00 and taper ratio 0.5. K1 is the ratio of C_/A_ for the aspect ratio of the "unswept" wing to the value of CL/A_ for aspect ratio of 6.00 and taper of 0.5. K2 is the taper ratio correction factor which is the ratio of the value of CL/A_ for taper ratio of the "unswept" wing to the value of CL/A_ for taper ratio of 0.5. _6 is the flap effectiveness parameter based on the "unswept" flap chord ratio and A is the sweepof the wing leading edge.

bC L CL _ _ (6) _6 K3 cos A The lift effectiveness parameter is _6 _6 u The aspect-ratio correction factor is K 3 and is the ratio of the slope of the lift curve CL_ of the "unswept" wing to the slope of the lift curve for the wing of aspect ratio 6, Method 2 was presented in reference 8.

The pitching moment effectiveness parameter CM6 may be calculated by multiplying the experimental lift load at each spanwise station (CL)(C/Cs) Cs 2 as computed by ACL = _ 57.3 C cos A _ where CL(C/C s) is the spanwise loading factor calculated from reference I, by the corresponding moment arm and C s = wing root chord. The lift and rolling can also be calculated.

These methods are limited to the range wherein lift has a linear variation with both wing angle of attack and flap deflection.

EXPERIMENTAL ANDCALCULATED CHARACTERISTICS OF SEVERAL HIGH- TN 1677 ASPECT-RATIO TAPERED WINGS INCORPORATING NACA 44-SERIES_230- SERIES_ ANDLOW-DRAG 64-SERIESAIRFOIL SECTIONS_ ThomasV. Bollech_ September 1948 The lift_ drag_ and pitching-moment characteristics of several unswept wings were determined by wind-tunnel tests and by calcula- tions using the method of NACATN 1269. The wings were similar in plan form with aspect ratio i0_ taper ratio 2.5_ and with root-chord and tip-chord thickness ratios of 20 and 12 percent_ respectively. The airfoil sections used were the NACA 44-seriesj 230-series_ and low-drag 64-series. The aerodynamic characteris- tics of the wings were determined experimentally for the smooth and rough model conditions with flaps neutral and partial-span and full-span split flaps deflected 60° . The tests were made through a range of Reynolds number from approximately 2.0xlO6 to approximately 5.0xlO 6 to determine the effects of aspect rati% taper ratio and chord thickness of the characteristics.

A split flap was used in all tests where the flaps were deflected.

Corrections were applied for support tare and interference.

Results I. Calculated and experimental results agreed.

2. CLmaxfor smoothwings with neutral flaps were approximately equal.

3. For deflected flaps the highest CLmax was obtained for the NACA-230-series.

4. The greatest loss in maximum lift due to roughness was experi- enced by the wing of the 230-serie% the smallest loss was with the 64-series.

5. The wing of NACA230-series sections with the flaps neutral exhibited an abrupt stall_ which may be unsatisfactory when stall warning or lateral stability at the stall is considered. The stall of the wings with NACA 64-series and 44-series sections was gradual.

6. The wing of NACA64-series sections in the smooth condition exhibited lower minimumdrag values and slightly better values of maximum lift-drag ratios than the wings of NACA230-series or 44-series sections.

7. In rough condition the maximum lift-drag ratios for all wings was approximately equal.

TN 1683 AN EXPERIMENTAL INVESTIGATION OFAN NACA631-012 AIRFOIL SECTION WITHLEADING-EDGE SUCTION SLOTS_ George B. McCullough and D. E.

Gault_ August 1948 An NACA 631-012 airfoil section equipped with a single suction slot near the leading edge was investigated to determine whether or not the maximum lift coefficient could be increased by delaying the separation of flow at the leading edge characteristic of the basic section.

The leading-edge type of separation of flow was successfully fore- stalled by meansof a single suction slot near the nose of the airfoil. The maximum lift of the airfoil was thereby increased until the turbulent boundary layer separated from the trailing edge. Although it was not demonstrated that the complete stall was the result of turbulent separation_ the abruptness of the stall was considerably alleviated from that of the basic airfoil section.

The largest increment of the maximum section lift coefficient realized was 0.46 with the flap undeflected and 0.51 with the plain flap deflected 40° . It is believed that somewhatgreater increments of lift could be obtained with a slot of more nearly optimumwidth and location.

The chordwise location and width of the slot are important. The results of this investigation indicate that the leading edge of the slot should be downstreamof the point of separation imme- diately prior to the stall of the basic section. The effective- ness of the slot increased with slot width up to a value of at least 0.8 percent chord.

TN 1696 CHORDWISE PRESSURE DISTRIBUTIONS ONA 12-FOOT-SPAN WING OF NACA 66- SERIES AIRFOIL SECTIONS UP TO A MACH NUMBER OF 0.6, Nancy E. Wall_ October 1948 This report presents graphical results for chordwise pressure distributions on a 12-foot span wing of the NACA 66-series sections for _ = -4° to stall and Mach numbersfrom 0.20 to 0.60. These results are generally contained in handbooks.

TN 1703 DOWNWASH ANDWAKE BEHIND UNTAPERED WINGS OF VARIOUS ASPECT RATIOS ANDANGLES OF SWEEP_ H. PageHoggard_ Jr_, and John R. Hagerman_ October 1948 An extensive survey of downwash behind swept wings was madeat 80 mph.

Sweepranged from 60° to -60° (60°_ 30°_ 0°_ -30°_ -60o). For each sweep angl% there were 2 aspect ratios tried. The report included 140 pages of data. Correction madefor jet-boundary_ but not for tares. Data for wakewas taken with wing i% then with wing removed_ which should be sufficient correction. Airfoil shape was close to NACA 0015.

Conclusions I. Wakecenter line location behind the sweptforward wings was high_ for sweptback wings it was found to be in or below the chord plane.

2. Both types have greatest energy loss at plane of symmetryand tips.

3. Low position for tail appeared most stable for all models except for short tail behind unswept wing at _ = 16o_ where high tail was better.

4. At short tail lengths and low angles of attack_ the rate of changes of downwash angle with angle of attack generally increased; at long tail lengths and high angles of attack the reverse seemedto be true.

TN 1741 EXPLORATORY WIND-TUNNEL INVESTIGATION OF THEEFFECTIVENESS OF AREASUCTION IN ELIMINATING LEADING-EDGE SEPARATION OVER ANNACA 641A212AIRFOIL_ Robert J. Nuber and JamesR. Needham_ Jr._ November1948 Area suction was used successfully to prevent leading edge separa- tion. It also helped prevent trailing edge separation from advancing.

The maximum effectiveness was obtained when 4.5% chord at upper leading edge was porous.

TN 1763 FLIGHTINVESTIGATION OF A COMBINED GEARED UNBALANCING-TAB AND SERVOTAB CONTROL SYSTEM AS USED WITHAN ALL-MOVABLE HORIZONTAL TAIL_ Robert G. Mungall_ December1948 A flight investigation was madeof a Curtiss XP-42 airplane equipped with an all-movable horizontal tail having a control system incorporating a combination of geared unbalancing tabs and servotabs. This system was used in order to provide in- creased stick force in rapid maneuverswhich was not obtainable with the plain servotab control system.

Whenthe stick is deflected initially_ the action of the damper in moving the whole horizontal tail and tabs in the samedirection gives an immediate stick force that is proportional to the stick deflection_ and this stick force is then gradually relieved by the ensuing servotab action.

I. Satisfactory longitudinal control was achieved in rapid as well as steady maneuvers.

2. The static friction in the viscous dampermust be held at a low value in order to obtain the desired operation of the control system.

THEEFFECTS OFVARIATIONS IN REYNOLDS NUMBER BETWEEN 3.0x106 AND TN 1773 25.0xi06 UPON THEAERODYNAMIC CHARACTERISTICS OF A NUMBER OF NACA 6-SERIESAIRFOIL SECTIONS_ Laurence K. Loftin_ Jr._ and William J. Bursnall_ December1948 An investigation was madeto determine the two_dimensional lift and drag characteristics of nine NACA6-series airfoil sections at Reynolds numbersof 15.0xi06_ 20.0xi06_ and 25.0xi06. Also presented are data from NACA Report 824 for the sameairfoils at Reynolds numbers of 3.0xi06_ 6.0xI06_ and 9.0xlO 6. The airfoils selected represent sections having variations in the airfoil thick- ness_ thickness form_ and camber. The characteristics of an air- foil with a split flap were determined in one instance as was the effect of surface roughness. Only lift and drag were measured.

Results i. The flow conditions for thicker airfoils are seen to be more favorable for delaying the forward movement of transition.

2. For a given lift coefficient outside the low-drag rang% the drag decreased as the RN varied from 3.0xlO 6 to 9.0xi06.

The results were all kind of general which related to a certain low or high drag group. These conclusions were the general con- clusions like a thicker boundary layer would give more form drag.

Many graphs were drawn_ but they were usually approximately the s ame.

WIND-TUNNEL INVESTIGATION OF AN NACA 65-210 SEMISPAN WING TN 1802 EQUIPPED WITH CIRCULAR PLUG AILERONS AND A FULL-SPAN SLOTTED FLAP_ Jack Fischel_ January 1949 Tests were made to find the lateral control characteristics on thin low-drag semispan wing_ with full spa% 25% chord slotted flap.

Ailerons at 68% chord_ covered 49.2% semispan_ in five equal seg- ments. Mach Numbers ranged from 0.13 to 0.61. Ailerons were of 3 types: (i) Thin-plate_ (2) Double-wailed with top plate_ (3) Double- walled without top plate.

Results For all 3 types_ effectiveness increased with Mach number with and without flap deflection. With flap retracted_ all 3 increased aileron effectiveness with angle of attack_ especially thin plate aileron. With flap deflected_ an increase in angle of attack had no effect on or decreased aileron effectiveness. Larger rolling momentcoefficients were produced with flap deflected. Double walled ailerons produced lower rolling momentsbut exhibited more linear relation with projection.

Yawing momentswere generally favorabl% becomingmore so with projection_ less so with increased angle of attack and flap deflec- tio% unaffected by Mach and Reynolds number.

Variation of hinge momentcoefficient with projection was non- linear_ it gave no consistent relation to Reynolds or Machnumber.

Double-walled aileron with top plate was closest to linear. In- creasing angle of attack madevariation less linear. Flap deflec- tion increased negatively the hinge momentcoefficients of all 3 types.

.60¢ J "Circular Plug Aileron TN 1872 HIGH-LIFT AND LATERAL CONTROL CHARACTERISTICS OF AN NACA 652-215 SEMISPAN WING EQUIPPED WITH PLUG AND RETRACTABLE AILERONS AND A FULL-SPAN SLOTTED FLAP_ Jack Fischel and Raymond D. Vogler_ April Wind-tunnel investigation at low Mach numbers on an NACA 652_215 section wing with 25% chord full span slotted flap_ and plug and retractable ailerons. Ailerons were at 70% chord_ covering outer 49% of semispan.

Results A flap deflection to 45 ° increased lift gradually from 1.34 to 2.30 at optimum positions. Roll effectiveness of ailerons increased with increased aileron projection and first increased_ then de- creased with increased angle of attack. Ailerons were effective past wing stall. Yawing moments of ailerons were favorable_ becoming More favorable with aileron projection and less favorable with angle of attack and flap deflection.

BOUNDARY-LAYER AND STALLING CHARACTERISTICS OF THE NACA 63-009 TN 1894 AIRFOIL SECTION_ Donald E. Gault_ June 1949 A wind tunnel investigation at a Reynolds number = 5.8xi06 was conducted. Pressure distributions_ tuft studies_ and boundary layer measurements were made at Mach Number = 0.167.

NACA 63-009_ like all other thin airfoils_ tended to stall abruptly at RN < 15x106 for this particular model with a 5' chord_ 7' span and approximating 2-dimensional.

Mechanism of stall was found to be as follows: a region near lead- ing edge separated while still laminar and forms a bubble of separated flow past which flow reattaches as turbulent. Stall came as separated boundary layer failed to reattach itself to airfoil surface.

EXPERIMENTAL AND THEORETICAL STUDIES OF AREA SUCTION FOR THE TN 1905 CONTROL OF THE LAMINAR BOUNDARY LAYER ON A POROUS BRONZE NACA 64A010 AIRFOIL_ Dale L. Burrows_ Albert L. Braslow_ and Neal Tetervi% July 1949 A low-turbulence wind-tunnel investigation was made of an NACA 64A010 airfoil having a porous surface of sintered,bronze to determine the reduction in section drag coefficient that might be obtained at large Reynolds numbers by the use of suction to pro- vide continuous inflow through the surface of the model (area suction). In addition to the experimental investigatio% a re- lated theoretical analysis was made to provide a basis of compari- son for tests results. The stability of the laminar boundary layer was calculated for two important cases of chordwise suction distribution for the test airfoil. The model was made such that chordwise inflow could be altered. Reynolds numbers ranged from as low as 3.0x106 to as high as 16.7xi06.

Results I. The area suction made it possible to keep laminar flow for the full-chord to RN's up to 7.8xi06 even though the surface was neither smoothed or faired.

2. At a Reynolds number of 6.0xi06_ the ,total-drag coefficient was .0028 while it was .0052 without suction.

3. The boundary-layer velocity profiles and thicknesses were calculated by the Schlichtin_ method and _Lin's approximate formula was used to calculate the R6cri t at which any Schlichting velocity profile is neutrally stable. Good agreement was found between experiment and theory at RN= 3.0x106 but not at higher Reynolds numbers_when both were based on full chord laminar flow.

4. Area suction appeared to decrease the angular spread of turbulence emanating from an individual surface disturbance.

5. Although area suction was able to overcome the destabilizing effects of an adverse pressure gradient such as occurs over the rear portion of an airfoil_ area suction does not appear to stabilize the boundary layer completely for relatively large dis- turbances such as those which might be caused by protuberances that have a height comparable to the boundary layer thickness.

TN 1923 BOUNDARY-LAYER ANDSTALLING CHARACTERISTICS OF THENACA64A006 AIRFOIL SECTION_ George B. McCullough and Donald E. Gault_ August The boundary-layer and stalling characteristics of an NACA64A006 airfoil section were investigated experimentally at a RN of 5.8xi06. Measurementsincluded lift_ drag_ pitching moment_ chordwise distribution of pressure_ visual studies of the boundary- layer flow_ and surveys of the static-pressure and velocity distri- bution within the boundary layer.

The model had a chord of 5 ft_ a span of 7 ft and extended from the top of the tunnel to the bottom.

Results I. At 3° angle of attack (C L = 0.35)_ the pressure distribution and liquid-film studies indicated the presence of a small bubble of separated flow on the upper surface near 0.5-percent chord.

2. At 5° _ and C L = 0.56 the boundary layer flow detached from the upper surface near the leading edge and reattached at about 8-percent chord_ leaving dead air beneath. The drag increased.

3. At _ = 9° (C L = 0.89) the flow was separated over the entire upper surface of the model.

4. The cause of the discontinuity in lift at 5° angle of attack was a partial collapse of the peak pressures near the leading edge accompaniedby the formation of a region of approximately constant pressure.

5. With increasing _ the region of approximately constant pres- sure expanded rearwardly_ thereby producing an increasingly negative pitching moment.

6. Beyondmaximum lift there was no abrupt redistribution of pressur% therefore no sudden loss of lift.

AERODYNAMIC CHARACTERISTICS OF 15 NACA AIRFOIL SECTIONS AT SEVEN TN 1945 REYNOLDS NUMBERS FROM 0.7x106 TO9xi06_ Laurence K. Loftin_ Jr._ and Hamilton A. Smith_ October 1949 The report compiles data from NACA Report 824 and TN's 1368 and 1591 on section lift_ drag_ lift curve slop% and angle of zero lift for 15 airfoils at RN= 0.7 to 9.0xI06_ with and without standard roughness. It includes a discussion of possible flow patterns.

Airfoils 64 - 409 632-415 0012 641 - 412 652-415 4412 642- 412 662-415 4415 643 - 418 23012 641- 012 23015 641 A212 641- 612 Conclusions I. C D at CL(design) in both smooth and rough condition increased as Reynolds number (RN) was decreased: from 9x106to 0.7x106. Magni- tude of increase increased with airfoil thickness_ and with rearward movement of point of minimum pressure. At low RN_ the drag advan- tage of 6-series over 5-series disappeared.

2. A reduction of RN led to an increase of the low drag bucket of the 6-series airfoils. For all airfoils_ the actual low drag bucket was larger than the theoretical bucket.

3. Reduction of RN decreased CLmax of all airfoils_ with or with- out split flaps_ and with or without surface roughness. The magni- tude and character of the reduction with section and surface was inconsistent.

4. In general_ the reduction of RN made stall less abrupt for the 6-series. A variation of RN did not improve stalling characteris- tics of the 230-series.

5. Slight decreases in lift curve slope accompanied decrease in Reynolds number. The angle of zero lift was generally independent of Reynolds number.

6. The value of CMc/4 at design angle of attack did not vary for I plain airfoils. The position of aerodynamic center varied slightly with RN.

TN 1946 MEASUREMENTS IN THE BOUNDARY LAYER OF A YAWED WING_ A. M. Kuethe, P. B. McKe% and W. H. Curry_ September 1949 Measurements of the velocity profiles in the turbulent boundary layer on the upper surface of a wing of semi-elliptical plan form at an angle of yaw of 25° and angles of attack of 12° and 14° are reported along with pressure distributions. The airspeed was 50 mph.

RN = 700_000 based on root chord of 18".

The wing model used for the investigation was of semi-elliptical plan form and Clark Y section.

Results I. The wing was sprayed with camphor and ether to see where transition occurred and it was found that it occurred in the first 10% of the chord.

2. The chordwise flow in the turbulent boundary layer of a finite wing at an angle of yaw of 25 ° may be expressed: u is the chordwise velocity u _ f(_x__ _y) H = 6/e where e* = displacement thickness u 1 XX @ = momentum thickness 0xx = _o (I - u_ ) u_lldy 3. The separation point for the chordwise profile does not neces- sarily mark the beginning of the turbulent wake for a yawed cylinder. The criterion for the beginning of the turbulent wake is probably (_V) = 0 where IV1 is the absolute velocity.

oby y= 4. The boundary layer for the chordwise flow is considerably thicker than that for the spanwise flow.

TN 1961 INVESTIGATIONS RELATING TO THE EXTENSION OF LAMINAR FLOW BY MEANS OF BOUNDARY-LAYER SUCTION THROUGH SLOTSj Laurence K. Loftin_ Jr._ and Dale L. Burrows_ October 1949 Experimental investigations were made of boundary-layer suction through slots as a means of increasing the extent of laminar flow.

It was found that when using boundary-layer suction through properly designed slots_ substantial increases in the extent of laminar flow can be realized with a small expenditure of power at free- stream Reynolds numbers as high as about 7.0x106. On an airfoil having an extensive region of unfavorable pressure gradient_ the extent of laminar flow was increased by 52% of the chord at RN = 7xlO 6 with an expenditure of suction power the drag- coefficient of which for one surface was only 3.7xi0 -4. Difficul- ties arose apparently as a result of disturbances introduced into the boundary layer by surface imperfections_ free-stream turbulenc% or by the effects of the slots themselves. The boundary-layer control was not found to decrease noticeably the sensitivity of the laminar layer to surface roughness. It was also found that the power required dependedon slot geometry.

Because this report is not current_ it is felt that current knowledge is muchmore valuable.

Flow r Probably Most Favorable Slot Design AERODYNAMIC CHARACTERISTICS OF THE NACA 8-H-12 AIRFOIL SECTION AT TN 1998 SIX REYNOLDS NUMBERS FROM l. Sx106 TO ll.0xlO 6 Raymond F. Schaefer and Hamilton A. Smith_ December 1949 Tests were made to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers from 3.0 xl06 to ll. Oxl06. The section lift_ drag_ and pitching-moment characteristics were presented for both the smooth and rough surface condition at these four Reynolds numbers_ together with previously published results for the same section at Reynolds numbers of 1.8xlO 6 and 2.6xi06. Some of the more important aerodynamic characteristics of the NACA 8-H-12 airfoil are compared with those of two sections commonly used in rotor-blade design_ the NACA 0012 and NACA 23012. The maximum Mach number attained is 0.13. The density of air ranged from 2 to i0 atmospheres.

Results i. No unusual scale effects on lift_ drag_ or pitching moment were presented for the smooth NACA 8-H-12 airfoil over the range of RN from 1.8 to ll. Oxl06. This was true for the airfoil with roughened leading edge also except for an apparent adverse scale effect on drag between RN's of (2.6 and 3.0) x 106.

2. The values of the pitch-moment coefficient about the aero- dynamic center were somewhat positive and increased in magnitude with increasing RN. Roughness on the edge caused the moment to decrease.

3. The position of the aerodynamic center had a pronounced for- ward movementbetween RNof 1.8x106 and 2.6-3.0xi06.

TN 2041 AN EXPERIMENTAL INVESTIGATION OFTHENACA 631-012 AIRFOIL SECTION WITHLEADING-EDGE ANDMIDCHORD SUCTION SLOTS_ George B. McCullough and Donald E. Gault_ February 1950 Tests were run on an NACA631-012 two-dimensional airfoil employing boundary layer control. Originally only a leading edge slot was used_ but now a midchord slot has been added. Tests were con- ducted at Reynolds numbers of 4.1 and 5.8 million with the wing chord of 5 feet.

The maximum section lift coefficient (CLmax)of the basic airfoil section was 1.38. Using a plain flap deflected 40o_ a CLmaxof 2.03 was obtained. Using suction only in the nose slot_ these two values were increased to 1.84 and 2.54. Nowusing both slots_ a CLmax of 2.39 for no flaps and a CLmaxof 2.89 were obtained.

Becauseof the greater values of lift obtained by using both slots_ it seems that the nose slot of the model without a midchord slot was capable of preventing leading-edge separation for conditions of minimumpressure and pressure gradient more severe than those encountered without a midchord slot.

I

F_._N-_Isxlo__ RN = '_.8x1066 j/Both_ Slots 0 ._ '.6 2!4 CL TN 2061 THE EFFECT OF RATE OF CHANGE OF ANGLE OF ATTACK ON THE MAXIMUM LIFT OF A SMALL MODEL_ Paul W. Harper and Roy E. Flanigan_ March A wind-tunnel investigation was conducted of a 1/20-scale partial model of a conventional fighter airplane to determine the effects of rate of change of angle of attack on its maximum lift. The tests covered Mach numbers from 0.I to 0.8. The results showed that the maximum lift coefficient increased linearly with pitching velocity up to a limiting value of the lift coefficient which depended on the Mach number. The magnitude of the pitching velocity effect on the maximum lift coefficient decreased with increasing Mach number so that it became negligible for a Mach number of about O.6.

The model was made to rotate in a manner to simulate the motion of an airplane during pull-ups of varying abruptness. The pitch- ing velocity range was from 0 to 20 radians per second.

Owing to limitations of the available torque of the pitching mechanism the maximum angle of attack attained during the pull- ups diminished with increasing Mach number from a maximum value of 30 ° at Mach numbers below about 0.3 to a value of about 15 ° at a Mach number of 0.8.

TN 2074 AERODYNAMIC CHARACTERISTICS AT REYNOLDS NUMBERS OF 3.0x106 AND 6.0x10 6 OF THREE AIRFOIL SECTIONS FORMED BY CUTTING OFF VARIOUS AMOUNTS FROM THE REAR PORTION OF THE NACA 0012 AIRFOIL SECTION_ Hamilton A. Smith and Raymond F. Schaefer_ April 1950 An investigation was made of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing 1.5_ 4.0_ and 12.5% of the original chord from the trailing edge of an NACA 0012 airfoil section. The tests consisted of measurements of section lift_ drag_ and pitching-moment coefficients (CL_ CD_ CM) at Reynolds numbers (Re) of 3.0x106 and 6.0x106 for the airfoils both in the smooth condition and with roughened leading edges.

As the trailing edge thickness was increased by cutting off portions near the trailing edg% the maximum C L varied by a rela- tively small amount for the smooth airfoil condition and pro- gressively increased for the rough leading-edge conditions.

The CD_ over a large range of CL'S_ increased progressively as the trailing-edge thickness was increased by cutting off more of the chord. The magnitude of this increase varied erratically with C L for the smooth airfoil having a trailing edge thickness of 1.4% chord and particularly for both the smooth and rough conditions of the airfoil having a trailing-edge thickness of 4.0%.

The value of the quarter-chord CM at zero angle of attack remained virtually zero as the trailing-edge thickness increased_ and the position of the aerodynamic center consistently moved rearward.

The application of rivet heads near the trailing edge of the airfoil formed by cutting off 1.5% of the original chord caused relatively minor changes in lift_ drag_ and pitching-moment characteristics.

Re = 6 x 106 _ 16- Re= 3x|O 6 .30- CLma x o.8.

CD .20- .10- , 4 0 2 4 2 4 Trailing Edge Trailing Erc_je .

Thickness 19/o chord) Thickness I,_ chord_ TN 2080 WIND-TUNNEL INVESTIGATION AT LOW SPEED OF AN UNSWEPT UNTAPERED SEMISPAN WING OF ASPECT RATIO 3.13 EQUIPPED WITH VARIOUS 25- PERCENT-CHORD PLAIN FLAPS_ Harold S. Johnson and John R. Hagerman_ April 1950 Force and moment data were obtained at low speeds to determine the aerodynamic characteristics of an unswept untapered semispan wing of NACA 64A010 section and aspect ratio 3.13 equipped with 25% unsealed plain flaps having various spans and spanwise loca- tions. The flaps were deflected up to 60 ° with the wing section angle of attack from -4 ° to stall and a Reynolds number of 4.5xi06.

Changes in angle of attack_ flap deflectio% or flap span and spanwise location generally produced trends in lift_ drag_ and pitching moment_ and flap hinge moment that were similar to but of different magnitude from those for unswept wings of higher aspect ratio.

The increment of the lift coefficient due to 30 ° of flap deflec- tion increased almost linearly with increasing flap span and was relatively unaffected by the spanwise location of the flaps.

Because of the increase in the drag coefficients and the associated decrease in the values of the lift-drag ratio with increasing flap deflectio% an advantage may be gained by limiting the flap deflec- tion to moderate angles (about 30o)_ even though increases in lift coefficient result from further increases in flap deflection.

.8 .4" AC L ._' Half-span Flap ! I I I, 4 L ' 6O 10 20 30 40 50 Flap Deflection (deg.)

TN 2112 FURTHER EXPERIMENTAL STUDIES OF AREA SUCTION FOR THE CONTROL OF THE LAMINAR BOUNDARY LAYER ON A POROUS BRONZE NACA 64A010 AIRFOIL_ Albert L. Braslow and Fioravante Visconti (Superseded by Report I025)_ May 1950 A low-turbulence wind-tunnel investigation was made of an NACA 64A010 airfoil having a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of area suction. Initial results of this investigation have been reported previously. The present paper presents the results of additional tests of the same airfoil model equipped with a porous skin of lower porosity.

The tests consisted of wake-drag_ suction-flow_ and suction air pressure-loss measurements. The tests were made with the model at zero angle of attack at Reynolds numbers of 5.9xi06_ 12.0xi06_ 15.0xi06_ and 19.8xi0 v. The Mach n_mber for all tests was less than 0.2.

Results i. Full-chord laminar flow was maintained by the application of area suction up to a RN of 19.8xi0 V.

2. At RN of 19.8xI06_ the total-drag coefficient (wake drag + drag equivalent of the suction power required) was equal to 0.0017 as compared with an estimated value of 0.0045 for a smooth and fair NACA 64A010 airfoil without boundary layer control at a RN = 20xlO 6.

3. It seems likely from the results that attainment of full-chord laminar flow by means of continuous suction through a porous surface will not be precluded by a further increase in Reynolds numbers provided that the airfoil surfaces are maintained suffi- ciently smooth and fair_ and provided that outflow of air through the surface is prevented.

TN 2143 ANALYSIS OFTHEEFFECTS OF BOUNDARY-LAYER CONTROL ONTHEPOWER- OFFLANDING PERFORMANCE CHARACTERISTICS OFA LIAISONTYPEOF AIR- PLANE_ Elmer A. Horton_ Laurence K. Loftin_ Jr._ and Stanley F.

Racisz_ August 1950 A performance analysis has been madeto determine whether boundary layer control by suction might be effective in making the power- off landing distance of a liaison type of airplane less than that obtainable with conventional high lift devices.

The combined ground and breaking friction coefficient was 0.4.

The payload was fixed at 1500 pounds.

Wing span varied from 25 to i00 ft_ aspect ratio was varied from 5 to 15_ engine horsepower was baried from 300 to 1200.

Maximum C L of 5.0 and 2.8 were assumedfor the airplanes with and without boundary-layer control.

Gross weight equations as well as power required equations were written for the plane.

Landing equations were developed for each of the 4 phases: the steady glide_ a transition path executed at maximum lift coeffi- cient to bring the airplane from a steady glide to level flight_ a floating period of 2 seconds to allow for lag in control response and for the application of brakes_ and finally the ground run.

Results I. For a specified airplane maximum speed_ the total landing distance can be reduced from 25 to 40 percent by using boundary layer control.

2. The ground distance for a maximum speed can be reduced 30 to 40 percent.

3. Boundary-layer control is much more effective in reducing landing distance than take-off distance.

4. The gliding and stalling speeds were 20 to 25 percent lower with boundary layer control.

5. For a fixed wing span_ the sinking speed_ or vertical velocity_ was slightly higher for the airplane with boundary-layer control than for the conventional airplane.

TN 2149 INVESTIGATION OF BOUNDARY-LAYER CONTROL TO IMPROVE £HELIFT AND DRAG CHARACTERISTICS OF THENACA 652-415 AIRFOIL SECTION WITH DOUBLE SLOTTED ANDPLAINFLAPS_ Elmer A. Horton_ Stanley F.

Racisz_ and Nicholas J. Paradiso_ August 1950 A two-dimensional wind-tunnel investigation has been madeof the relative effectiveness of two methods of boundary layer control in increasing the maximum lift coefficient of an NACA652-415 air- foil section. Boundary-layer suction was applied at the 45%chord station of the airfoil equipped with a double slotted flap and in the vicinity of the hinge line of the airfoil with the deflected plain flap. For the sameexpenditure of suction power or flow co- efficient_ the configuration with a double slotted flap and a 0.45-chord suction slot had higher maximumlift coefficients (CLmax)than did the configuration with suction slots on a de- flected plain flap.

The data indicated that the CLmax of NACA6-series airfoils equipped with a single suction slot and a double slotted flap increased as the airfoil thickness ratio increased from 12 to 24% and that the increment in CLmaxassociated with a given flow re- moval increased with increasing thickness ratio. CLmaxbetween 3.0 and 4.0 were obtained with NACA6-series airfoils in the smooth condition depending on the thickness and quantity of flow removed.

The corresponding range of maximum CL obtainable with NACA6- series airfoils in the rough-surface condition extended from 2.7 to 3.6. The application of boundary layer control in the vicinity of the hinge line of the 652-415 airfoil section with a 0.30- chord plain flap increased the section lift-drag ratio for C L above 0.6 for the rough section and above 0.8 for the smooth condition.

The maximum section lift-drag ratio occurred at a C L of 1.05 and was increased 10.5%for the smooth condition and 42.5% for the rough condition by the use of boundary layer control.

The extent to which the maximum lift-drag ratio of airplanes having unswept wings composedentirely of NACA 652-415 airfoil sections can be substantially increased by boundary layer control was found to dependupon the structural feasibility of building wings having values of the span-to-root thickness ratio in the range of 40 to I00. For an airplane having a wing composedentire- ly of NACA 652-415 airfoil sections and a span to root thickness of 35 to i_ the effect of boundary layer control on the airplane maxi- mumlift-drag ratio will be negligible for the smooth condition_ and although the airplane maximum lift-drag ratio would be in- creased somewhatfor the rough condition it is unlikely that the maximum section lift-drag ratio could be utilized.

Tests were conducted at Reynolds numbers of 1.0xlO6 to 6.0xlO 6.

LOW-SPEED CHARACTERISTICS OFFOUR CAMBERED_ 10-PERCENT-THICK NACA AIRFOIL SECTIONS, GeorgeB. McCullough and William M. Hair% August 1950 A two-dimensional low-speed investigation was madeof four thin_ camberedairfoil sections. The airfoil sections were the NACA 64A310_a = 1.0; the 64A810, a = 0.8 (modified); and the NACA 0010 camberedto the same two meanlines. The data, obtained for Reynolds numbersof 3.7xi06 and 5.2xI06_ include measurementsof lift s drag_ pitching moment_and chordwise distribution of pres- sure. The effect of surface roughness was investigated as well as the effect of a split flap deflected 60° .

The maximum section lift coefficients (CLmax)of the four-digit sections were greater than those of the 64A-series sections for all test conditions. The superiority of the four-digit sections diminished with increased amountof camber.

The stall of the sections was little affected by the change of thickness distribution_ but was significantly affected by camber.

Visual observation of tufts attached to the upper surfaces of the models indicated that the stall of the sections camberedfor an ideal C L of 0.3 was the result of separation of flow from the leading edge almost immediately after the appearance of turbulent separation at the trailing edge_ whereas_ for the sections camberedfor an ideal lift coefficient of 0.8_ turbulent separa- tion from the trailing edge progressed as far forward as the 70%-chordstation before laminar separation appeared near the leading edge.

The effect of Reynolds number on maximum lift was small for the range investigated.

Surface roughness decreased the maximum lift of all the unflapped airfoil sections. This reduction was greater for the sections camberedfor a design C L of 0.3 than for those camberedfor a design C L of 0.8. Roughnessreduced the maximum lift of the flapped four-digit-series sections_ but showedno consistent effect on the flapped 64A-series sections.

The increment of maximum lift produced by a simulated split flap deflected 60° was greater for the four-digit series airfoils than for the 64A series. For either series_ the increment of maximum lift produced by the flap was greater for the greater amount of camber.

TN 2228 EFFECTS OFMODIFICATIONS TO THELEADING-EDGE REGION ONTHESTALLING CHARACTERISTICS OF THENACA 631-012 AIRFOIL SECTION_ John A. Kelly_ November1950 A wind-tunnel investigation of a series of modifications to the leading-edge region of the NACA 631-012 airfoil section was con- ducted to determine the possibilities of delaying the flow separa- tion that occurs near the leading edge of the basic section and of improving the stalling characteristics.

Modifications with greater-than-normal leading-edge radii combined with certain types of camberhad a favorable effect on the maximum lift_ but showedonly slight improvements in the stalling charac- teristics. Modifications with greater-than-normal leading-edge radii and no camberand modifications incorporating a super-posi- tion of increased thickness showedlittle or no improvement over either the maximum lift or stalling characteristics of the basic airfoil section.

For the basic airfoil section with the leading-edge flaps_ the maximum lift coefficient increased fairly rapidly with flap de- flections up to a deflection of i0°_ remained nearly constant for the range of deflections from i0 ° to 30°_ and decreased for deflections greater than 30° . The stalling characteristics throughout the range of leading-edge-flap deflections remained essentially those of the basic airfoil section.

TN 2235 THE BOUNDARY-LAYER AND STALLING CHARACTERISTICS OF THE NACA 64A010 AIRFOIL SECTION_ Robert F. Peterson_ November 1950 A wind-tunnel investigation of the NACA 64A010 airfoil section was conducted to determine the boundary-layer and stalling char- acteristics at low speed. The tests were made at a Reynolds number of 4.1 million and included force measurements_ pressure- distribution measurements_ flow studies_ and boundary-layer measurements.

A small region of separated flow was evident on the upper surface of the airfoil at approximately 1.2% chord at an angle of attack of 5 ° . For an angle of attack of 9°_ the separated region had moved forward to 0.4% chord and had become narrower. At an angle of attack of 9.5 ° the flow failed to reattach to the surfac% causing the airfoil to stall suddenly with no warning. This type of stall gives a sharp peak to the lift curve with little change of slope of the curve prior to the stall.

The pressure coefficient at the leading edge increased uniformly with increasing angle of attack_ and the sudden and complete collapse of the pressure peak at the stall was similar to that observed on the 9- and 12_percent-thick sections of the NACA 63- series airfoils.

EFFECTS OF MACH NUMBER UP TO 0.34 AND REYNOLDS NUMBER UP TO 8x106 TN 2251 ON THE MAXIMUM LIFT COEFFICIENT OF A WING OF NACA 66-SERIES AIR- FOIL SECTIONS_ G. Chester Furlong and James E. Fitzpatrickj December 1950 The ranges of Mach numberobtained at two different tunnel pressures were 0.I to 0.34 and 0.07 to 0.26_ the corresponding Reynolds number (RN) ranges were from 1.36xi06 to 4.66xi06 and from 2.20xi06 to 8.00xI06_ respectively.

The wing was tested with full-span and partial span split flaps deflected 60° and also without flaps. Chordwise-pressure- distributions were madefor all flap configurations of the model.

The tunnel pressures were 14.7 and 33 psi absolute.

Leading edge roughness tests were madewith the plain wing and with partial-span flaps deflected.

The lift coefficients were corrected for tare and interference and the angles of attack have been corrected for air-stream mis- alinement and jet-boundary effects. No correction was applied to the local value of static pressure.

Results i. For a given value of Mach number the values of CLmax were increased when the RN was increased.

2. For a given RN an increase in Mach number in the sub-critical speed range caused small reductions in CLmax _ whereas an increase in Mach number that caused the critical speed to be exceeded re- suited in large reductions of CLmax.

3. Although an increase in Mach number and RN may produce several types of variations of CLmax with RN_ the peak values of CLmax on the wing tested appeared to occur with the attainment of sonic speed locally on the wing.

4. Roughness on the leading edge materially reduced the effect of RN on CLmax , but Mach number effects in the subcritical speed range were of the same order as those obtained with the smooth _ wing.

TN 2338 EXPERIMENTAL INVESTIGATION OF LOCALIZED REGIONS OF LAMINAR- BOUNDARY-LAYER SEPARATION_ William J. Bursnall and Laurence K.

Loftin_ Jr._ April 1951 An experimental investigation was made of a localized region of laminar separation behind the position of minimum pressure on an NACA 663-018 section _ = 0 o and Reynolds numbers = 1.2xi06_ 1.7xI06_ 2.4xi06. This region can be characterized by a length of laminar boundary layer following separation after which transi- tion occurs and the resultant separated turbulent boundary layer spreads and reattaches to the surface. The length of laminar bound- ary layer between separation and transitio% expressed as the ratio of the length of layer to the boundary layer thickness at separa- tion 3 was found to be a function of the value of the boundary layer Reynolds numberat separation. The functional relationship is not the samefor localized regions of separation behind the position of minimumpressure at the ideal _ and for similar regions in the vicinity of the leading edge at high _ this result suggests that the correlation b_tween the length of laminar layer following separation and the boundary layer Reynolds number is related to the history of the flow preceding separation and to the nature of the pressure gradients.

After transition occurred in the separated layer_ turbulence was found to spread at a relatively constant angle as is the case in a spreading turbulent jet. The boundary layer shape parameter was found to vary from 2.6 just before flow reattachment to 1.3 within a relatively short distance after reattachment. The nature of the flow in the turbulent boundary layer immediately after reattachment was such that the usual methods of predicting the rate of growth and change in shape of the turbulent boundary layer did not give satisfactory results.

TN 2353 CHARTS ANDTABLES FORUSEIN CALCULATIONS OF DOWNWASH OF WINGS OF ARBITRARY PLANFORM_ Franklin W. Diederich_ May 1951 Charts are given for the values of downwash of a horseshoe vortex in incompressible flow. These charts are basically inapplicable to swept wings and to wings of more complicated plan form because the assumedspanwise lift distributions are those of unswept wings and differ from swept wings. The method consists basically of distributing these vortices along the wing span in such a way that they approximate the lifting action of the wing and of super- imposing the downwash fields of the individual vortices. The method is probably inapplicable (without modification) in many cases of present interest where such characteristics as high angle of attackj low aspect ratio_ large angle of sweep_high taper_ or relatively large fuselage result in uncertain spanwise lift distributions_ partly separated flow_ and rolled-up vortices extending rearward off the upper surface of the wing. The cal- culating procedures are based on the assumption that the lifting action on the wing may be represented by a single concentrated vortex at the quarter-chord line.

TN 2404 AN ANALYTICAL INVESTIGATION OF EFFECT OF HIGH-LIFTFLAPSONTAKE- OFFOF LIGHTAIRPLANE_ Fred E. Weick_ L. E. Flanagan_ Jr._ and H. H. Cherry_ September 1951 Three phases of the problem of improving take-off performance by the use of flaps were considered. The optimum lift coefficient for take-off was determined for airplanes having loadings representative of light aircraft and flying from field surfaces encountered in personal-aircraft operation. Power loading_ span loading_ aspect ratio_ and drag coefficient were varied sufficiently to determine the effect of these variables on take-off performanc% and_ for each given set of conditions_ the lift coefficient and velocity were determined for the minimumdistance to take off and climb to 50 feet. Existing high-lift control-device data were studied and comparedto determine which combinations of such de- vices appeared to offer the most suitable arrangements for light aircraft. Computations were madeto verify that suitable stability_ control_ and performance can be obtained with the optimum devices selected when they are applied to a specific airplane.

Assumptions The airplane was assumed to carry four people and baggage and enough fuel and oil for 5 hours cruising flight at 65 percent of full power. The wings were cantilever and rectangular in plan form. The frontal area "F" was determined from the following I expression of F = 0.15Wu 2/3 where w u was taken as 1500 pounds.

The empennage area assumed to be 25% of wing area. The propeller was fully automatic and permits development of full power and speed at all airspeeds. The total drag coefficient based on wing area is determined by the expression: C D = 0.0025 + (19.63)(20 + 0.05) + __CL + CD S 0.9_A o A three phase take-off was assumed: an accelerated ground run in the attitude of least resistance until takeoff speed is reached.

A circular transition arc from the end of the ground run to the beginning of the steady climb_ and steady climb to 50 feet.

The optimum high-lift arrangement for the present purpose was: Maximum lift coefficient of approximately 3.0_ low drag at high lift_ low minimum drag coefficient_ simplicity of structur% and feasibility of satisfactory lateral control.

Conclusions i. The shortest distances to take off and climb to a height of 50 feet are obtained only when both the span loading and the power loading are low.

2. Both the ground friction and the air drag are of critical importance with heavy span and power loadings_ but they are rela- tively unimportant at the lightest loadings considered.

3. For each combination of span and power loadings_ there is an optimum take-off speed which varies only slightly with changes in drag or aspect ratio.

4. The shortest distance to take off and climb to a height of 50 feet are obtained with aspect ratios of less than 3 and a maximum lift coefficient of approximately 1.4_ although distances only slightly better can be obtained with aspect ratios of 6 to 8 if proportionately higher lift coefficients are available so that the sametake-off speed is used.

5. The optimumvalue of maximum lift coefficient for the take-off over a 50-foot obstacle with airplanes having aspect ratios of 6 to 8 is in the neighborhood of 3.0.

6. Although flapped wings with maximum values of section lift coefficient of 3.0 are availabl% the best of those which are simple enough to be suitable for personal airplanes have values of approximately 2.5.

7. The experimental data available are not adequate to determine the optimumairfoil camber_ thickness_ or thickness distribution to obtain high lift with low drag.

8. For the purpose of the present study_ one of the most likely high-lift arrangements for use on personal airplanes is the single slotted flap covering the entire span of the wing. Lateral con- trol can be obtained simply by deflecting the right and left wing flaps differentially as ailerons_ with the rudder tied in elastically to overcome the adverse yawing moment.

9. The high-lift and lateral-control arrangement selected_ when applied to a typical four-place personal airplane_ could improve the take-off distance required to clear a 50-foot obstacle by 25 percent_ apparently with no detrimental effect on the speed and climb performances or on the weight or simplicity of construction.

TN 2405 INVESTIGATION OF NACA 64_2-432 AND 64_3-440 AIRFOIL SECTIONS WITH BOUNDARY-LAYER CONTROL AND AN ANALYTICAL STUDY OF THEIR POSSIBLE APPLICATIONS, Elmer A. Horton_ Stanley F. Racisz_ and Nicholas J.

Paradis% July 1951 Tests were made on NACA 64_2-432 and 64_3-440 airfoil sections to determine the effects of boundary layer control (BLC) by suction on the aerodynamic characteristics. The lift-drag ratios were somewhat low because of the use of standard roughness on the lead- ing-edge.

Large reductions in the wake-drag coefficient were obtained through a wide CL range on the 32 and 40% thick sections with relatively moderate flow coefficients and pressure loss coefficients for the pump. The minimum total CD'S were 0.017 and 0.028 for 32- and 40% thick_ respectively. Wing characteristics calculated from section data indicate that_ for wings of ratio span to root thickness of 35 and a taper ratio of 0.2_ the use of BLCincreases the maximum L/D by 13%_i.e. from 26.6 at a CL of 0.5 to 30.1 at a C L of 0.9_ and increases the aspect ratio for maximum L/D from 12 to 60.

With a parasite C D of 0.015 added to account for the drag of the fuselage tail_ etc._ the use of BLCincreases the maximum L/D ratio by 20%_i.e._ from 16.9 at a C L of 0.82 to 20.25 at a CL of 1.08_ and increases the aspect ratio for maximum L/D ratio from 12.4 to 21. These gains are based on calculations obtained by using section data corresponding to the rough surface condition and do not dependon the attainment of extensive laminar layers.

Maximum lift coefficients of 2.57 and 3.49 were obtained for the 32% and 40%thick Sections without flaps for flow coefficients of 0.038 and 0.032. The critical Mach numbers of the 32%and 40%thick sec- tions as determined from the theoretical pressure distributions at a C L of 0.4 were 0.527 and 0.462_ respectively. These sections would have application to relatively low-speed_ long range aircraft.

TN 2440 WIND-TUNNEL INVESTIGATION ANDANALYSIS OF THEEFFECTS OF END PLATES ONTHEAERODYNAMIC CHARACTERISTICS OFAN UNSWEPT WING_ Donald R. Riley_ August 1951 A wind-tunnel investigation was made to determine the effects of end plates of various areas and shapes on the aerodynamic charac- teristics of an unswept and untapered wing of aspect ratio 4.

Various shapes of plates were tested. A stainless-steel wing was tested along with 15 different plates. The wing had a span of 32 inches_ an aspect ratio of 4 and was a NACA641A412airfoil section.

Conclusions i. The addition of end plates to an unswept wing may provide relatively large increases in the lift-drag ratio at the higher lift coefficients for a limited range of end-plates areas_ but end plates cannot be expected to produce substantial increases in the maximum lift-drag ratio. The most favorable effect of end plates on the maximum lift-drag ratio is obtained when the wing aspect ratio is low and the ratio of the wing profile drag coeffi_ cient to end-plate profile drag coefficient is high. For such cases_ however_ the absolute value of the maximum lift-drag ratio will_ of necessity_ be low.

2. Substantial increases may be obtained in the maximum lift- drag ratio of wing-body combinations or complete airplanes_ for which the total drag of the componentsother than the wing is large relative to the wing drag_ by the use of appropriately designed end plates. Except possibly for the smaller end-plate areas_ however_ the increases obtained are not likely to be as large as those which would be obtained by utilizing the end plate area as a simple addition to the wing span_ thus increasing the wing geometric aspect ratio.

3. The lift coefficient at which the lift-drag ratio becamea maximum increased with an increase in end-plate area. Adding end plates to the wing also tended to increase the lift-coefficient range at which the lift-drag ratio remained at or near the maxi- mum value.

4. The maximum lift coefficient of the wing experienced an in- crease when the end plates were added. The rate of increas% how- ever_ decreased with increasing end-plate area.

5. The lift-curve slope for the wing-end-plate combinations in- vestigated_ as well as the slope of the curve of induced-drag co- efficient as a function of the lift coefficient squared_ could be calculated within reasonable accuracy by using the classical theory for evaluating the end-plate effects.

6. The use of airfoil shapes as end-plate cross sections is desirable.

7. The influence of the addition of end plates of various sizes and shapes on the static longitudinal stability of an unswept wing was found to be negligible.

WIND-TUNNEL TESTS AT LOW SPEED OF SWEPT ANDYAWED WINGS HAVING TN 2445 VARIOUS PLANFORMS_ Paul E. Purser and M. Leroy Spearma%December The results of low speed tests of several small-scale models of yawed and swept wings indicated that: The lift-curve slope and the effective dihedral for swept wings can be computedwith a reasonable degree of accuracy in the low C L range with existing theories.

In general_ reducing the aspect ratio and the ratio of root chord to tip chord produced increases in drag and effective dihedral and slightly increased the longitudinal stability near the stall.

Cutting off the tip of a sweptback wing normal to the leading edge reduced the effective dihedral at low CL'S and gave a slight reduction in the drag at high CL'S.

Sweeping forward a part of the outer panel of a sweptback wing improved the longitudinal stability and decreased the effective dihedral but also increased the drag at high CL'S and slightly increased the CLmax.

i00 The use of either leading-edge or trailing-edge high-lift devices on sweptback wings increased the L/D ratio and the effective dihedral at high CL'S.

An increase in the ratio of root chord to tip chord on a swept- forward wing caused decreases in aileron rolling-moment effective- ness that were greater than the losses computed for unswept wings.

TN 2465 EXPERIMENTAL AERODYNAMIC DERIVATIVES OF A SINUSOIDALLY OSCILLATING AIRFOIL IN TWO-DIMENSIONAL FLOW_ Robert L. Halfman_ November1951 Experimental measurementsof the aerodynamic reactions on a symmetrical airfoil oscillating harmonically in a two-dimensional flow are presented and analyzed. Harmonicmotions include pure pitch and pure translation_ for several amplitudes and super- imposed on an initial angle of attack# as well as combinedpitch and translation. For all but the combined.motion tests_ either two or three airspeeds were used_ averaging about 95 mph_and the frequency range was covered for each airspeed in half-cycle per second steps.

The most general conclusion to be drawn from this analysis is that the experimental data corroborate the predictions of the theory over an important range of reduced frequency. The component analysis indicates that two-dimensional conditions were not quite realized for the tests_ although the effective aspect ratio was well above six. A reduction of the clearances between airfoil and vertical end plates would undoubtedly raise the effective aspect ratio to a very high value. The combined-motion tests indicate that_ for the typical flutter condition chosen_ the experimental and theoretical work-per-cycle conditions check very well. In the case of pure pitch there is an encouraging agreement between vari- ous independent groups of data.

TN 2495 WIND-TUNNEL INVESTIGATION OF EFFECTS OFVARIOUS AERODYNAMIC BALANCE SHAPES ANDSWEEPBACK ONCONTROL-SURFACE CHARACTERISTICS OF SEMI- SPAN TAlL SURFACES WITHNACA 0009_ 0015_ 66-009# 66(215)-014_ AND CIRCULAR-ARC AIRFOIL SECTIONS_ John J. Harper_ October 1951 Tests were madeof the above airfoil sections for use as tail surfaces. The ones with sweepwere swept back 40° at the 25%-chord line.

The slope of CL_varied with thickness. Sweeping the airfoil back reduced the lift-curve slope_ but the decrease due to sweepwas not as much as predicted. Increasing the trailing edge angle decreased CL_.

For a given thickness ratio_ the hinge-moment coefficient Ch_was not greatly affected by airfoil section when comparedwith changes i01 in trailing edge angle. Also for the trailing edge change had more effect than airfoil section. Ch6_ The plain tab tested on the unswept models yielded about the same increment in Ch6on the NACA 0009 and 0015 profiles with an internal balance. A lagging tab reduced the flap lift effectiveness_ but it also reduced Ch6 to about 50%of the unbalanced value. On the swept profiles the tab was less effective generally. The results come closer to lifting-surface results than lifting line-results.

TN 2502 EXAMPLES OFTHREE REPRESENTATIVE TYPES OFAIRFOIL-SECTION STALL AT LOWSPEED_ GeorgeB. McCullough and Donald E. Gault_ September The following airfoil sections were tested generally for stalls which were put into the categories of leading edge stall_ trailing edge stall_ and thin wing stall: 633-018 631-012 63 -009 64A006 Information can be obtained in an airfoil section handbook.

TN 2525 THE EFFECT OF RATE OF CHANGE OF ANGLE OF ATTACK ON THE MAXIMUM LIFT COEFFICIENT OF A PURSUIT AIRPLANE_ Burnett L. Gadeberg_ October 1951 The effect of rate of change of _ on CLmax of a pursuit type air- plane equipped with a low-drag wing has been investigated in stalls of varying abruptness over a Mach number range of 0.18 to 0.49 and Reynolds numbers from 6.1 to 13.4 million.

The CLmax increased approximately linearly with rate of change of to the limits of this test [tests carried to values of (C/V)(d_/dt) --pitching parameter_ degrees per chord length of travel--of 0.66].

The combined effect of Mach and Reynolds number caused the rate of change of CLmax with rate of change of _ to vary from approxi- mate 0.25 to 0.70.

Above a Mach number of approximately 0.32_ Reynolds number had less effect on the rate of change of CLmax with rate of change of than at lower Mach numbers.

TN 2644 EXPERIMENTAL INVESTIGATION OF A NACA 64A010AIRFOIL SECTION WITH 41 SUCTION SLOTS ONEACH SURFACE FORCONTROL OFLAMINAR BOUNDARY LAYER_ Dale L. Burrows and Milton A. Schwartzberg_ April 1952 An experimental investigation of an NACA64A010airfoil section equipped with 82 boundary-layer suction slots (41 per surface) indicated that laminar flow could be maintained over 0.91 chord up to Reynolds numbers as high as 107. This result was obtained on only one surface of the model where the slot radii forward and rearward_ respectively_ were approximately 1.0 and 0.5 times the slot width_ 0.005 inch. The C D equivalent of the suction power required to obtain this result was as low as 0.0006 (for the one surface) which when multiplied by 2 and combinedwith an estimated wake drag indicated that a drag coefficient of 0.0024 or less might be obtained for an airfoil having two sides that operated with equal effectiveness_ as compared to 0.0042 for the plain smooth airfoil. It was found that the total suction-flow quantity and the suction drag required to obtain the results at a Re of 107 were of the sameorder as the values predicted by this analysis.

Perhaps the most significant observation of the investigation was the increasing difficulty encountered in obtaining full-chord laminar flow at higher Reynolds numbers. The degree of the dif- ficulty was indicated by the extreme amount of care required to provide slot-entry contours and a smoothness of surface that would not cause transition. At the higher Reynolds numbers the rough- ness which seemedto prevent laminar flow was so small that a soft- lead pencil used as a hone was found to be effective in further reducing the roughness and advancing the Re for extensive laminar flow.

TN 2676 SUMMARY OF STALL-WARNING DEVICES_ John A. Zalovcik_ May 1952 Gives principles of operation of devices only.

TN 2753 EFFECTS OFMACH NUMBER VARIATION BETWEEN 0.07 AND0.34 ANDREYNOLDS NUMBER VARIATION BETWEEN 0.97xi06 AND8.10x106 ONTHEMAXIMUM LIFT COEFFICIENT OF A WING OF NACA 64-210 AIRFOIL SECTIONS_ James E.

Fitzpatrick and William C. Schneider_ August 1952 The effects of Machnumber and Reynolds numberon CLmax of a wing of section NACA64-210 are presented. The ranges of Mach number (M) obtained was 0.07 to 0.34 at atmospheric pressure and 0.08 to 0.26 at a pressure of 33 psia. The corresponding Reynolds number ranges were from 0.97xi06 to 4.44xi06 and from 2.20xi06 to 8.10x106 respectively. The tests were madewith and without partial-span and full-span split flaps deflected 60°. Pressure distribution measure- ments were obtained for all configurations.

The CLmax was a function of the two independent variables_ Mach number and Re_ and both parameters had an important effect on the CLmaxin the ranges investigated. The stall progression and the shape of the lift-curve at the stall were influenced by variations in both M and Re. Peak CLmax'Swere measuredat M between 0.12 and 0.20_ depending on Re range and flap configuration.

There was very little influence of either M or Re on the maximum lift of the wing with leading edge roughness.

TN 2776 THEEFFECT OF A SIMULATED PROPELLER SLIPSTREAM ONTHEAERODYNAMIC CHARACTERISTICS OF AN UNSWEPT WING PANEL WITHANDWITHOUT NACELLES AT MACH NUMBERS FROM 0.30 TO0.86_ Gareth H. Jordan and Richard I.

Cole_ September 1952 A preliminary investigation was madein the Langley 24" high-speed tunnel in order to determine the effect of a simulated propeller slipstream on the aerodynamic characteristics of an unswept wing panel with and without nacelles at _ of 0o and 3° for M = 0.30 to 0.86. The test results obtained with Machnumbers of the simu- lated propeller slipstream equal to and 10%greater than free- stream Mach numbers indicated: The increased velocity of the simulated propeller slipstream caused no significant changes in lift and pitching-moment coeffi- cients for the configurations tested here.

The Machnumber for drag rise near zero lift was decreased approximately 0.02 as a result of the increase in simulated- propeller-slipstream velocity for all configurations.

TN 2796 EXPERIMENTAL STUDY OF THEEFFECTS OF FINITE SURFACE DISTURBANCES ANDANGLE OFATTACK ONTHELAMINAR BOUNDARY LAYER OFAN NACA 64A010AIRFOILWITHAREA SUCTION_ Milton A. Schwartzberg and Albert L. Braslow_ October 1952 A low-turbulence investigation of an NACA 64A010airfoil section with porous surfaces was madeto determine the effectiveness of continuous suction in maintaining full-chord laminar flow behind finite disturbances and at _ other than 0o. It was found that: The use of area suction resulted in a relatively small increase in the size of a small but finite surface disturbance required to cause premature boundary layer transition as comparedwith that for the airfoil without suction. With or without continuous suction_ the maximum size of a proturberance that will not cause premature transition is small with respect to the boundary layer thickness.

The laminar boundary layer stability theory_ which is based on vanishingly small_ 2-dimensional_ aerodynamically possible dis- turbances in the boundary-layer_ appears to be of little practical significance in determining the sensitivity of the laminar boundary layer to surface projections.

By use of area suction_ it was possible to restore the flow in the boundary layer from the turbulent to the laminar state in the wake of a single cylindrical projection situated on the airfoil in the region of favorable pressure gradient at high suction-flow co- efficients. The flow about the projection was such that probably only slight increases in suction quantity or projection Reynolds numberwould have been required to establish complete turbulence from the projection to the airfoil trailing edge.

Combined wake and suction drag coefficients lower than the C D of the plain airfoil can be obtained through a range of low C L by the use of area suction_ provided that the airfoil surfaces are main- tained sufficiently smooth.

TN 2847 SECTION CHARACTERISTICS OFA 10.5-PERCENT-THICK AIRFOIL WITHAREA SUCTION AS AFFECTED BY CHORDWISE DISTRIBUTION OF PERMEABILITY_ Robert E. Dannenbergand JamesA. Weiberg_ December1952 The maximum lift of a symmetrical 10.51% thick wing was increased from a CL of 1.3 to 1.8 by meansof area suction over the first 3%of the chord for a section flow coefficient of 0.0014 at a free-stream q of 30 psf.

The maximum lift of the plain wing appeared to be limited by leading-edge (LE) stall_ whereas the stall of the wing with suc- tion appeared to result from separation of the turbulent boundary layer from the trailing-edge (TE). This would make subsequent increases in the maximum lift dependent on control of the turbu- lent boundary layer.

The flow-resistance characteristics as well as the chordwise variation of permeability were found to be important in reducing the suction-flow quantity and suction power required for a given lift. A C L of 1.71 was attained with a flow coefficient CQof 0.00135 and a power drag coefficient of 0.033 with a porous sur- face material of constant resistivity. By stepping the thickness of the porous material and hence changing the chordwise distribu- tion of resistivity_ the CQrequired to attain a C L of 1.71 was reduced to 0.0008 and power drag coefficient was reduced to 0.024.

An analysis of the effects of the distribution and resistivity of the porous surface material on the suction power and velocity distribution indicated that power drag coefficients lower than those obtained in the tests may be possible. It must be empha- sized that the minimumpower attainable will be governed by the suction-air velocities necessary to obtain satisfactory lift characteristics at a given free stream velocity.

TN 2908 DETERMINATION OFMEAN CAMBER SURFACES FORWINGS HAVING UNIFORM CHORDWISE LOADING ANDARBITRARY SPANWISE LOADING IN SUBSONIC FLOW_ S. Katzoff_ M. Frances Faison and Hugh C. DuBose_May 1953 The field of a uniformly loaded wing in subsonic flow is discussed in terms of the acceleration potential. It is shown that_ for the design of such wings_ the slope of the meancamber surface at any point can be determined by a line integration around the wing boundary. By an additional line integration around the wing boundary_ this method is extended to include the case where the local section lift varies with spanwise location (the chordwise loading at every section still remaining uniform).

The design of meancamber surfaces to sustain a specified area distribution of lift at subsonic speeds involves basically a relatively straightforward process: a system of bound and trail- ing vortices is set up in the plane of the wing according to the specified distribution of lift_ and the corresponding vertical velocity is calculated_ by the Biot-Savart law_ at points on the surface where the local slopes are desired. Reasonably practical numerical and graphical procedures have been developed for per- forming this integration of the velocity due to this distribution of vortices. If the chordwise loading is specified to be uniform_ as in a number of recent wing-design studies_ the problem is basically simplified_ as was shown_ the solution can then be re- duced from a double integral over the wing area (or over the wing area plus wake area) to a line integral around the boundary of the wing and_ in the simplest cases_ it can even be reduced to a purely analytical procedure.

The purpose of the paper was to outline the basic theory behind the solution of problems involving uniform chordwise loading_ to sum- marize the mathematical application of the theory and the develop- ment of the required formulas_ and to describe the actual use of these derived results in the design of meancamber surfaces for this type of loading.

Wings with arbitrary plan form and arbitrary spanwise loading were examined. Someof the integrals were given and methods of solu- tion were shown. Polygonal wings with uniform area loading were also examined. Compressibility corrections were shown and examples of calculated meancamber surfaces were given. Formulas for uni- formly loaded polygonal wings were developed in the appendix.

Three cases were developed in the appendix: (i) Path of integra- tion crosses vortex se_ment_ (2) Path of integration does not cross vortex segment_ (3) Vortex segmentparallel to free stream and hence to path of integration.

Most of the graphs given were used in conjunction with determina- tion of the value of someof the integrals.

THEEFFECTS OF CAMBER ONTHEVARIATION WITHMACH NUMBER OFTHE TN 2998 AERODYNAMIC CHARACTERISTICS OF A IO-PERCENT-THICK MODIFIED NACA FOUR-DIGIT-SERIES AIRFOIL SECTION_ Albert D. Hemenover_September The results of a wind-tunnel investigation to determine the effects of moderate amountsof camberon the aerodynamic characteristics of a 10-percent-thick modified NACA four-digit series airfoil section were presented for Mach numbers from 0.3 to 0.9. The corresponding Reynolds number variation was from approximately ix106 to 2xi06. The characteristics of airfoil sections cambered for design lift coefficients of 0.2 and 0.4 on an NACAequal to 0.8 mean line were comparedwith those of the corresponding un- camberedprofile. The investigation was conducted in the Ames I- by 3-1/2-foot high-speed wind tunnel_ a low-turbulence two- dimensional-flow wind tunnel. Measurementsof lift_ drag_ and pitching momentabout the quarter-chord point were madesimul- taneously at Machnumbers ranging from 0.3 to approximately 0.9 for the models at angles of attack increasing by increments of 1° or 2° from -6° to 12° . This range of angles of attack was suffi- cient to encompass negative lift at all Machnumbers and the lift stall up to a Mach numberof 0.775. The Reynolds number variation with Machnumber for these tests was shown.

i It was found that an increase in camber from 0 to 0.4 design section lift coefficient resulted in an increase in maximum lift coefficient. The effects on the respective variations with Mach number of lift-curve slope and angle of attack required to main- tain a given lift coefficient were similar to those on the cor- responding characteristics of an NACA 6-series airfoil of the same thickness. Increasing amounts of camber produced decreases in lift- and drag-divergence Mach numbers at low lift coefficients and increases in the values of these parameters at moderate to large lift coefficients.

Plots are given for section lift versus Mach number for various angles of attack.

Plots are given for section drag versus Mach number for various angles of attack.

Plots are given for section li_t versus Mach number for _=0 ° axis for various Mach numbers.

Plots are given for section lift versus section drag for various Mach numbers.

TN 3007 LIFT AND PITCHING MOMENT AT LOW SPEEDS OF THE NACA 64A010 AIRFOIL SECTION EQUIPPED WITH VARIOUS COMBINATIONS OF A LEADING-EDGE SLAT_ LEADING-EDGE FLAP_ SPLIT FLAP_ AND DOUBLE-SLOTTED FLAP_ John A.

Kelly and Nora-Lee F. Hayter_ September 1953 A two-dimensional wind-tunnel investigation at low speeds was madeof the NACA64A010airfoil equipped with various combina- tions of a leading-edge slat_ leading-edge flap_ split flap_ and double-slotted flap. Optimumslat positions were determined for a Reynolds numberof 6 million for the model with no trailing-edge flap and with the two trailing-edge flaps deflected. Section lift and pitching-moment characteristics of the various model arrange- ments were obtained for Reynolds numbers of 2_ 4_ 6_ and 7 million.

DynamicPressure (psf) MachNo.

TESTCONDITIONS R x 10-6 2 5 .06 4 20 .12 6 40 .17 7 60 .20 Measurementsof lift and pitching momentwere madewith a wind tunnel balance system. For the most part_ the tests were con- ducted at a Reynolds numberof 6 million. Data also were taken for Reynolds numbers of 2_ 4_ and 7 million for the basic airfoil model_ the model with optimum slat settings_ and the model with leading-edge-flap deflections of i0o_ 20o_ 30o_ and 40o.

Results The increases in the maximum section lift coefficient produced by the leading-edge flap or by the leading-edge slat in combina- tion with either of the trailing-edge flaps were approximately equal to the sum of the increments produced by each of the high- lift devices deflected individually. Extension of the leading- edge slat and deflection of the leading-edge flap produced incre- ments in maximum section lift coefficient of about 0.83 and 0.66_ respectively. Deflection of either leading-edge high-lift device caused the aerodynamic center to move forward. In the case of the leading-edge slat_ the aerodynamic center moved forward to approxi- mately the quarter point of the extended chord.

Section lift and section pitching momentwere plotted against angle of attack for three trailing edge flap configurations: (i) None_ (2) Split flap_ (3) Double-slotted flap.

TN 3126 A DESIGN STUDY OFLEADING-EDGE INLETSFORUNSWEPT WINGSjRobert E. Dannenberg_ March 1954 A practical method_ employing a lofting techniqu% was presented for determining the profile coordinates of an air inlet for the leading edge of an airfoil from formulas which were dependent only on the airfoil coordinates and on the height of the opening. The usefulness of this method was demonstrated by an analysis of the results of a wind-tunnel investigation of leading-edge inlets in an airfoil having the NACA 631-012 section. The analysis indicates that satisfactory characteristics were obtained for this airfoil with inlets designed from the formulas. The analysis includes a study of the effects of variations of inlet geometry on the experi- mentally determined aerodynamic characteristics of the ducted airfoil.

A leading-edge inlet designed by the method presented in this report entailed a change in the profile of the airfoil from the leading edge to the station of maximum airfoil thickness. Behind the latter station the shape of the airfoil remained unchanged.

The method for determining the profile for an inlet in an airfoil was presented in two parts_ designated as design step I and design step 2. Design step i provided a method for the design of a leading-edge inlet of arbitrary height_ upper- and lower-lip radii_ and stagger for a symmetrical airfoil. Design step 2 was concerned primarily with an alteration of the profile determined by step I to improve the internal pressure-recovery characteris- tics at high angles of attack. These design steps were described with equations written out. Design of inlets for camberedair- foils were also discussed. To study the characteristics of inlets derived from the design method_ an airfoil with various leading- edge inlets was tested in a wind tunnel. Air was drawn through the inlets into a hollow spar in the airfoil and then through a ducting system by a compressor outside the test chamber. The air flow through the inlet was calculated. The pressure drop across a calibrated orifice plate was measured. The inlet pressure losses were measured. The pressure distribution over the external surfaces of the inlets was measured.

Tunnel wall corrections to force measurementswere applied. The test results were presented for a Mach number of 0.14 and a Reynolds numberof 3_840_000based on the airfoil chord. The external drag on each inlet was calculated.

Results The airfoil with an inlet devised by the design method was found to possess satisfactory aerodynamic characteristics_ as compared to the plain airfoil_ with regard to lift_ drag_ pressure distri- bution_ and predicted drag-divergence Mach number. Introduction of stagger_ increasing the inlet entrance height_ or decreasing the leading-edge radius of the upper lip had a deleterious effect on the maximum lift. Increasing the amount of stagger and round- ing the inner surface of the lower lip improved the ram-pressure recovery at high angles of attack. A change in inlet-velocity ratio introduced an increment of velocity over the outer surface of an inlet that had a linear variation with inlet-velocity ratio.

With a given inlet and the experimental velocity distribution of the given inlet as a reference_ the change in the external velocity distribution caused by a small change of the external ordinates of the inlet can be calculated by an application of the principles of thin-airfoil theory.

I09 Lift coefficient_ critical Machnumber_ram-recovery ratio_ are plotted against _ and pressure coefficient is plotted against per- cent airfoil chord for various inlet height to airfoil thickness ratios.

TN 3129 INVESTIGATION OFA SLATIN SEVERAL DIFFERENT POSITIONS ONAN NACA 64A010AIRFOIL FORA WIDERANGE OF SUBSONIC MACH NUMBERS_ John A. Axelson and GeorgeL. Stevens_ March 1954 An investigation of the two-dimensional aerodynamic characteris- tics of an NACA64A010airfoil with a slat was conducted in the Mach number range from 0.25 to 0.85 with a corresponding Reynolds numberrange from 3.4 million to 8.1 million. Two families of slat positions were investigated_ one with the slat leading edge extended forward along the airfoil chord lin% and the other with the slat extended forward and displaced below the chord line. The angle-of-attack range was from -4° to 20° at the lower test Machnumbers but was limited by model strength at the higher Mach numbers. All section force coefficients presented were computed from the balance measurements. Section normal- force coefficients computed from integrations of the pressure distributions were in close agreementwith those from the balance measurements.

Over the entire Mach number range from 0.25 to 0.85_ the airfoil with the slat retracted was generally aerodynamically superior to any of the other airfoil-slat arrangements for section lift coeffi- cients up to 0.60.

At lower Machnumbers_ the highest maximum section lift coeffi- cients and the largest lift-drag ratios at high angles of attack were obtained with the slat extended forward but with its nose displaced below the extended chord line of the airfoil. At the higher Mach numbers_adverse aerodynamic changes resulted with those slat arrangements. These adverse changes which occurred at the higher Mach numbersconsisted of large increases in section drag_ increased angle of attack for zero lift_ and increasingly negative section pitching moments.

For section lift coefficients above 0.80 and for the widest range of test Mach numbers_the best aerodynamic characteristics were obtained with the nose of the slat on the extended chord line of the airfoil.

The increased maximum lifts and lift-drag ratios at the higher angles of attack which were obtained with the slats extended may be attributed primarily to the increased loading carried by the slat and the forward portion of the airfoil and to the greater pressure recovery on the upper surface of the airfoil.

ii0 for various Mach numbers for Charts are given for c6_ Cd_ cm different positions of the slat.

Pressure coefficient and drag were plotted against Mach number and lift was plotted against drag.

TN 3172 _FFECTS OF LEADING-EDGE RADIUS ANDMAXIMUM THICKNESS-CHORD RATIO ONTHEVARIATION WITHMACH NUMBER OF THEAERODYNAMIC CHARACTERIS- TICS OF SEVERAL THINNACA AIRFOIL SECTIONS_ Robert E. Berggren and Donald J. Graham_ April 1954 A wind-tunnel investigation was made to determine the effects of leading-edge radius and maximumthickness-chord ratio on the varia- tion with Mach numberof the aerodynamic characteristics of sev- eral thin syu_netrical NACA 4-digit-series airfoil sections. The Mach number range of the investigation was from 0.3 to approximately 0.9 and the corresponding Reynolds number range from approximately ixl0 6 to 2x106.

Airfoils Tested Leading Edge Radius (percent chord) O. 18 0004 - 1.10 40/1. 575 0004 - 3.30 40/1.575 coordinates of the airfoils 0006 - i. I0 40/1. 575 are given in this report in 0006 - .70 40/1. 575 table form i0 0006 - .27 40/1. 575 0008 - I. i0 40/1. 575 1 I0 0010 - 1.10 40/1.575 Tests were made in a high speed- low-turbulence_ two-dimensional wind tunnel. Measurements of lift_ drag_ and pitching moment were made. Lift and pitching moments were evaluated by integra- tions of the pressure reactions on the tunnel walls produced by the airfoil models. Drag measurements were made by means of wake surveys using a rake of total-head tubes.

Results i. The variations with Mach number of the lift_ drag_ and pitch- ing moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of the leading-edge radius from 0.18 to 0.53 percent of the chord. The same is true for a leading-edge-radius variation from 0.I0 to 0.40-percent chord on a 6-percent-chord-thick section.

2. Reduction of the maximum thickness-chord ratio from i0 to 4 percent progressively improved the variation of lift-curve slope with Mach number_ the lift and drag-divergence characteristics_ and the maximum section lift characteristics at Mach numbers above 0.60.

iii 3. Section pitching-moment characteristics were not greatly affected by a variation of the maximum thickness-chord ratio.

Lift_ drag_ and pitching momentcoefficients were all plotted against Machnumber and Machnumber for _ = 0° axis. These graphs were usually made for one airfoil and various flap deflections.

INFLUENCE OF AIRFOIL TRAILING-EDGE ANGLE ANDTRAILING-EDGE- TN 3174 THICKNESS VARIATION ONTHEEFFECTIVENESS OFA PLAIN FLAPAT HIGH SUBSONIC MACH NUMBERS_ Albert D. Hemenoverand Donald J. Graham_ June 1954 The effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap were appraised from wind-tunnel tests at Machnumbers from 0.3 to 0.9 and Reynolds numbersvarying correspondingly from i to 2 million. The airfoil trailing-edge angle was varied from approxi- mately 18° to 6o_ and the trailing-edge thickness from zero to the thickness at the flap hinge line.

Profile Trailing Edge Angle 17.9 ° 00.0-0.70 40/1. 575 12 ° 0000-0.70 40_I.051 6° 0010-0.70 40/0.524 0o 0010-0.70 40/1. 575 7.5 ° 0010-0.70 40/1.575 Tests were made in a high-speed wind tunnel_ 2_dimensional flow and low turbulence'.

Measurements of lift_ drag_ and pitching moment were made at Mach numbers from 0.3 to 0.9 with angle of attack range from -2 ° to 12° .

Flap deflection was varied by small increments from approximately -i ° to approximately 6° for the greatest part of the investigation_ but in a few cases it was increased to as high as 14 degrees. Lift and pitching moments were measured by interpretations of the pres- sure reactions on the tunnel walls of the forces on the airfoils.

Drag was determined by wake surveys.

Results From the results it would appear that the variation with Mach number of the effectiveness of a plain flap cannot be satisfac- torily controlled by variation of such parameters as the trailing- edge angle and the trailing-edge thickness independently. In order to maintain a satisfactory degree of flap effectiveness throughout the subsonic Mach number range by variation of airfoil geometry_ the airfoil shape should be such as to prevent flow separation from the surface appreciably ahead of the trailing edge.

This can readily be accomplished from placing the airfoil maximum thickness at the trailing edge_ but the attendant penalty in drag would be large. To approach the desired objective for an airfoil on which somepressure recovery is to be madeahead of the trail- ing-edge_ present indications are that the profile should embody sometrailing-edge thickness in conjunction with a relatively small trailing-edge angle.

Numerousgraphs are given of lift_ drag_ and pitching moment versus both Mach number and Mach number of _ = 0o axis for a specific trailing edge thickness and various angles of attack and flap deflections.

TN 3244 AERODYNAMIC CHARACTERISTICS OF THENACA 64-010 AND0010-I. I0 40/1.051 AIRFOIL SECTIONS AT MAC_NUMBERS FROM 0.30 TO0.85 ANDREYNOLDS NUMBERS FROM 4.0x10v TO 8.0xi06_ Laurence K. Loftin_ Jr._ August 1954 A short two-dimensional investigation has been madein the Langley low-turbulence pressure tunnel to determine the aerodynamic char- acteristics of the NACA 64-010 and 0010-I. I0 40/1.051 airfoil sections. The Mach number range was .3 to .85 while the Reynolds number range was 4.0xlO 6 to 8.0x106. The purpose of the investi- gation was to determine the extent to which the relative merits of the two airfoil sections_ as indicated by previous investiga- tions _NACA RMA9_18 and RMA9E31) at Reynolds numbers from 1.0xl0 _ to 2.0x10 _ might be altered by increases in the Reynolds number. The investigation was madeso that a choice could be madebetween the two sections for an aerodynamic problem. The tests of each model consisted in measurementsof the lift_ drag_ and pitching momentfor angles of attack from -2 ° to 7° .

The results indicated that the increment between the higher drag of the NACA 0010-i. I0 40/1.051 airfoil section and the drag of the NACA 64-010 airfoil section shown by the data of NACARM AgGI8 and RMA9E31for moderate lift coefficients and relatively high subsonic speeds was much smaller in the present higher Rey- nolds numberinvestigation.

Lift_ drag_ and pitching momentsection coefficients were plotted against Mach number_c_ was plotted against cd and Reynolds numberwas plotted agalnst Machnumber.

This report could only serve as a point on a graph for the particular airfoil sections when considering a design manual.

TN 3285 SECTION CHARACTERISTICS OFAN NACA 0006 AIRFOIL WITHAREASUCTION NEAR THELEADING EDGE_ JamesA. Weiberg and Robert E. Dannenberg_ September1954 Suction was investigated to see if it could prevent or delay leading edge stall. The airfoil investigated was the NACA 0006.

The model was equipped for area suction near the leading edge and with a 0.20-chord split flap.

Measurementswere madeof the surface pressure distributions_ lift_ profile drag_ suction requirements_ and boundary-layer character- istics. A vacuumpumpprovided the suction. Boundary-layer velocities were measuredby meansof small rakes fastened to the airfoil surface.

The tests covered a range of free-stream velocities from 93 to 183 fps. Reynolds number range was from 2.4 to 5.1 million.

Wake-drag data were obtained at a Reynolds numberof 5.1 million.

At a free-stream velocity of 162 fps_ a section flow coefficient of 0.0010 increased C_maxfrom about 0.87 to 1.25 by delaying stall from 9° to 12° angle of attack. The most economical extent of suction for this lift increase was on the upper surface from the leading edge fo 0.5-percent chord.

High negative values of pressure coefficient were obtained on the leading edge of the airfoil with suction. The pumpmust supply low pressures and this tends to complicate the design of the system for area suction.

From a comparison of the results obtained on the NACA 0006 airfoil in this investigation with the results obtained on a symmetrical airfoil 10.5 percent thick (NACA TN 3093)_ it was found that for a given lift increase the minimumsuction quality required was re- lated to the magnitude of the difference between the external pressure coefficients at the leading and trailing edges of the porous area.

TN 3324 A NOTE ONTHEDRAG DUETO LIFT OFRECTANGULAR WINGS OFLOW ASPECT RATIO_Edward C. Polhamus_January 1955 Considerable work both experimental and theoretical_ has been done with regard to the aerodynamic characteristics of low.aspect-ratio wings. Comparisonsof the experimental and theoretical results have indicated that_ at least for incompressible flow_ the lift and pitching-moment characteristics of low_aspect-ratio wings can be estimated with reasonable accuracy. The estimation of the drag due to lift_ however_ has been hamperedby what appears to be a large effect of aspect ratio on the variation of profile drag with lift coefficient. The purpose of the'present paper_ the_e- fore_ was to attempt to determine the effect of aspect ratio on the variation of the profile drag with lift coefficient.

Lifting line theory neglects any effect of the vortex sheet on the chordwise loading due to induced curvature of the streamlines and therefore is not applicable to low aspect ratio wings with regard to lift and moment. Lifting-surface solutions must be used to account for this effect of the vortex sheet.

In the low-lift range_ where the profile drag is relatively in.

dependent of lift coefficient_ the drag due to lift can be pre- dicted fairly accurately by equation C L CDi - 3.14(A+_ The problem remaining is that of the variation of the profile drag with lift.

From tests it was found that the profile drag due to lift is dependent to a large extent upon the aspect ratio of the wing_ with extremely high values occurring for the low-aspect-ratio wing. Therefore_ it would seemthat the profile drag for a three- dimensional wing at a given lift coefficient cannot be determined from corresponding two-dimensional tests at that lift coefficient.

The large effect of aspect ratio on the profile drag may be associated with the fact that_ as the aspect ratio decreased_ the chordwise pressure gradient due to angle of attack in the vicinity of the leading edge increases as a result of the induced camber (streamline curvature) associated with the chordwise variation of the induced downwash. This increase in the adverse pressure gradient_ through its effect on separation at the leading edge_ would be expected to cause an increase in the profile drag.

The effect of aspect ratio on the chordwise pressure gradient is shownbelow.

k CL=1.0 AP =°'s x/c The induced camber corresponds to a negative geometric camber and increases in magnitude with decreasing aspect ratio.

From the graph it would therefore appear that boundary-layer and separation characteristics of the wing with aspect ratio of 0.5 may more nearly correspond to those of the two-dimensional airfoil operating at twice the lift coefficient.

It will be noted that at low aspect ratios considerably greater suction is required than is given by lifting-line or two- dimensional theory that incorporates a lift coefficient increased by a delta CL_which corresponds to the loss due to induced camber.

It now appears possible that the increment of profile drag due to lift may be independent of aspect ratio for a given value of the effective two-dimensional lift coefficient where delta C L is equal to the delta CL) c_ -- cL (I + amount of induced camber load.

C L In figure 3 the data of figure 2 for profile drag due to lift are replotted as a function of the effective two-dimensional lift coefficient_ c_ = C L I + .08 R=O.5

I

e_ o .o6" / /AR=I,O U I U .04 .d AR=2.O II _.. .02 U • 2 .4 .6 .8 C L .08 Points indicate / UI_.06 different AR[5,1,2) U 0 .04 J)Z

o

Cl I ' ._ .4 .6 .8

ci' = cL

It was shown that_ to a good approximation_ this effective two- dimensional lift coefficient can be expressed as

4 c L I•

where CL is the total lift coefficient and _R is the aspect ratio.

When the profile drag for several aspect ratios was plotted as a function of CL i +_ the effect of aspect ratio was eliminated to a large extent.

This_ of coursej implies that when utilizing two-dimensional data to determine the three-dimensional profile drag_ the two- dimensional profile drag corresponding to a higher lift coefficient must be used. Other implications are that effects that occur in two-dimensional flow (such as Reynolds number_ profile shape_ and so forth) will occur at progressively lower lift coefficients and be more severe as the aspect ratio is reduced.

TN 3536 A LIMITED FLIGHT INVESTIGATION OF THE EFFECT OF THREE VORTEX- GENERATOR CONFIGURATIONS ON THE EFFECTIVENESS OF A PLAIN FLAP ON AN UNSWEPT WING_ Garland J. Morris and LindsaY J. Lina_ September A test was conducted to study the effectiveness of vortex genera- tors. The vortex generators consisted of airfoils mounted on the upper surface of the wing and at right angles to it. For rectangular generators mounted at 63%and 75%chord_ no appreciable results were found_ but for a tapered type of vortex generator_ the lift at 19 ° of flaps was equal to the lift at 27° of flaps without the generators. It was concluded that vortex generators provided only a little useful improvement in flap effectiveness_ but that vortex generators may be suitable for improving the effective- ness of ailerons which operate at moderate deflections.

TN 3797 SECTION CHARACTERISTICS OF THENACA 0006 AIRFOILWITHLEADING-EDGE ANDTRAILING-EDGE FLAPS_Bruno J. Gambucci_December1956 The 0006 section was tested in a wind tunnel to obtain all the airfoil section characteristics. The airfoil had a 0.15ochord leading edge flap and a 0.30-chord trailing-edge flap. Tests were madewith increments of leading edge and trailing edge flap deflections. Pressure distributions were taken_ and the results were given in tabular form on charts.

Re = 4.5x106 MachNo. = 0.15 2.4_ 1.6- Variation of maximum lift ¢Imo x with nose flap deflected 0.8 ._ l I I I, I 0 20 3 0 40 50 _n, deg.

TN 3822 SOME MEASUREMENTS OF AERODYNAMIC FORCES AND MOMENTS AT SUBSONIC SPEEDS ON A WING-TANK CONFIGURATION OSCILLATING IN PITCH ABOUT THE WING MIDCHORD_ Sherman A. Clevenson and Sumner A. Leadbetter_ December 1956 The investigation was made to further the knowledge of the unsteady aerodynamic forces on wing-tank configurations. Measurements were made of the air forces acting on low aspect ratio wings with a tip tank. The tank was tested with a delta fin_ a trapezoidal fin_ and without a fin. The coefficients for the oscillating tank in the presence of an oscillating wing were compared with calculated coefficients for an engine nacelle as determined from a paper by Andropoulos_ Chee_ and Targoff.

The aerodynamic characteristics were presented for a range of reduced frequency from 0.050 to 0.657 and for a range of Mach numbers from 0.18 to 0.75. The Re range was 0.9 x 106 to 9.5 x 106. A resonant-oscillating technique was used.

Results I. Total moments were decreased with fin addition_ but moments were still larger than for the wing alone. The addition of the tip tank with or without fins had a stabilizing influence on the configuration.

2. The overall lift and moment phase angle did not change greatly with the tank addition.

3. Either fin increased tank lift.

4. Tank lift and phase angle agreed well with results of an engine-nacelle theory_ while moment agreement was poor.

n TN 3871 AN INVESTIGATION AT SUBSONIC SPEEDS OF SEVERAL MODIFICATIONS TO THE LEADING-EDGE REGION OF THE NACA 64A010 AIRFOIL SECTION DESIGNED TO INCREASE MAXIMUM LIFT_ Ralph L. Maki and Lynn W.

Hunton_ December 1956 Three modifications of the leading-edge region of a NACA 64A010 airfoil section were tested. One of the nose modifications was designed to have the same leading-edge radius and similar camber distributions as a standard designated section_ the NACA 13010.

The other two sections differed either in leading edge radius or type of camber. Pressure distributions were found_ and measurements of lift_ drag and pitching moment were made.

The Reynolds numbers were = 2.8_ 4.0_ and 5.8 x 106 with Mach number varying from 0.08 to 0.17. High speed tests were also made.

Tests at low speeds showed that the leading-edge modifications were capable of increasing CLmax by as much as 0.58 for a 10% thick section. Increases were explained by an increase in angle of attack at which stall occurs. The nose modifications intro- duced no incremental pitching moment. A simple design procedure for estimating the incremental maximum lift due to an arbitrary modification_ based on control of the theoretical minimumpres- sure_ was unsatisfactory.

Tests at high speeds showedthe increments in maximum lift pro- vided by the leading-edge modifications were reduced by compres- sibility effects and vanished at a Machnumber of 0.65.

NACA Technical Notes Dealing with Aerodynamics But Not Judged Applicable to Light Aircraft A NEW METHOD OF STUDYING THE FLOW OF THE WATER ALONG THE BOTTOM TN 749 OF A MODEL OF A FLYING BOAT HULL_ Kenneth E. Ward_ February 1940 WIND-TUNNEL INVESTIGATION OF AN NACA 23030 AIRFOIL WITH VARIOUS TN 755 ARRANGEMENTS OF SLOTTED FLAPS_ I. G. Recant_ March 1940 PRESSURE-DISTRIBUTION INVESTIGATION OF NACA 0009 AIRFOIL WITH A TN 759 30-PERCENT-CHORD PLAIN FLAP AND THREE TABS_ Milton B. Ames_ Jr.

and Richard I. Sears_ May 1940 TN THE FLOW OF A COMPRESSIBLE FLUID PAST A SPHERE_ Carl Kaplan_ May TN 771 TRANSIENT EFFECTS OF THE WING WAKE ON A HORIZONTAL TAIL_ Robert T.

Jones and Leo F. Fehlner_ August 1940 TN 779 AERODYNAMIC HEATING AND THE DEFLECTION OF DROPS BY AN OBSTACLE IN AN AIR STREAM IN RELATION TO AIRCRAFT ICING_ Arthur Kantrowitz_ October 1940 TN 782 WIND-TUNNEL TESTS OF AN NACA 23021 AIRFOIL EQUIPPED WITH A SLOTTED EXTENSIBLE AND A PLAIN EXTENSIBLE FLAP_ Thomas A. Harris and Robert S. Swanson_ November 1940 TN 797 THE END-PLATE EFFECT OF A HORIZONTAL-TAIL SURFACE OF A VERTICAL- TAlL SURFACE_ S. Katzoff and William Mutterperl_ February 1941 TN 801 TEST OF ROUND AND FLAT SPOILERS ON A TAPERED WING IN THE NACA 19-FOOT PRESSURE WIND TUNNEL_ Carl J. Wenzinger and John D. Bowen_ March 1941 808 WIND-TUNNEL INVESTIGATION OF AN NACA 23012 AIRFOIL WITH SEVERAL TN ARRANGEMENTS OF SLOTTED FLAPS WITH EXTENDED LIPS_ John G. Lowry_ May 1941 TN 823 PLATE METHOD OF GROUND REPRESENTATION FOR WIND-TUNNEL DETERMINA- TION OF ELEVATOR EFFECTIVENESS IN LANDING_ I. G. Recant_ September TN 829 VELOCITY GAINED AND ALTITUDE LOST IN RECOVERIES FROM INCLINED FLIGHT PATHZ_ H. A. Pearson and J. B. Garvin_ October 1941 TN 835 ANALYSIS OF GROUND EFFECT ON THE LIFTING AIRSCREW_ Montgomery Knight and Ralph A. Hefner, December 1940 TN 836 HYDRODYNAMIC TESTS OF A 1/10-SIZE MODEL OF THE HULL OF THE LATECOEE 521 FLYING BOAT - NACA MODEL 83_ Roland E. Olson and Lindsay J. Lina_ December 1941 TN 841 THEPHOTOVISCOUS PROPERTIES OFFLUIDS_R. Weller_ D. J. Middlehurst_ and R. Steiner_ February 1942 TN 844 INVESTIGATION OF THEFORCES ACTING ONGLIDERS IN AUTOMOBILE-_ PULLEY-_ WINCH-_ ANDAIRPLANE-TOWED FLIGHT_W. B. Klemperer_ March 1942 TN 845 GROUND EFFECT ONDOWNWASH ANGLES ANDWAKE LOCATION_ S. Katzoff and Harold H. Sweberg_May 1942 TN 850 A PREL]]_INARY INVESTIGATION OFTHEELECTRICAL STRUCTURE OF THUNDERSTORMS_ E. J. Workman and R. E. Holzer_ July 1942 TN 864 THEELECTRICAL STRUCTURE OF THUNDERSTORMS_ E. J. Workman_ R. E.

Holzer_ and G. T. Pelsor_ November1942 TN 875 A ROSETTE STRAINCOMPUTER_ W. B. Klemperer_ December1942 TN 881 A HOT-WIRE CIRCUIT WITHVERY SMALL TIME LAG_John R. Weske_February TRANSITION BETWEEN LAMINAR ANDTURBULENT FLOW BYTRANSVERSE CON- TN 891 TAMINATION_ Alex C. Charters_ Jr._ March 1943 TN 892 TURBULENT FLOW BETWEEN ROTATING CYLINDERS_ Pai Shih-l_ March 1943 / TN 932 THE NUMERICAL SOLUTION OF COMPRESSIBLE FLUID FLOW PROBLEMS_ Howard W. Emmons_ May 1944 TN 946 ON THE GENERAL THEORY OF THIN AIRFOILS FOR NON-UNIFORM MOTION_ Eric Reissner_ August 1944 THE "LIMITING LINE" IN MIXED SUBSONIC AND SUPERSONIC FLOW OF TN 961 COMPRESSIBLE FLUIDS_ Hsue-Shen Tsien_ November 1944 TN 963 FRICTION IN PIPES AT SUPERSONIC AND SUBSONIC VELOCITIES_ Joseph H.

Keenan and Ernest P. Neumann_ January 1945 ON A METHOD OF CONSTRUCTION TWO-DIMENSIONAL SUBSONIC COMPRESSIBLE TN 969 FLOWS AROUND CLOSED PROFILES_ Lipman Bers_ March 1945 ON THE CIRCULATORY SUBSONIC FLOW OF A COMPRESSIBLE FLUID PAST A TN 970 CIRCULAR CYLINDER_ Lipman Bers_ July 1945 TN 972 ON TWO-DIMENSIONAL FLOW OF COMPRESSIBLE FLUIDS_ Stefan Bergman_ August 1945 TN 973 GRAPHICAL AND ANALYTICAL METHODS FOR THE DETERMINATION OF A FLOW OF A COMPRESSIBLE FLUID AROUND AN OBSTACLE_ Stefan Bergman_ July 122 • TN 980 A PHOTOELECTRIC HYGROMETER_ Bernard Hamermesh_ Frederick Relnes, and Serge A. Korff_ May 1945 TN 985 MEASUP_ENTS OF RECOVERY FACTORS ANDCOEFFICIENTS OF HEATTRANSFER IN A TUBE FORSUBSONIC FLOW OF AIR3 William H. McAdams_ Lloyd A.

Nicolai_ and Joseph H. Keenan_June 1945 TN 990 MEASUREMENT OF THEARITHMETIC MEAN VELOCITY OF A PULSATING FLOW OF HIGHVELOCITY BYTHEHOT-WIRE METHOD_ John R. Wesk% April 1946 TN 995 TWO-DIMENSIONAL IRROTATIONAL MIXEDSUBSONIC ANDSUPERSONIC FLOW OF A COMPRESSIBLE FLUID ANDTHEUPPER CRITICAL MACH NUMBER, Hsue-Shen Tsien and Yung-Huai Kuo, May 1946 TN 1003 THETHEORETICAL FLOW OFA FRICTIONLESS, ADIABATIC,PERFECT GAS INSIDE OFA TWO-DIMENSIONAL HYPERBOLIC NOZZLE, HowardW. Emmons_ May 1946 TN 1006 VELOCITY DISTRIBUTIONS ONWINGSECTIONS OF ARBITRARY SHAPE IN COMPRESSIBLE POTENTIAL FLOW. I - SYMMETRIC FLOWS OBEYING THE SIMPLIFIEDDENSITY-SPEED RELATION, Lipman Bers_ April 1946 TN 1012 VELOCITY DISTRIBUTION ONWINGSECTIONS OF ARBITRARY SHAPE IN COMPRESSIBLE POTENTIAL FLOW. II - SUBSONIC SYMMETRIC ADIABATIC FLOWS_ Lipman Bers, June 1946 TN i017 A METHOD FORTHEDETERMINATION OF AIR INFILTRATION RATES IN AIR- PLANE CABINS_ Jackson R. Stadler and E. Lewis Zeiller_ April 1946 TN i018 METHODS FORDETERMINATION ANDCOMPUTATION OF FLOW PATTERNS OF A COMPRESSIBLE FLUID, Stefan Bergman, September 1946 TN 1024 USEOF FREON-12 AS A FLUID FORAERODYNAMIC TESTINU_ Paul W. Huber, April 1946 TN 1032 PROPERTIES OF LOW-ASPECT-RATIO POINTED WINGS AT SPEEDS BELOW AND ABOVE THESPEED OF SOUND, Robert T. Jones_ March 1946 TN 1049 ANALYSIS OF AVAILABLE DATA ONTHEEFFECTS OF TABSONCONTROL- SURFACE HINGE MOMENTS, Stewart M. Crandall and Harry E. Murray, May 1946 TN 1050 WIND-TIINNEL INVESTIGATION OF END-PLATE EFFECTS OF HORIZONTAL TAILS ONA VERTICAL TAIL COMPARED WITHAVAILABLE THEORY_ Harry E. Murray, April 1946 TN 1055 COMPARISON OF TWO-DIMENSIONAL AIR FLOWS ABOUT AN NACA 0012 AIR- FOIL OF 1-INCHCHORD AT ZERO LIFT IN OPEN ANDCLOSED 3-1NCHJETS ANDCORRECTIONS FORJET-BOUNDARY INTERFERENCE, Ray H. Wright and ColemanduP. Donaldson_May 1946 TN 1062 TANKTESTS TODETERMINE THEEFFECT OFVARYING DESIGN PARAMETERS OF PLANING-TAlL HULLS. I - EFFECT OF VARYING LENGTH_ WIDTH_ AND PLAN-FORM TAPER OF AFTERBODY_ John R. Dawson_ Robert Co Walter_ and Elizabeth S. Hay_May 1946 TN i070 A EMPIRICAL EQUATION FORCOEFFICIENT OF HEATTRANSFER TO A FLAT SURFACE FROM A PLANE HEATED-AIR JET DIRECTED TANGENTIALLY TO THE SURFACE_ John Zerbe and JamesSelna_ June 1946 TN 1073 NOTE ONTHETHEOREMS OF BJERKNES ANDCROCCO, Theodore Theodorsen_ May 1946 TN 1075 EFFECTS OF COMPRESSIBILITY ONSECTION CHARACTERISTICS OF AN AIR- FOIL WITHA ROUND-NOSE FRISEAILERON_ Arvo A. Luoma,May 1946 TN 1077 JET-BOUNDARY ANDPLAN-FORM CORRECTIONS FORPARTIAL-SPAN MODELS WITHREFLECTION PLANE_ ENDPLATE_ ORNOENDPLATEIN CLOSED CIRCULAR TUNNEL_ JamesC. Sivells and OwenJ. Deters_ June 1946 TN 1079 PRESSURE DISTRIBUTION OVER A PLUG-TYPE SPOILER-SLOT AILERON ONA TAPERED WING WITHFULL-SPAN SLOTTED FLAPS 3 John G° Lowry and Thomas R. Turner_ June 1946 TN 1081 FLOW OVER A SLENDER BODY OFREVOLUTION AT SUPERSONIC VELOCITIES_ Robert T. Jones and Kenneth Margolis_ August 1946 TN 1083 STALLING OF HELICOPTER BLADES_ F. B. Gustafson and G. C. Myers_ Jr._ June 1946 TN 1096 ONSUPERSONIC ANDPARTIALLY SUPERSONIC FLOWS_ Stefan Bergman_ December1946 TN ii01 TANKTESTS TO DETERMINE THEEFFECT OFVARYING DESIGN PARAMETERS OF PLANING TAlL HULLS. II - EFFECT OF VARYING DEPTH OF STEP_ ANGLE OF AFTERBODY KEELj LENGTH OFAFTERBODY CHINE_ ANDGROSS LOAD,John R. Dawson_ Robert McKann_and Elizabeth S. Hay_July 1946 TN 1107 THIN OBLIQUE AIRFOILSAT SUPERSONIC SPEED_ Robert T. Jones_ Septem- ber 1946 TN 1114 CALCULATION OF SURFACE T_IPERATURES IN STEADY SUPERSONIC FLIGHT 3 GeorgeP. Wood_December1946 TN 1115 AN INVESTIGATION OF THESTABILITYOFTHELAMINAR BOUNDARY LAYER IN A COMPRESSIBLE FLUID_Lester Lees and Chia Chiao Lin_ September TN 1118 EFFECT OF COMPRESSIBILITY AT HIGHSUBSONIC VELOCITIES ONTHE LIFTING FORCE ACTING ONAN ELLIPTICCYLINDER_ Carl Kaplan_ July STANDARD NOMENCLATURE FOR AIRSPEEDS WITH TABLES AND CHARTS FOR USE TN 1120 IN CALCULATION OF AIRSPEED 3 William S. Aiken 3 Jr._ September 1946 TN 1121 HIGH-SPEED INVESTIGATION OF SKIN WRINKLES ON TWO NACA AIRFOILS 3 Harold L. Robinson 3 August 1946 A DISCUSSION OF THE APPLICATION OF THE PRANDTL-GU__UERT METHOD TO TN 1127 SUBSONIC COMPRESSIBLE FLOW OVER A SLENDER BODY OF REVOLUTION 3 Lester Lees_ September 1946 TN 1128 AN INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF A ROTATING AXIAL-FLOW BLADE GRID 3 John R. Weske 3 February 1947 TN 1135 APPLICATION OF THE METHOD OF CHARACTERISTICS FO SUPERSONIC ROTA- TIONAL FLOW 3 Antonio Ferai_ September 1946 TN 1141 AN ANALYSIS OF THE AIRSPEEDS AND NORMAL ACCELERATIONS OF BOEING S-307 AIRPLANES IN COMMERCIAL TRANSPORT OPERATION 3 A. M. Peiser and W. G. Walker 3 September 1946 TN 1142 AN ANALYSIS OF THE AIRSPEEDS AND NORMAL ACCELERATIONS OF DOUGLAS DC-3 AIRPLANES IN COMMERCIAL TRANSPORT OPERATION_ A. M. Peiser 3 September 1946 TN 1143 CHARTS FOR DETERMINING THE CHARACTERISTICS OF SHARP-NOSE AIRFOILS IN TWO-DIMENSIONAL FLOW AT SUPERSONIC SPEEDSj Reese Ivey 3 George W.

Stickle_ and Alberta Schuettler_ January 1947 TN 1152 FLIGHT INVESTIGATION OF THE EFFECT OF A LOCAL CHANGE IN WING CON- TOUR ON CHORDWISE PRESSURE DISTRIBUTION AT HIGH SPEEDS 3 Richard E.

Adams and Norman S. Silsby 3 September 1946 TN 1153 FOAMING VOLUME AND FOAM STABILITY_ Sydney Ross_ February 1947 TN 1154 A COMPARISON OF THE LATERAL MOTIONS CALCULATED FOR TAILLESS AND CONVENTIONAL AIRPLANES_ Charles W. Harper and Arthur L. Jones_ February 1947 TN 1160 THE INFRARED SPECTRA OF SPIROPENTANE METHYLENECYCLOBUTANE AND 2-METHYL-I-BUTENE_ Alden P. Cleaves and Mildred E. Sherrick 3 October TN 1161 EFFECT OF CATALYSTS AND pH ON STRENGTH OF RESIN BONDED PLYWOOD_ G. M. Kline_ F. W. Reinhart 3 R. C. Rinker_ and N. J. DeLollis_ April TN i168 SOME RECENT CONTRIBUTIONS TO THE STUDY OF TRANSITION AND TURBU- LENT BOUNDARY LAYERSj Hugh L. Dryden_ April 1947 TN 1169 THE EFFECT OF GEOMETRIC DIHEDRAL ON THE AERODYNAMIC CHARACTERIS- TICS OF A 40 ° SWEPT-BACK WING OF ASPECT RATIO 33 Bernard Maggin and Robert E. Shanks_ December 1946 TN 1170 ONSUBSONIC COMPRESSIBLE FLOWS BYA METHOD OF CORRESPONDENCE.

I - METHODS FOROBTAINING SUBSONIC CIRCULATORY COMPRESSIBLE FLOWS ABOUT TWO DIMENSIONAL BODIES_ Abe Gelbart_ March 1947 TN 1171 ONSUBSONIC COMPRESSIBLE FLOWS BYA METHOD OF CORRESPONDENCE.

II - APPLICATION OFMETHODS TO STUDIES OFFLOW WITHCIRCULATION ABOUT A CIRCULAR CYLINDER_ Shepard Bartnoff and Abe Gelbart_ April TN 1173 FLIGHTMEASUR_4ENTS OF INTERNAL COCKPIT PRESSURES IN SEVERAL FIGHTER-TYPE AIRPLANES_ Edward C. B. Danforth_ III_ and John P.

Reeder_February 1947 TN 1175 LIFTING-SURFACE-THEORY ASPECT-RATIO CORRECTIONS TO THELIFT AND HINGE-MOMENT PARAMETERS FORFULL-SPAN ELEVATORS ONHORIZONTAL TAlL SURFACES_ Robert S. Swansonand Stewart M. Crandall_ February 1947 TN 1179 NOTES ONTHETHEORETICAL CHARACTERISTICS OF 2-DIMENSIONAL AIR- FOILS_Reese Ivey_ January 1947 TN 1183 THEORETICAL LIFT ANDDRAG OF THINTRIANGULAR WINGS AT SUPERSONIC SPEEDS_ Clinton E. Brown_December1946 TN 1184 THEORY OF GROUND VIBRATIONS OFA TWO-BLADE HELICOPTER ROTOR ON ANISOTROPIC FLEXIBLESUPPORTS_ Robert P. Colemanand Arnold M.

Feingold_ January 1947 TN 1185 APPLICATION OF THEANALOGY BETWEEN WATER FLOW WITHA FREESURFACE AND2-DIMENSIONAL COMPRESSIBLE GAS FLOWjW. JamesOrlin_ NormanJ.

Lindner_ and Jack G. Bitterly_ February 1947 TN 1190 WAKE MEASURI_IENTS BEHIND A WINGSECTION OF A FIGHTER AIRPLANE IN FASTDIVES_De E. Beeler and George Gerard_March 1947 TN 1194 EFFECT OFFINITE SPAN ONTHEAIRLOAD DISTRIBUTION FOROSCILLATING WINGS. I - AERODYNAMIC THEORY OF OSCILLATING WINGS OF FINITE SPAN_ Eric Reissner_ March 1947 TN 1195 EFFECT OF FINITE SPAN ONTHEAIRLOAD DISTRIBUTIONS FOROSCILLATING WINGS. II - METHODS OF CALCULATION ANDEXAMPLES OF APPLICATION_ Eric Reissner and John E. Stevens_ October 1947 TN 1196 INVESTIGATIONS OF EFFECTS OF SURFACE T_PERATURE ANDSINGLE ROUGHNESS ELEMENTS ONBOUNDARY-LAYER TRANSITION_ HansW. Liepmann and Gertrude H. Fila_ April 1947 TN 1200 TENTATIVE TABLES FORTHEPROPERTIES OF THEUPPER ATMOSPHERE_ Calvin R. Warfield_ January 1947 TN 1210 EFFECT OF SLIPSTREAM ROTATION IN PRODUCING ASYMMETRIC FORCES ONA FUSELAGE_ Herbert S. Ribner and Robert MacLachlan_March 1947 TN 1211 THEFLOW ANDFORCE CHARACTERISTICS OF SUPERSONIC AIRFOILSAT HIGH SUBSONIC SPEEDS_ W. F. Lindsey_ Bernard N. Daley_ and Milton D.

Humphreys_ March 1947 TN 1212 EFFECT OF REFLEX CAMBER ONTHEAERODYNAMIC CHARACTERISTICS OFA HIGHLY TAPERED MODERATELY SWEPT-BACK WING AT REYNOLDS NUMBERS UP TO 8_000_000_D. William Conner_March 1947 TN 1215 AN IMPROVED CONTINUOUS INDICATION DEW POINTMETER_ Frank A. Friswol_ Ralph D. Lewis_ and R. Clyde Wheeler_ Jr._ February 1947 TN 1218 EFFECT OF COMPRESSIBILITY AT HIGHSUBSONIC VELOCITIES ONTHE MOMENT ACTING ONAN ELLIPTICCYLINDER, Carl Kalpan_ March 1947 TN 1225 THEFORMATION ANDSTABILITYOF NORMAL SHOCK WAVES IN CHANNEL FLOWS_ Arthur Kantrowitz_ March 1947 TN 1226 THEORETICAL SUPERSONIC LIFT ANDDRAG CHARACTERISTICS OF SYMMETRI- CALWEDGE SHAPE AIRFOIL SECTIONS AS AFFECTED BY SWEEPBACK OUTSIDE THEMACH CONE_ H. Reese Ivey and EdwardN. Bowen_Jr._ March 1947 TN 1227 EXPLORATORY INVESTIGATION OF LAMINAR BOUNDARY-LAYER OSCILLATIONS ONA ROTATING DISK_ Newell H. Smith_ May 1947 TN 1228 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF A 10.7-PERCENT-THICK SYMMETRICAL TAlL SECTION WITHA 0.40 AIRFOIL-CHORD CONTROL SURFACE ANDA 0.20 CONTROL-SURFACE-CHORD TAB_Albert L. Braslow_ June 1947 TN 1231 THESTREAMLINE PATTERN IN THEVICINITY OF AN OBLIQUE AIRFOIL_ Charles E. Watkins_ March 1947 TN 1233 PRELIMINARY ANALYSIS OFNACA MEASUR_IENTS OF ATMOSPHERIC TURBU- LENCE WITHINA THUNDERSTORM - U.S. WEATHER BUREAU THUNDERSTORM PROJECT_ Harold B. Tolefson_ March 1947 TN 1234 EXPERIMENTS ONBUNSEN-BURNER FLAMES FORTURBULENT FLOW_ Lowell M.

Bollinger and David T. Williams_ June 1947 TN 1244 EFFECTS OF THE_EL-WALL BOUNDARY LAYER ONTESTRESULTS OFA WING PROTRUDING FROM A TUNNEL WALL_ Robert A. Mendelsohn and Jose- phine F. Polhamus_April 1947 TN 1252 INTERFERENCE METHOD FOROBTAINING THEPOTENTIAL FLOW PASTAN ARBITRARY CASCADE OF AIRFOILS_S. Katzoff_ Robert S. Finn_ and JamesC. Laurenc% May 1947 TN 1255 THEEFFECT OF COMPRESSIBILITY ONTHEGROWTH OF THELAMINAR BOUNDARY LAYER ONLOW-DRAG WINGS ANDBODIESjH. Julian Allen and Gerald E. Nitzberg_ July 1947 TN 1257 INVESTIGATION OF FREETURBULENT MIXING_HansWolfgang Liepmann and John Laufer_ August 1947 TN 1259 A GRAPHIC METHOD FORINTERPOLATION OF HYDRODYNAMIC CHARACTERIS- TICS OF SPECIFICFLYINGBOATS FROM COLLAPSED RESULTS OF GENERAL TESTS OFFLYINGBOAT-HULL-MODELS_ F. W. S. Locke_ Jr._ January TN 1265 BOUNDARY-INDUCED UPWASH FORYAWED ANDSWEPT-BACK WINGS IN CLOSED CIRCULAR WINDTUNNELS_ Bertram J. Eisenstadt_ May 1947 TN 1266 FLIGHTMEASUREMENTS OF HELICOPTER BLADE MOTION WITHA COMPARISON BETWEEN THEORETICAL ANDEXPERIMENTAL RESULTS_ Garry C. Meyers_ Jr.j April 1947 TN 1267 FLIGHTTESTS OF A HELICOPTER IN AUTOROTATION_ INCLUDING A COMPARISON WITHTHEORY_ Alfred Gessowand Garry C. Myers_ Jr._ April 1947 TN 1272 INTERFERENCE OFWING ANDFUSELAGE FROM TESTS OF 30 COMBINATIONS WITHTRIANGULAR ANDELLIPTICALFUSELAGES IN THENACA VARIABLE- DENSITY TUNNEL_ Albert Sherman_ May 1947 TN 1273 METEOROLOGICAL CONDITIONS ASSOCIATED WITHFLIGHTMEASUREMENTS OF ATMOSPHERIC TURBULENCE_ B. B. Helfand_ June 1947 TN 1275 A LIFTING-SURFACE-THEORY SOLUTION ANDTESTS OFAN ELLIPTIC TAlL SURFACE OF ASPECT RATIO3 WITHA 0.5-CHORD 0.85-SPAN ELEVATOR_ Robert S. Swanson_Stewart M. Crandall_ and Sadie Miller_ May 1947 TN 1276 LOW-SPEED TESTS OF FIVE NACA66-SERIESAIRFOILSHAVING MEAN LINES DESIGNED TOGIVE HIGHCRITICAL MACH NUMBERS_ Albert E.

von Doenhoff_ Louis S. Stivers_ Jr._ and JamesM. O'Connor_ May TN 1283 THELANGLEY TWO-DIMENSIONAL LOW-TURBULENCE PRESSURE TUNNEL, Albert E° von Doenhoff and Frank T. Abbott_ Jr._ May 1947 TN 1285 THEORETICAL MOTIONS OF HYDROFOIL SYSTEMS_ Frederick H. Imlay_ June FLIGHTTESTS OF ANAIRPLANE MODEL WITHA 42° SWEPT-BACK WING IN TN 1287 THELANGLEY FREE-FLIGHT TUNNEL_ Bernard Maggin and Charles V.

Bennett_ May 1947 TN 1289 FULL-SCALE INVESTIGATION OF THEAERODYNAMIC CHARACTERISTICS OFA TYPICALSINGLE-ROTOR HELICOPTER IN FORWARD FLIGHT; Richard C.

Dingeldein and Raymond F. Schaefer_ May 1947 TN 1290 APPRECIATION ANDDETERMINATION OF THEHYDRODYNAMIC QUALITIES OF SEAPLANES, John B. Parkinson_ May 1947 TN 1300 THE EFFECTS OF AERODYNAMIC HEATING AND HEAT TRANSFER ON THE SURFACE TEMPERATURE OF A BODY OF REVOLUTION IN STEADY SUPERSONIC FLIGHT_ Richard Scherrer_ July 1947 TN 1301 A METHOD FOR CALCULATING THE HEAT REQUIRED FOR THE PREVENTION OF FOG FORMATIONS ON THE INSIDE SURFACE OF SINGLE-PANEL BULLET- RESISTING WINDSHIELDS DURING DIVING FLIGHT_ James Selna and John E. Zerbe_ July 1947 TN 1303 A TRANSONIC PROPELLER OF TRIANGULAR PLAN FORM_ Herbert S. Ribnerj May 1947 TN 1305 EFFECT OF LENGTH-BEAM RATIO ON THE AERODYNAMIC CHARACTERISTICS OF FLYING-BOAT HULLS_ Campbell C. Yates and John M. Riebe_ June 1947 TN 1306 AERODYNAMIC CHARACTERISTICS OF THREE PLANING-TAIL FLYING-BOAT HULLS_ Campbell C. Yates and John M. Riebe_ June 1947 TN 1307 EFFECT OF AERODYNAMIC REFINEMENT ON THE AERODYNAMIC CHARACTERISTICS OF A FLYING-BOAT HULL_ John Riebe and Rodger L. Naeseth_ June 1947 TN 1308 ISOLATED AND CASCADE AIRFOILS WITH PRESCRIBED VELOCITY DISTRIBU_ TION_ Arthur W. Goldstein and Meyer Jerison_ May 1947 TN 1311 FRICTION COEFFICIENTS IN A VANELESS DIFFUSER_ W. Byron Brown_ May TN 1315 FREE-FALL AND PARACHUTE DESCENTS IN THE STANDARD ATMOSPHERE_ A. P.

Webster_ June 1947 TN 1316 THEORETICAL AERODYNAMIC COEFFICIENTS OF TWO-DIMENSIONAL SUPERSONIC BIPLANESj W. E. Moeckel_ June 1947 TN 1319 CALCULATIONS OF THE SUPERSONIC WAVE DRAG OF NON LIFTING WINGS WITH ARBITRARY SWEEPBACK AND ASPECT RATIO WINGS SWEPT BEHIND THE MACH LINES_ Sidney M. Harmon and Margaret D. Swanson_ May 1947 TN 1326 AIRFOIL IN SINUSOIDAL MOTION IN A PULSATING STREAM_ J. Mayo Green- berg_ June 1947 TN 1328 CALCULATION OF COMPRESSIBLE FLOWS PAST AERODYNAMIC SHAPES BY USE OF THE STREAMLINE CURVATUREj W. Perl_ June 1947 TN 1331 EMPIRICAL METHOD FOR FREQUENCY COMPENSATION OF THE HOT-WIRE ANEMOMETER_ Raymond A. Runyan and Robert J. Jeffries_ June 1947 TN 1340 SUBSONIC FLOW OVER THIN OBLIQUE AIRFOILS AT ZERO LIFT_ Robert T. Jones_ June 1947 TN 1350 ESTIMATED LIFT-DRAG RATIOS AT SUPERSONIC SPEED_ Robert T. Jones_ July 1947 TN 1353 EFFECT OF DISTANCE ON AIRPLANE NOISE_ Arthur A. Regier_ June 1947 TN 1356 AN INVESTIGATION OF EFFECTS OF REVERSED-TYPE LONGITUDINAL STEPS ON RESISTANCE AND SPRAY CHARACTERISTICS OF A FLYING-BOAT HULL, Arthur W. Carter_ Eugene P. Clement, and Alvin H. Morewitz, July 1947 TN 1371 CONSIDERATIONS OF THE TOTAL DRAG OF SUPERSONIC AIRFOIL SECTIONS, H. Reese Ivey and E. Bernard Klunker, July 1947 TN 1372 SOME CONSIDERATIONS ON AN AIRFOIL IN AN OSCILLATING STREAM_ J. Mayo Greenberg_ August 1947 TN 1373 CHARTS FOR DETERMINATION OF SUPERSONIC AIR FLOW AGAINST INCLINED PLANES AND AXIALLY SYMMETRIC CONES_ W. E. Moeckel and J. F. Connors_ July 1947 TN 1376 COMPARISON OF THEORETICAL AND EXPERIMENTAL LIFT AND PRESSURE DIS- TRIBUTIONS ON AIRFOILS IN CASCADE, S. Katzoff, Harriet E. Bogdonoff, and Howard Boyet, July 1947 TN 1378 PRELIMINARY INVESTIGATION AT LOW SPEED OF DOWNWASH CHARACTERISTICS OF SMALL-SCALE SWEPTBACK WINGS_ Paul E. Purser, M. Leroy Spearman_ and William R. Bates_ July 1947 TN 1381 NUMERICAL EVALUATION OF MASS-FLOW COFJ_FICIENT AND ASSOCIATED PARAM- ETERS FROM WAKE-SURVEY EQUATIONS, No[man F. Smith_ July 1947 DISTRIBUTION OF WAVE DRAG AND LIFT IN THE VICINITY OF WING TIPS AT TN 1382 SUPERSONIC SPEEDS_ John C. Eward_ July 1947 TN 1383 THEORETICAL STUDY OF THE AIR FORCES ON AN OSCILLATING OR STEADY THIN WING IN A SUPERSONIC MAIN STREAM, I. E. Garrick and S. I.

Rubinow_ July 1947 TN 1384 A REVIEW OF BOUNDARY-LAYER LITERATURE, Neal Tetervin_ July 1947 TN 1387 A PRELIMINARY CORRELATION OF THE BEHAVIOR OF WATER RUDDERS ON SEA- PLANES AND FLYING BOATS, F. W. S. Locke_ Jr._ August 1947 TN 1390 EFFECT OF COMPRESSIBILITY ON THE DISTRIBUTION OF PRESSURES OVER A TAPERED WING OF NACA 230-SERIES AIRFOIL SECTIONS_ E. O. Pearson_ Jr._ July 1947 TN 1396 HIGH SPEED TESTS OF AN AIRFOIL SECTION CAMBERED TO HAVE CRITICAL MACH NUMBERS HIGHER THAN THOSE ATTAINABLE WITH A UNIFORM-LOAD MEAN LINE_ Donald J. Graham_ August 1947 TN 1401 INTRODUCTION TO THE PROBLEM OF ROCKET-POWERED AIRCRAFT PERFORMANCE, H. Reese Ivey_ Edward N. Bowen 3 Jr._ and Lester F. Ornby_ December TN 1403 WIND TUNNEL INVESTIGATION OF THE EFFECT OF TAB BALANCE ON TAB AND CONTROL-SURFACE CHARACTERISTICS_ Jack D. Brewer and M. J. Queijo_ August 1947 TN 1405 THE OPTICAL SYSTEM OF THE NACA 400_000-FRAME-PER-SECOND MOTION- PICTURE CAMERA_ Cearcy D. Miller_ August 1947 TN 1406 HIGH-SPEED WIND-TUNNEL TESTS OF AN NACA 16-009 AIRFOIL HAVING A 32.9-PERCENT-CHORD FLAP WITH OVERHANG 20.7 PERCENT OF THE FLAP CHORD; David B. Stevenson and Robert W. Byrne_ August 1947 TN 1412 VOLTERRA'S SOLUTION OF THE WAVE EQUATION AS APPLIED TO THREE- DIMENSIONAL SUPERSONIC AIRFOIL PROBLEMS_ Max. A. Heaslet_ Harvard Lomax_ and Arthur L. Jones_ September 1947 TN 1417 HIGH-SPEED WIND-TUNNEL TESTS OF AN NACA 0009-64 AIRFOIL HAVING A 33.4-PERCENT-CHORD FLAP WITH AN OVERHANG 20.1 PERCENT OF THE FLAP CHORD_ David B. Stevenson and Alfred A. Adlerj September 1947 TN 1419 CHARTS FOR THE ANALYSIS OF ONE-DIMENSIONAL STEADY COMPRESSIBLE FLOW_ L. Richard Turner_ Albert N. Addie_ and Richard H. Zimmerman_ January 1948 TN 1420 AN APPLICATION OF LIFTING-SURFACE THEORY TO THE PREDICTION OF ANGLE-OF-ATTACK HINGE MOMENT PARAMETERS FOR ASPECT RATIO 4.5 WING_ Arthur L. Jones_ Mildred G. Flanagan_ and Loma Sluder_ September TN 1423 THE STABILITY DERIVATIVES OF LOW-ASPECT-RATIO TRIANGULAR WINGS AT SUBSONIC AND SUPERSONIC SPEEDS_ Herbert S. Ribner_ September 1947 TN 1428 NOTES AND TABLES FOR USE IN TEE ANALYSIS OF SUPERSONIC FLOW_ The Staff of the Ames I- by 3-Foot Supersonic Wind Tunnel Section_ December 1947 TN 1429 THE EFFECT OF YAWING THIN POINTED WINGS AT SUPERSONIC SPEEDS_ John C. Eward_ September 1947 TN 1430 A THEORETICAL STUDY OF THE DYNAMIC PROPERTIES OF HELICOPTER BLADE SYSTEMj H. Reissner and M. Morduchow, November 1948 TN 1442 FRICTION AT HIGH SLIDING VELOCITIES_ Robert L. Johnson; Max A.

Swikert_ and Edmond E. Bisson_ October 1947 TN 1445 TWO-DIMENSIONAL IRROTATIONAL TRANSONIC FLOWS OF A COMPRESSIBLE FLUIDj Yung-Huai Kuo_ June 1948 TN 1448 SUPERSONIC WAVE DRAG OF SWEPTBACK TAPERED WINGS AT ZERO LIFT_ Kenneth Margolis_ October 1947 THEORETICAL SUPERSONIC WAVE DRAG OFUNTAPERED SWEPTBACK AND TN 1449 RECTANGULAR WINGS AT ZERO LIFT_ Sidney M. Harmon_October 1947 TN 1457 OVERBALANCING IN RESIDUAL-LIQUIDATION COMPUTATIONS_ Alfred S. Niles_ February 1949 TN 1460 INFLUENCE OF CRYSTAL PLANE ANDSURROUNDING ATMOSPHERE ONCH_ICAL ACTIVITIESOF SINGLECRYSTALS OFMETALS_ Allan T. Gwarthmey_ Henry Leidheiser_ Jr._ and G. Pedro Smith_ June 1948 TN 1471 EXPERIMENTAL INVESTIGATION OFVELOCITY DISTRIBUTIONS DOWNSTREAM OF SINGLE DUCTBENDS_ John R. Weske_January 1948 TN 1473 HIGH-SPEED WIND-TUNNEL INVESTIGATION OF HIGHLIFT ANDAILERON- CONTROL CHARACTERISTICS OF ANNACA65-210 SEMISPAN WING_ Jack Fischel and Leslie E. Schneiter_ November1947 WIND-TUNNEL INVESTIGATION OF EFFECTS OF UNSYMMETRICAL HORIZONTAL- TN 1474 TAIL ARRANGI_MENTS ONPOWER-ON STATICLONGITUDINAL STABILITYOF A SINGLE-ENGINE AIRPLANE MODEL_ Paul E. Purser and Margaret F. Spear_ October 1947 TN 1477 GENERALIZED PERFORMANCE COMPARISON OF LARGE CONVENTIONAL_ TAIL- BOOM_ ANDTAILLESS AIRPLANESp HermanO. Ankenbruck and Marion O. McKinney_Jr._ October 1947 TN 1479 BOUNDARY-LAYER MOMENTUM EQUATIONS FORTHREE-DIMENSIONAL FLOW_ Neal Tetervin_ October 1947 TN 1487 EFFECT OF ASPECT RATIOANDTAPER ONTHEPRESSURE DRAG AT SUPER- SONICSPEEDS OF UNSWEPT WINGS AT ZERO LIFT_ Jack N. Nielsen_ November1947 TN 1496 INVESTIGATION OF THEFUSELAGE INTERFERENCE ONA PITOT-STATIC TUBE EXTENDING FORWARD FROM THENOSE OF THEFUSELAGE_ William Letko_ December1947 THEUSEOF SOURCE-SINK ANDDOUBLET DISTRIBUTIONS EXTENDED TO THE TN 1515 SOLUTION OF ARBITRARY BOUNDARY VALUE PROBLEMS IN SUPERSONIC FLOW_ Max. A. Heaslet and Harvard Lomax_January 1948 TN 1516 A GENERALIZED THEORETICAL ANDEXPERIMENTAL INVESTIGATION OF THE MOTIONS ANDHYDRODYNAMIC LOADS EXPERIENCED BYV-BOTTOM SEAPLANES DURING STEP-LANDING IMPACTS_ Benjamine Milwitzky_ February 1948 TN 1521 FULL-SCALE INVESTIGATION OF THEBLADE MOTION OF THEPV-2 HELI- COPTER ROTOR_ EugeneMigotsky_ March 1948 TN 1524 TAKE-OFF PERFORMANCE OFLIGHTTWIN-FLOAT SEAPLANES_ John B. Parkin- son_ February 1948 TN 1527 ONSIMILARITYRULES FORTRANSONIC FLOWS_ Carl Kaplan_ January 1948 TN 1538 ANALYSIS OFACCURACY OF GAS-FILLED BELLOWS FORSENSING GASDENSITY_ EdwardW. Otto_ February 1948 TN 1542 EFFECT OF ROTOR-BLADE TWISTANDPLAN-FORM TAPER ONHELICOPTER HOVERING PERFORMANCE_ Alfred Gessow_ February 1948 TN 1543 EFFECT OF CHORDWISE LOCATION OF MAXIMUM THICKNESS ONTHESUPER- SONIC WAVE DRAG OF SWEPTBACK WINGS_ Kenneth Margolis_ March 1948 TN 1546 AERODYNAMIC CHARACTERISTICS OF 24 NACA16-SERIESAIRFOILSAT MACH NUMBERS BETWEEN 0.3 AND0.8j W. F. Lindsey_ D. B. Stevenson_ and Bernard N. Daley_ September 1948 TN 1547 TANKTESTS OFTHREE TYPES OFAFTERBODIES ONA FLYING-BOAT MODEL WITHA BASICHULLLENGTH-BEAM RATIOOF 10.0j Charlie C. Garrison and EugeneP. Clement s March 1948 TN 1549 EFFECT OFYAW AT SUPERSONIC SPEEDS ONTHEORETICAL AERODYNAMIC COEFFICIENTS OF THIN POINTED WINGS WITHSEVERAL TYPES OF TRAILING EDGE_ W. E. Moeckel_ March 1948 TN 1555 THETHEORETICAL LIFT OFFLAT SWEPT-BACK WINGS AT SUPERSONIC SPEEDS_ Doris Cohen s March 1948 TN 1570 HYDRODYNAMIC QUALITIES OFA HYPOTHETICAL FLYINGBOAT WITHA LOW- DRAG HULLHAVING A LENGTH-BEAM RATIOOF 15_ Arthur W. Carter and Marvin I. Haar_ April 1948 TN 1571 EFFECT OF AFTERBODY LENGTH ANDKEELANGLE ONMINIMUM DEPTH OF STEPFORLANDING STABILITYANDONTAKE-0FFSTABILITYOF A FLY- ING BOAT_ Roland E. Olson and NormanS. Lands September 1948 TN 1576 WIND-TUNNEL INVESTIGATION OF A SYSTEMATIC SERIES OFMODIFICATIONS TOA FLYING-BOAT HULL s Felicien Fo Fullmer_ Jr, s May 1948 TN 1577 NOTEONSIMILARITYCONDITIONS FORFLOWS WITHHEATTRANSFER_ Albert E. yon Doenhoff_ April 1948 TN 1585 THEORETICAL DISTRIBUTION OF LIFT ONTHINWINGS AT SUPERSONIC SPEEDS (AN EXTENSION)s John C. Eward s May 1948 TN 1592 COMPRESSIBLE FLOW TABLES FORAIR_ Marie A. Burcherj August 1948 TN 1595 ANALYSIS OFFLIGHT-PERFORMANCE MEASUR_IENTS ONA TWISTED_ PLYWOOD- COVERED HELICOPTER ROTOR IN VARIOUS FLIGHTCONDITIONS_ F. B.

Gustafson and Alfred Gessow s June 1948 TN 1596 AN INVESTIGATION OF THESECTION CHARACTERISTICS OF PLAINUN- SEALED AILERONS ONAN NACA 66_ 1-115 AIRFOIL SECTION IN THE LANGLEY 8-FOOTHIGH-SPEED TUNNEL_ Arvo A. Luoma_January 1949 TN 1600 CHARACTERISTICS OF THINTRIANGULAR WINGS WITHTRIANGULAR-TIP CONTROL SURFACES AT SUPERSONIC SPEEDS WITHMACH LINES BEHIND THELEADING EDGE_ Warren A. Tucker_ May 1948 TN 1601 CHARACTERISTICS OF THINTRIANGULAR WINGS WITHCONSTANT-CHORD FULL- SPAN CONTROL SURFACES AT SUPERSONIC SPEEDS_ Warren A. Tucker_ July TN 1604 STANDARD SYMBOLS FORHELICOPTERS, Alfred Gessow,June 1948 TN 1605 ACCURACY OF AIRSPEED MEASUREMENTS _ FLIGHTCALIBRATION PROCEDURES_ Wilber B. Huston_ June 1948 TN 1613 A METHOD FORDETERMINING THEAERODYNAMIC CHARACTERISTICS OF TWO- ANDTHREE-DIMENSIONAL SHAPES AT HYPERSONIC SPEEDS_ H. Reese Ivey_ E. Bernard Klunker_ Edward N. Bowen_July 1948 TN 1615 INVESTIGATION OF THEPENETRATION OF ANAIR JET DIRECTED PERPEN- DICULARLY TOAN AIR STREAM_ Edmund E. Callaghan and Robert S.

Ruggeri_ June 1948 TN 1620 THECALCULATION OF DOWNWASH BEHIND SUPERSONIC WINGS WITHAN APPLI- CATION TO TRIANGULAR PLANFORMS_ Max. A. Heaslet and Harvard Lomax_ June 1948 TN 1621 TWO-DIMENSIONAL UNSTEADY LIFT PROBLEM IN SUPERSONIC FLIGHT,Max.

A. Heaslet and Harvard Lomax_June 1948 TN 1622 ANALYSIS ANDPRELIMINARY DESIGN OF AN OPTICAL INSTRUMENT FORTHE MEASUREMENT OF DROP SIZE ANDFREE-WATER CONTENT OF CLOUDS_ Willem V. R. Malkus_ Richard H. Bishop_ and Robert O. Briggs_ June 1948 TN 1623 SOME FUNDAMENTAL SIMILARITIESBETWEEN BOUNDARY-LAYER FLOW AT TRANSONIC ANDLOWSPEEDS_ Gerald E. Nitzberg and Steward Crandall_ June 1948 TN 1630 A GENERALIZED THEORETICAL INVESTIGATION OF THEHYDRODYNAMIC PITCH- ING MOMENTS EXPERIENCED BYV-BOTTOM SEAPLANES DURING STEP-LANDING IMPACTS ANDCOMPARISONS WITHEXPERIMENTS_ Benjamine Milwitzky_ June AN EVALUATION OF THECHARACTERISTICS OF A i0-PERCENT-THICK NACA TN 1633 66-SERIESAIRFOIL SECTION WITHA SPECIAL MEAN-CAMBER LINE DESIGNED TOPRODUCE A HIGHCRITICALMACH NUMBER_ Laurence K. Loftin_ Jr._ and Kenneth S. Cohen_July 1948 TN 1638 EXPERIMENTAL INVESTIGATION OF THEJET-BOUNDARY CONSTRUCTION CORRECTION FOR A MODEL SPANNING A CLOSED CIRCULAR TUNNELj M. Tucker and M. D. Rousso_ June 1948 TN 16'39 INVESTIGATION OF SOME FACTORS AFFECTING COMPARISONS OF WIND-TUNNEL AND FLIGHT MEASUREMENTS OF MAXIMUM LIFT COEFFICIENTS FOR A FIGHTER- TYPE AIRPLANE_ Don D. Davis_ Jr._ and Harold H. Sweberg_ June 1948 TN 1642 VELOCITY DISTRIBUTIONS ON SYMMETRICAL AIRFOILS IN CLOSED TUNNELS BY CONFORMAL MAPPING_ W. Perl and H. E. Moses_ June 1948 TN 1644 LAMINAR FLOW OF A SLIGHTLY VISCOUS INCOMPRESSIVLE FLUID THAT ISSUES FROM A SLIT AND PASSES OVER A FLAT PLATE_ Neal Tetervin_ June 1948 TN 1646 LOW-SPEED WIND-TUNNEL INVESTIGATION OF VARIOUS PLAIN-SPOILER CONFIGURATIONS FOR LATERAL CONTROL ON A 42 ° SWEPTBACK WING, Leslie E. Schneiter and James M. Watson_ June 1948 TN 1657 EFFECTS OF COMPRESSIBILITY ON THE FLOW PAST THICK AIRFOIL SECTIONS_ Bernard N. Daley and Milton D. Humphreys_ July 1948 TN 1660 CHARACTERISTICS OF THIN TRIANGULAR WINGS WITH CONSTANT-CHORD PARTIAL-SPAN CONTROL SURFACES AT SUPERSONIC SPEEDS_ Warren A.

Tucker and Robert L. Nelson_ July 1948 TN 1662 AERODYNAMIC PROPERTIES OF SLENDER WING-BODY COMBINATIONS AT SUB- SONIC_ TRANSONIC_ AND SUPERSONIC SPEEDS_ John R. Spreiter_ July TN 1663 HIGH-SPEED WIND-TUNNEL INVESTIGATION OF AN NACA 65-210 SEMI- SPAN WING EQUIPPED WITH PLUG AND RETRACTABLE AILERONS AND A FULL- SPAN SLOTTED FLAP_ Jack Fischel and Leslie E. Schneiter_ July 1948 TN 1664 A DEVICE FOR MEASURING SONIC VELOCITY AND COMPRESSOR MACHNUMBER_ Paul W. Huber and Arthur Kantrowitz_ July 1948 TN 1665 CHARACTERISTICS OF LOW-ASPECT-RATIO WINGS AT SUPERCRITICAL MACH NUMBERS_ John Stack and W. F. Lindsey_ August 1948 1666 FLIGHT INVESTIGATION OF EFFECTS OF ROTOR-BLADE TWIST ON HELICOPTER PERFORMANCE IN THE HIGH SPEED AND VERTICAL-AUTOROTATIVE-DESCENT CONDITIONS_ Alfred Gessow_ August 1948 TN 1672 SUPERSONIC WAVE DRAG OF NONLIFTING SWEPT BACK TAPERED WINGS WITH MACH LINES BEHIND THE LINE OF MAXIMUM THICKNESS_ Kenneth Margolis_ August 1948 TN 1673 TABLES AND CHARTS OF FLOW PARAMETERS ACROSS OBLIQUE SHOCKS_ Mary M.

Neice_ August 1948 TN 1675 TEMPERATURE GRADIENTS IN THE WING OF A HIGH-SPEED AIRPLANE DURING DIVES FROM HIGH ALTITUDES_ Thorval Tendeland and Bernard A. Schlaff_ July 1948 TN 1748 CALCULATION OF TUNNEL-INDUCED UPWASH VELOCITIES FORSWEPT AND YAWED WINGS_ S. Katzoff and Margery E. Hannah_November1948 TN 1752 JET-BOUNDARY-INDUCED-UPWASH VELOCITIES FORSWEPT REFLECTION PLANE MODELS MOUNTED VERTICALLY IN 7- BY 10-FOOT_ CLOSED_ RECTANGULAR WINDTUNNELS_ Edward C. Polhamus_November1948 TN 1754 AN ANALYSIS OF THEAIRSPEEDS ANDNORMAL ACCELERATIONS OF DOUGLAS DC-2 AIRPLANES IN COMMERCIAL TRANSPORT OPERATION_ Walter G. Walker_ November1948 TN 1755 THEDESIGN OF LOW TURBULENCE WINDTUNNELS_ HughLo Dryden and Ira H. Abbott_ November1948 TN 1759 THEEFFECTS OF COMPRESSIBILITY ONNORMAL-FORCE_ PRESSURE_ ANDLOAD CHARACTERISTICS OFA TAPERED WING OFNACA66-SERIESAIRFOIL SECTIONS WITHSPLIT FLAPS# F. E. West_ Jr._ and J. M. Hallissy_ Jr._ December TN 1767 THEAPPLICATION OF GREEN'S THEOREM TO THESOLUTION OF BOUNDARY- VALUE PROBLEMS IN LINEARIZED SUPERSONIC WING THEORY 3 Max. A.

Heaslet and Harvard Lomax_April 1949 TN 1771 THEDEVELOPMENT OF CAMBERED AIRFOIL SECTIONS HAVING FAVORABLE LIFT CHARACTERISTICS AT SUPERCRITICALMACH NUMBERS_ Donald J. Graham_ December1948 TN 1780 CHARTS FORTHECONICAL PARTOF THEDOWNWASH FIELD OF SWEPT WINGS AT SUPERSONIC SPEEDS_ Jack N. Neilsen and EdwardW. Perkins# December1948 TN 1782 EFFECT OF HULLLENGTH-BEAM RATIOONTHEHYDRODYNAMIC CHARACTERISTICS OFFLYINGBOATS IN WAVES_ Arthur W. Carter_ January 1949 TN 1783 AN ANALYSIS OF THEAIRSPEEDS ANDNORMAL ACCELERATIONS OF BOEING B-247 ANDB-247DAIRPLANES IN COMMERCIAL TRANSPORT OPERATION: Walter G. Walker and Ivan K. Hadlock_ December1948 TN 1788 FLIGHTTESTS OF AN APPARATUS FORVARYING DIHEDRAL EFFECT IN FLIGHT_ William M. Kauffman_ Allan Smith_ C. J. Liddell_ Jr._ and G. E.

Copper_ December1948 TN 1792 STUDY BYTHEPRANDTL-GLAUERT METHOD OF COMPRESSIBILITY EFFECTS AND CRITICALMACH NUMBER FORELLIPSOIDS OF VARIOUS ASPECT RATIOS AND THICKNESS RATIO_Robert V. Hess and Clifford S. Gardner_ January TN 1796 THEORETICAL ANALYSIS OF OSCILLATIONS OF A TOWED CABLE_ William H.

Phillips_ January 1949 TN 1797 A STUDY OF STALLPHENOMENA ONA 45° SWEPT-FORWARD WING_ Gerald M. McCormack and Woodrow L. Cook_ January 1949 TN 1800 LAMINAR MIXINGOFA COMPRESSIBLE FLUID_Dean R. Chapman_ February TN 1803 DOWNWASH IN VERTICAL ANDHORIZONTAL PLANES OF SYMMETRY BEHIND A TRIANGULAR WINGIN SUPERSONIC FLOW_ Harvard Lomaxand LomaSluder_ January 1949 TN 1804 EFFECT OF LONGITUDINAL STEPS ONSKIPPING CHARACTERISTICS OF PB2Y-6 FLYINGBOAT_ R. B. Clark and W. T. Sparrow_ January 1949 TN 1805 REMARKS CONCERNING THEBEHAVIOR OF THELAMINAR BOUNDARY LAYERIN COMPRESSIBLE FLOWS_ Neal Tetervin_ January 1949 TN 1808 METHOD FOREVALUATING FROM SHADOW ORSCHLIEREN PHOTOGRAPHS THE PRESSURE DRAG IN TWO-DIMENSIONAL ORAXIALLYSYMMETRICAL FLOW PHENOMENA WITHDETACHED SHOCK_ Antonio Ferri_ February 1949 TN 1809 THEMETHOD OF CHARACTERISTICS FORTHEDETERMINATION OF SUPERSONIC FLOW OVER BODIES OF REVOLUTION AT SMALL ANGLES OF ATTACK_ Antonio Ferri_ February 1949 TN 1812 THEAPPLICATION OF AIRFOILSTUDIES TO HELICOPTER BLADE DESIGN_ F. B. Gustafson_ February 1949 TN 1813 A STUDY OFFLOW CHANGES ASSOCIATED WITHAIRFOIL SECTION DRAG RISE AT SUPERCRITICAL SPEEDS_ Gerald E. Nitzberg and Stewart Crandall_ February 1949 TN 1815 ONCOMPRESSIBILITY CORRECTIONS FORSUBSONIC FLOW OVER BODIES OF REVOLUTION_ Eric Reissner_ February 1949 TN 1816 TRIANGULAR WINGS TWISTED ANDCAMBERED TO SUPPORT SPECIFIED DIS- TRIBUTION OF LIFT AT SUPERSONIC SPEEDS_ Barrett S. Baldwin_ Jr._ February 1949 TN 1819 THERESPONSE OF PRESSURE MEASURING SYSTEMS TOOXCILLATING PRES- SURES_ Israel Taback_February 1949 TN 1821 AMBIENT PRESSURE DETERMINATION AT HIGRALTITUDES BYUSEOF FREE- MOLECULE THEORY_ Bernard Wienerj March 1949 TN 1824 LINEARIZED COMPRESSIBLE-FLOW THEORY FORSONIC FLIGHTSPEEDS_ Max. A. Heaslet_ Harvard Lomax_and John R. Spreiter_ March 1949 TN 1826 LINEARTHEORY OF BOUNDARY EFFECTS IN OPEN WINDTUNNELS WITH FINITE JET LENGTH_ S. Katzoff_ Clifford S. Gardner_ Leo Diesendruck3 and Bertram J. Eisenstadt 3 March 1949 TN 1828 EFFECT OF FOREBODY WARP ON THE HYDRODYNAMIC QUALITIES OF A HYPOTHETICAL FLYING BOAT HAVING A HULL LENGTH-BEAM RATIO OF 15_ Arthur W. Carter and Irving Weinstein_ March 1949 TN 1849 USE OF CHARACTERISTIC SURFACES FOR UNSYMMETRICAL SUPERSONIC FLOW PROBLEMS_ W. E. Moeckel_ March 1949 TN 1857 INVESTIGATION WITH AN INTERFEROMETER OF THE TURBULENT MIXING OF A FREE SUPERSONIC JET_ Paul B. Gooderum_ George P. Wood_ and Maurice J. Brevoort_ April 1949 TN 1858 A REVIEW OF ANALYTICAL METHODS FOR THE TREATMENT OF FLOWS WITH DETACHED SHOCKS_ Adolf Busemann_ April 1949 TN 1861 ONE DIMENSIONAL FLOWS OF AN IMPERFECT DIATOMIC GAS 3 A. J. Eggers_ Jr._ April 1949 TN 1864 EXTENDED APPLICATIONS OF THE HOT-WIRE ANEMOMETER_ Stanley Corrsin_ April 1949 TN 1865 FURTHER EXPERIMENTS ON THE FLOW AND HEAT TRANSFER IN A HEATED TURBULENT AIR JET_ Stanley Corrsin and Mahinder S. Uberoi_ April TN 1873 SUBSONIC TWO-DIMENSIONAL-FLOW CONDITIONS NEAR AN AIRFOIL DETERMINED BY STATIC PRESSURES MEASURED AT THE TUNNEL WALL_ Bernard N. Daley and Lillian E. Hanna_ April 1949 TN 1875 ON TW0-DIMENSIONAL SUPERSONIC FLOWS_ Stefan Bergman_ May 1949 TN 1877 EFFECTS OF COMPRESSIBILITY ON LIFT AND LOAD CHARACTERISTICS OF A TAPERED WIN_ OF NACA 64-210 SECTIONS UP TO A MACH NUMBER OF 0.60_ F. E. West_ Jr._ and T. Himka_ May 1949 TN 1878 STUDY OF UNSTEADY FLOW DISTURBANCES OF LARGE AND SMALL AMPLITUDES MOVING THROUGH SUPERSONIC OR SUBSONIC STEADY FLOWS_ Robert V. Hess_ May 1949 TN 1884 NOTE ON THE ACCURACY OF A METHOD FOR RAPIDLY CALCULATING THE IN- CR_ENTS IN VELOCITY ABOUT AN AIRFOIL DUE TO ANGLE OF ATTACK_ Laurence K. Loftin_ Jr._ June 1949 TN 1885 DESIGN AND CALIBRATION OF A TOTAL TEMPERATURE PROBE FOR USE AT SUPERSONIC SPEEDS_ David L. Goldstein and Richard Scherrer_ May TN 1894 BOUNDARY-LAYER AND STALLING CHARACTERISTICS OF THE NACA 63-009 AIRFOIL SECTION_ Donald E. Gault_ June 1949 TN 1895 EFFECT OF ASPECT RATIO ON UNDAMPED TORSIONAL OSCILLATIONS OF A THIN RECTANGULAR WING IN SUPERSONIC FLOW_ Charles E. Watkins_ June IMPROVEMENT OFACCURACY OF BALANCE-PRESSURES INDICATORS AND TN 1896 DEVELOPMENT OFAN INDICATOR CALIBRATING MACHINE_ James C. Liven- good_ June 1949 AERODYNAMIC PROPERTIES OF CRUCIFORM-WINGAND BODY COMBINATIONS AT TN 1897 SUBSONIC_ TRANSONICj ANDSUPERSONIC SPEEDS_ John R. Spreiter_ June VELOCITY DISTRIBUTIONS ONARBITRARY AIRFOILSIN CLOSED TUNNELS BY TN 1899 CONFORMAL MAPPING_ H. E. Moses_June 1949 TN 1900 PRELIMINARY INVESTIGATION OF THEUSEOFAFTERGLOW FORVISUAL- IZING LOW-DENSITY COMPRESSIBLE FLOWS_ ThomasW. Williams and JamesM. Benson_June 1949 TN 1903 EXPERIMENTAL INVESTIGATION OFMOVING PRESSURE DISTURBANCES AND SHOCK WAVES ANDCORRELATION WITHONE-DIMENSIONAL UNSTEADY-FLOW THEORY_ Paul W. Huber_ Cliff E. Fitton_ Jr._ and F. Delpino_ July TN 1913 METHOD OF DESIGNING AIRFOILSWITHPRESCRIBED VELOCITY DISTRIBU- TIONSIN COMPRESSIBLE POTENTIAL FLOWS_ GeorgeR. Costello_ August TN 1916 THEEFFECTS OF SIDESLIP_ASPECT RATIO_ANDMACH NUMBER ONTHELIFT ANDPITCHING MOMENT OF TRIANGULAR_ TRAPEZOIDAL_ ANDRELATED PLAN FORMS IN SUPERSONIC FLOW_ Arthur L. Jones_ Robert M. Sorenson_ and Elizabeth E. Lindler_ August 1949 TN 1919 ANALYTICAL METHOD FORDETERMINING TRANSMISSION ANDABSORPTION OF TIME-DEPENDENT RADIATION THROUGH THICKABSORBERS. I - RADIO- ACTIVITYOFABSORBER_ TIME-DEPENDENT_ G. Allen_ August 1949 TN 1921 APPROXIMATE METHOD FORPREDICTING FORM ANDLOCATION OF DETACHED SHOCK WAVES AHEAD OF PLANE ORAXIALLYSYMMETRIC BODIES_ W. E.

Moeckel_ July 1949 TN 1922 TWO-DIMENSIONAL INVESTIGATION OF FIVE RELATED NACA AIRFOIL SECTIONS DESIGNED FORROTATING-WING AIRCRAFT_ Raymond F. Schaefer_ Laurence K. Loftin_ Jr._ Elmer A. Horton_ July 1949 TN 1925 LINE-VORTEX THEORY FORCALCULATIONS OF SUPERSONIC DOWNWASH_ Harold Mirels and Rudolph C. Haefeli_ August 1949 TN 1929 ONTHESTABILITYOF THEFREELAMINAR BOUNDARY LAYERBETWEEN PARALLEL STREAMS_ Martin Lessen_ August 1949 TN 1930 AN ANALYSIS OF THEEFFECT OF LIFT-DRAGRATIO ANDSTALLING SPEED ON LANDING-FLARE CHARACTERISTICS_ J. Calvin Lovell and Stanley Lip- son_ September 1949 TN 1931 DESIGN METHOD FORTWO-DIMENSIONAL CHANNELS FORCOMPRESSIBLE FLOW WITHAPPLICATION TO HIGH-SOLIDITY CASCADES_ SumnerAlpert_ August TN 1932 TWO-DIMENSIONAL COMPRESSIBLE FLOW IN CENTRIFUGAL COMPRESSORS WITH STRAIGHT BLADES_ John D. Stanitz and Gaylord O. Ellis 3 August 1949 TN 1933 INVESTIGATION OF SPOILER AILERONS FORUSEAS SPEED BRAKES OR GLIDE-PATH CONTROLS ONTWO NACA65-SERIES WINGS EQUIPPED WITH FULL-SPAN SLOTTED FLAPS_ Jack Fischel and JamesM. Watson_August TN 1934 LOW-SPEED EXPERIMENTAL INVESTIGATION OF A THIN_FAIRED_ DOUBLE- WEDGE AIRFOIL SECTION WITHNOSE ANDTRAILING-EDGE FLAPS_ Leonard M. Rose and John M. Altman_ August 1949 TN 1936 A FLIGHTDETERMINATION OF THETOLERABLE RANGE OF EFFECTIVE DIHEDRAL ONA CONVENTIONAL FIGHTER AIRPLANE_ C. J. Liddell_ Jr._ R. D.

VanDyke_Jr._ and D. R. Heinle_ August 1949 TN 1939 THEEFFECTS OF AERODYNAMIC BRAKES UPON THESPEED CHARACTERISTICS OF AIRPLANES_ Jack D. Stephenson_September 1949 TN 1941 ATTAINABLE CIRCULATION OFAIRFOILSIN CASCADE_ Arthur W. Goldstein and Arthur Mager_ September 1949 TN 1942 THEEFFECT OFWALL FRICTION ONTHESTRENGTH OF SHOCK WAVES IN TUBES ANDHYDRAULIC JUMPS IN CHANNELS_ ColemanduP. Donaldson and Roger D. Sullivan_ September 1949 TN 1943 THEORETICAL RELATIONS BETWEEN THESTABILITYDERIVATIVES OFA WING IN DIRECT ANDIN REVERSE SUPERSONIC FLOW_ Sidney M. Harmon_ September 1949 TN 1944 THEREVERSIBILITY THEOR_ FORTHINAIRFOILSIN SUBSONIC ANDSUPER- SONIC FLOW_ Clinton E. Brown_ September 1949 TN 1947 INVESTIGATION OFFLOW COEFFICIENT OF CIRCULAR_ SQUARE_ ANDELLIPTI- CALORIFICES AT HIGHPRESSURE RATIOS_ Edmund E. Callaghan and Dean T. Bowden_ September 1949 TN 1952 ANALYTICAL METHOD FORDETERMINING TRANSMISSION ANDABSORPTION OF TIME-DEPENDENT RADIATION THROUGH THICKABSORBERS. II - SOURCE INTENSITY_ TIME-DEPENDENT_ G. Allen_ September 1949 ONTHETHEORY OF OSCILLATING AIRFOILSOF'FINITE SPAN IN SUBSONIC TN 1953 COMPRESSIBLE FLOW_ Eric Reissner_ September 1949 TN 1955 PRELIMINARY INVESTIGATION AT SUPERSONIC SPEEDS OF TRIANGULAR ANDSWEPTBACK WINGS_ MaconC. Ellis_ Jr._ and Lowell E. Hasel_ October 1949 GUST-TUNNEL INVESTIGATION OF A FLEXIBLE-WING MODEL WITHSEMICHORD TN 1959 LINE SWEPT BACK 45°_ ThomasD. Reisert_ October 1949 TN 1960 AN EVALUATION OF THEUSEOF GROUND RADAR FORAVOIDING SEVERE TURBULENCE ASSOCIATED WITHTHUNDERSTORMS_ J. K. Thompson and V. W.

Lipscomb_ October 1949 TN 1969 COMPARATIVE DRAG MEASUREMENTS AT TRANSONIC SPEEDS OF RECTANGULAR ANDSWEPTBACK NACA 65-009 AIRFOILSMOUNTED ONA FREELY FALLING BODY_ Charles W. Mathewsand Jim Rogers Thompson_ October 1949 TN 1970 METHODS OF DESIGNING CASCADE BLADES WITHPRESCRIBED VELOCITY DIS- TRIBUTIONS IN COMPRESSIBLE POTENTIAL FLOWS_ GeorgeR. Costello, October 1949 TN 1975 EXPERIMENTAL INVESTIGATION OF T_4PERATURE RECOVERY FACTORS ON BODIES OF REVOLUTION AT SUPERSONIC SPEEDS_ William R. Wimbrow_ October 1949 TN 1977 SUMMARY OF THETHEORETICAL LIFT_ DAMPING-IN-ROLL_ ANDCENTER-OF- PRESSURE CHARACTERISTICS OF VARIOUS WINGPLANFORMS AT SUPERSONIC SPEEDS_ Robert O. Piland_ October 1949 TN 1979 A RADAR METHOD OF CALIBRATING AIRSPEED INSTALLATIONS ONAIRPLANES IN MANEUVERS AT HIGHALTITUDES ANDAT TRANSONIC ANDSUPERSONIC SPEEDS, John A. Zalovcik_ November1949 TN 1980 EFFECT OFFOREBODY WARP ANDINCREASE IN AFTERBODY LENGTH ONTHE HYDRODYNAMIC QUALITIES OFA FLYING-BOAT HULLOF HIGHLENGTH-BEAM RATIO_Walter J. Kapryan_ November1949 TN 1987 AN ANALYSIS OF SUPERSONIC AERODYNAMIC HEATING WITHCONTINUOUS FLUID INJECTION_ E. B. Klunker and H. Reese Ivey_ December1949 TN 1988 TRANSIENT BEHAVIOR OF LUMPED-CONSTANT SYST_SFORSENSING GAS PRESSURES_ GeneJ. Delio_ Glennon V. Schwentand Richard S.

Cesaro_ December1949 TN 1992 LINEARIZED LIFTING-SURFACE THEORY FORSWEPT-BACK WINGS WITHSLENDER PLANFORMS_ Harvard Lomaxand Max. A. Heaslet_ December1949 IN 1999 A THEORETICAL ANALYSIS OF ELASTIC VIBRATIONS OFFIXED-ENDED AND HINGED HELICOPTER BLADES IN HOVERING ANDVERTICAL FLIGHT_Morris Morduchowj January 1950 TN 2000 DATA ONSHAPE ANDLOCATION OF DETACHED SHOCK WAVES ONCONES ANDSPHERES_ Juergen W. Heberlej GeorgeP. Wood_and Paul B.

Gooderum_ January 1950 TN 2001 AERODYNAMIC CHARACTERISTICS OF DAMPING SCREENS_ G. B. Schubauer_ W. G. Spangenberg_and P. S. Klebanoff_ January 1950 TN 2008 THEDESIGN_ OPERATION_ ANDUSES OF THEWATER CHANNEL AS AN INSTRUMENT FORTHEINVESTIGATION OF COMPRESSIBLE-FLOW PHENOMENA_ Charles W. Mathews_January 1950 THEORETICAL CALCULATIONS OF THESUPERSONIC PRESSURE DISTRIBUTION TN 2009 ANDWAVE DRAG FORA LIMITEDFAMILYOF TAPERED SWEPTBACK WINGS WITHSYMMETRICAL PARABOLIC-ARC SECTIONS AT ZERO LIFT_ Julian H.

Kainer_ January 1950 TN 2018 LOW-SPEED INVESTIGATION OF A THIN_FAIRED_ DOUBLE-WEDGE AIRFOIL SECTION WITHNOSE FLAPSOF VARIOUS CHORDS_ Leonard M. Rose and John M. Altman_ February 1950 TN 2019 PENETRATION OF AIR JETSISSUINGFROM CIRCULAR_ SQUARE_ ANDELLIPTI- CALORIFICES DIRECTED PERPENDICULARLY TOAN AIR STREAM_ Robert A.

Ruggeri_ Edmund E. Callaghan3 and Dean T. Bowden_ February 1952 TABLES FORDETERMINING REDUCTION OF ENERGY ANDINTENSITY OF X-RAYS TN 2026 ANDGAMMA-RAYS AT VARIOUS SCATTERING ANGLES IN SMALL THICKNESSES OFMATTER_ G. Allen_ February 1950 TN 2028 EFFECT OF TUNNEL CONFIGURATION ANDTESTING TECHNIQUE ONCASCADE PERFORMANCE_ John R. Erwin and JamesC. Emery_February 1950 TN 2034 FIRST-ORDER THEORY FORUNSTEADY MOTION OFTHIN WINGS AT SUPERSONIC SPEEDS_ Barry Moskowitz and W. E. Moeckel_ February 1950 TN 2040 ANALYSIS OF AN INDUCTION BLOWDOWN SUPERSONIC TUNNEL_ Jerald M.

Bidwell_ April 1950 TN 2042 TIME-DEPENDENT DOWNWASH AT THETAIL ANDTHEPITCHING MOMENT DUETO NORMAL ACCELERATION AT SUPERSONIC SPEEDS_ Herbert S. Ribner_ February 1950 EXPERIMENTAL ANALYSIS OF A PRESSURE-SENSITIVE SYST_ FORMEASURING TN 2043 GASTEMPERATURE_ Richard S. Cesaro_ Robert J. Koenig_ and George J. Park_ February 1950 PRESSURE DISTRIBUTION ANDSOME EFFECTS OF VISCOSITY ONSLENDER TN 2044 INCLINEDBODIES OF REVOLUTION_ H. Julian Allen_ March 1950 APPROXIMATE TURBULENT BOUNDARY-LAYER DEVELOPMENT IN PLANE COMPRES- TN 2045 SIBLEFLOW ALONG THERMALLY INSULATED SURFACES WITHAPPLICATION TO SUPERSONIC-TUNNEL CONTOUR CORRECTION_ Maurice Tucker_ March 1950 TN 2046 A METHOD OF CALIBRATING AIRSPEED INSTALLATIONS ONAIRPLANES AT TRANSONIC ANDSUPERSONIC SPEEDS BYUSEOFT_IPERATURE MEASURE- MENTS_ John A. Zalovcik_ March 1950 TABLES OF WING-AILERON COEFFICIENTS OFOSCILLATING AIR FORCES FOR TN 2055 TWO-DIMENSIONAL SUPERSONIC FLOW_ Vera Huckel and Barbara J.

Durling_ March 1950 TN 2056 VELOCITY DISTRIBUTION ONWINGSECTIONS OF ARBITRARY SHAPE IN COMPRESSIBLE POTENTIAL FLOW. III - CIRCULATORY FLOWS OBEYING THESIMPLIFIEDDENSITY-SPEED RELATION_ Lipman Bers_ March 1950 TN 2057 A METHOD OF COMPUTING SUBSONIC FLOWS AROUND GIVENAIRFOILS_Abe Gelbart and Daniel Resch_March 1950 TN 2058 ONTHECONTINUATION OFA POTENTIAL GASFLOW ACROSS THESONICLINE_ Lipman Bers_ April 1950 TN 2062 DYNAMIC SIMILITUDEBETWEEN A MODEL ANDA FULL-SCALE BODY FORMODEL INVESTIGATION AT FULL-SCALE MACH NUMBER_ Anshal I. Neihouse and Philip W. Pepoon_March 1950 TN 2064 EFFECT OFASPECT RATIOONTHEAIR FORCES ANDMOMENTS OF HARMONICAL- LY OSCILLATING THIN RECTANGULAR WINGS IN SUPERSONIC POTENTIAL FLOW_ Charles E. Watkins_ April 1950 TN 2065 A TRANSFORMATION THEORY OF THEPARTIAL DIFFERENTIAL EQUATIONS OF GASDYNAMICS_ Charles Loewner_ April 1950 TN 2076 FRICTION OF SURFACE FILMSFORMED BYDECOMPOSITION OF COMMON LUBRI- CANTS OF SEVERAL TYPES_ Robert L. Johnson_Douglas Godfrey_ and Edmond E. Bisson_ April 1950 TN 2077 A DETERMINATION OF THELAMINAR-_ TRANSITIONAL-_ ANDTURBULENT- BOUNDARY-LAYER T_iPERATURE-RECOVERY FACTORS ONA FLATPLATEIN SUPERSONIC FLOW_ Jackson R. Stalder_ Morris W. Rubesin_ and Thorval Tendeland_ June 1950 TN 2087 COMPARISON OF THEORETICAL ANDEXPERIMENTAL HEATTRANSFER ONA COOLED 20° CONE WITHA LAMINAR BOUNDARY LAYER AT MACH 2.02_ Richard Scherrer and Forrest E. Gowen_ May 1950 TN 2090 INVESTIGATION OF SPARK-OVER VOLTAGE-DENSITY RELATION FORGAS- TEMPERATURE SENSING_ Robert J. Koenig and Richard S. Cesaro_May TN 2092 APPROXIMATE AERODYNAMIC INFLUENCE COEFFICIENTS FORWINGS OF ARBI- TRARY PLANFORM IN SUBSONIC FLOW_ Franklin W. Diederich_ July 1950 TN 2093 FORMULAS ANDCHARTS FORTHESUPERSONIC LIFT ANDDRAG OFFLAT SWEPT-BACK WINGS WITH INTERACTING LEADING ANDTRAILINGEDGES_ Doris Cohen_May 1950 TN 2095 APPLICATION OF THEWIRE-MESH PLOTTING DEVICE TO INCOMPRESSIBLE CASCADE FLOWS_ Willard R. Westphal and JamesC. Dunovant_May 1950 TN 2096 THEEFFECTS OF AMOUNT ANDTYPEOF CAMBER ONTHEVARIATION WITHMACH NUMBER OF THEAERODYNAMIC CHARACTERISTICS OFA 10%THICKNACA 64A-SERIES AIRFOIL SECTION_ James L. Summers and Stuart L. Freon_ May 1950 A METHOD OF CALIBRATING AIRSPEED INSTALLATIONS ON AIRPLANES AT TN 2099 TRANSONIC AND SUPERSONIC SPEEDS BY USE OF ACCELEROMETERS AND ALTITUDE-ANGLE MEASUREMENTS_ John A. Zalovick_ May 1950 COMPARISON BETWEEN THEORY AND EXPERIMENT FOR WINGS AT SUPERSONIC TN 2 i00 SPEEDS_ Walter G. Vincenti_ June 1950 TN 2101 A NUMERICAL PROCEDURE FOR DESIGNING CASCADE BLADES WITH PRESCRIBED VELOCITY DISTRIBUTIONS IN INCOMPRESSIBLE POTENTIAL FLOW_ Arthur G. Hansen and Peggy L. Yohner_ June 1950 TN 2102 REVIEW OF LITERATURE PERTINENT TO FIRE-EXTINGUISHING AGENTS AND TO BASIC MECHANISMS INVOLVED IN THEIR ACTION_ George Fryburg_ May ANALYTICAL METHOD FOR DETERMINING TRANSMISSION AND ABSORPTION OF TN 2108 TIME-DEPENDENT RADIATION THROUGH THICK ABSORBERS. III - ABSORBER WITH RADIOACTIVE DAUGHTER PRODUCTS_ G. Allen_ June 1950 TN 2109 FREQUENCY RESPONSE OF POSITIVE-DISPLACEMENT VARIABLE-STRIKE FUEL PUMP_ Harold Shames_ Seymour C. Himmel_ and Darnold Blivas_ June INTERFEROMETER CORRECTIONS AND MEASUREMENTS OF LAMINAR BOUNDARY TN 2110 LAYERS IN SUPERSONIC STREAM_ Robert E. Blue_ June 1950 TN 2111 A STUDY OF WATER DISTRIBUTIONS DURING LANDINGS WITH SPECIAL REF- ERENCE TO A PRISMATIC MODEL HAVING A HEAVY BEAM LOADING AND A 30 ° ANGLE OF DEAD RISE_ Robert F. Smiley_ June 1950 GENERAL METHOD FOR COMPUTATION OF EQUILIBRIUM COMPOSITION AND TN 2113 TEMPERATURE OF CHEMICAL REACTIONS, Vearl N. Huff and Virginia E.

Morrell_ June 1950 THEORETICAL WAVE DRAGS AND PRESSURE DISTRIBUTIONS FOR AXIALLY TN 2115 SYMMETRIC OPEN-NOSE BODIES_ John R. Jack_ June 1950 LINEARIZED SUPERSONIC AXIALLY SYMMETRIC FLOW ABOUT OPEN-NOSED TN 2116 BODIES OBTAINED BY USE OF STREAM FUNCTION_ Franklin Moor% June DESIGN AND APPLICATIONS OF HOT-WIRE ANEMOMETERS FOR STEADY- TN 2117 STATE MEASUREMENTS AT TRANSONIC AND SUPERSONIC AIRSPEEDS_ Herman H. Lowell_ July 1950 TN 2118 INVESTIGATION OF A NACA HIGH-SPEED OPTICAL TORQUEMETER_ John J.

Rebeske_ Jr._ June 1950 DEVELOPMENT ANDPRELIMINARY INVESTIGATION OF A METHOD OF OBTAINING TN 2120 HYPERSONIC AERODYNAMIC DATABYFIRING MODELS THROUGH HIGHLY COOLED GASES_ Harold V. Soule and Alexander P. Sabol_ July 1950 INVESTIGATION OF TURBULENT FLOW IN A TWO-DIMENSIONAL CHANNEL_ John TN 2123 Laufer_ July 1950 SPECTRUMS ANDDIFFUSION IN A ROUND TURBULENT JETj Stanley Corrsin TN 2124 and Mahinder S. Uberoi_ July 1950 PRANDTL-MEYER FLOW FORA DIATOMIC GASOF VARIABLE SPECIFICHEAT_ TN 2125 Robert N. Noyes_ June 1950 CALCULATION OF TRANSONIC FLOWS PASTTHINAIRFOILSBYAN INTEGRAL TN 2130 METHOD_ William Perl_ July 1950 BOUNDARY LAYER TRANSITION OF A COOLED 20° CONE AT MACH NUMBERS OF TN 2131 1.5 AND2.0_ Richard Scherrer_ July 1950 TN 2133 INVESTIGATION OF SEPARATION OF THETURBULENT BOUNDARY LAYER_ G. B.

Schubauerand P. S. Klebanoffj August 1950 TN 2135 THECALCULATION OF DOWNWASH BEHIND WINGS OF ARBITRARY PLANFORM AT SUPERSONIC SPEEDS_ John C. Martin_ July 1950 TN 2137 AN ANALYSIS OF BASE PRESSURES AT SUPERSONIC VELOCITIES ANDCOMPARI- SON WITHEXPERIMENT_ Dean R. Chapman_ July 1950 ANALYTICAL ANDEXPERIMENTAL INVESTIGATION OF ADIABATIC TURBULENT TN 2138 FLOW IN SMOOTH TUBES_ Robert G. Deissler_ July 1950 TN 2141 CHARTS FORESTIMATING DOWNWASH BEHIND RECTANGULAR_ TRAPEZOIDALj ANDRECTANGULAR WINGS AT SUPERSONIC SPEEDS_ Rudolph C. Haefeli_ Harold Mirels_ and John L. Cummings_ August 1950 PHOTOMICROGRAPHIC INVESTIGATION OF SPONTANEOUS FREEZING T_21PERA- TN 2142 TURES OF SUPERCOOLED WATER DROPLETS_ Robert G. Dorsch and Paul F.

Hacker_ July 1950 TN 2145 LIFT CANCELLATION TECHNIQUE IN LINEARIZED SUPERSONIC-WING THEORY_ Harold Mirels_ August 1950 TN 2147 SOME CONICAL ANDQUASI-CONICAL FLOWS IN LINEARIZED SUPERSONIC-WING THEORY_ Herbert S. Ribner_ August 1950 TN 2148 LAMINAR-BOUNDARY-LAYER HEAT-TRANSFER CHARACTERISTICS OF A BODY OF REVOLUTION WITHA PRESSURE GRADIENT AT SUPERSONIC SPEEDS_ William R. Wimbrowand Richard Scherrer_ August 1950 TN 2151 ESTIMATION OF THEDAMPING IN ROLLOF SUPERSONIC-LEADING-EDGE WING- BODY COMBINATIONS_ Warren A. Tucker and Robert O. Piland_ July 1950 TN 2154 AN ANALYSIS OF THEAUTOROTATIVE PERFORMANCE OF A HELICOPTER POWERED BYROTOR-TIP JET UNITS_Alfred Gessow_ July 1950 TN 2158 A GENERAL INTEGRAL FORM OF THEBOUNDARY-LAYER EQUATION FORIN- COMPRESSIBLE FLOW WITHAN APPLICATION TOTHECALCULATION OF THE SEPARATION POINTOF TURBULENT BOUNDARY LAYERS_ Neal Tetervin and Chia Chiao Lin_ August 1950 TN 2159 ONTHEPARTICULAR INTEGRALS OF THEPRANDTL-BUSEMANN INTERATION EQUATIONS FORTHEFLOW OF A COMPRESSIBLE FLUID_Carl Kaplan_ August TN 2160 MEASUREMENTS OF SECTION CHARACTERISTICS OF A 45° SWEPT WING SPANNING A RECTANGULAR LOW-SPEED WINDTUNNEL ASAFFECTED BY THETUNNEL WALLS_ Robert E. Dannenberg_August 1950 TN 2164 AXIAL-MOMENTUM THEORY FORPROPELLERS IN COMPRESSIBLE FLOW 3 Arthur W. Vogeley_ July 1951 TN 2165 METHOD OF ANALYSIS FORCOMPRESSIBLE FLOW THROUGH MIXED-FLOW CENTRI- FUGAL IMPELLERS OFARBITRARY DESIGN_ Joseph T. Hamrick_ Ambrose Ginsburg_ and Walter M. Osborn_August 1950 TN 2167 SONIC-FLOW-ORIFICE TEMPERATURE PROBE FORHIGH-GAS-TE>IPERATURE MEASUREMENTS_ Perry L. Blackshear_ Jr._ September 1950 TN 2169 WIND-TUNNEL INVESTIGATION AT LOW SPEED OF A 45° SWEPTBACK UN- TAPERED SEMISPAN WING OF ASPECT RATIO1.59 EQUIPPED WITHVARIOUS 25 PERCENT CHORD-PLAIN FLAPS_ Harold S. Johnson and John R. Hager- man_August 1950 TN 2171 INVESTIGATION OFA TWO-STEP NOZZLE IN THELANGLEY II-INCH HYPER- SONIC TUNNEL_ Charles H. McLellan_ ThomasW. Williams_ and Mitchel H. Bertram> September 1950 TN 2172 LOW-SPEED INVESTIGATION OF THESTALLING OF A THIN_FAIRED_ DOUBLE- WEDGE AIRFOIL WITHNOSE FLAP_Leonard M. Rose and John M. Altman_ August 1950 TN 2173 DENSITY FIELDSAROUND A SPHERE AT MACH NUMBERS 1.30 AND1.62_ Paul B. Gooderum and GeorgeP. Wood_August 1950 TN 2174 COMPARISON OF THEEXPERIMENTAL PRESSURE DISTRIBUTION ONAN NACA 0012 PROFILE AT HIGHSPEEDS WITHTHATCALCULATED BY THERELAXATION METHOD_ JamesL. Amick 3 August 1950 TN 2176 ANANALYSIS OF THENORMAL ACCELERATIONS ANDAIRSPEEDS OFA FOUR- ENGINE AIRPLANE TYPEIN POSTWAR COMMERCIAL TRANSPORT OPERATIONS ON TRANSPACIFIC ANDCARIBBEAN-SOUTH AMERICAN ROUTES_ ThomasL. Cole- man and Paul W. J. Schumacher_ August 1950 TN 2179 TURNING-ANGLE DESIGN RULES FORCONSTANT THICKNESS CIRCULAR-ARC INLET GUIDE VANES IN AXIAL ANNULAR FLOW_ SeymourLieblein_ September THEDEVELOPMENT ANDPERFORMANCE OF TWO SMALL TUNNELS CAPABLE OF TN 2189 INTERMITTENT OPERATION AT MACH NUMBERS BETWEEN 0.4 AND4.0_ Walter F. Lindsey and William L. Chew_September 1950 THEUSEOFAN UNCALIBRATED CONE FORDETERMINATION OFFLOW ANGLES TN 2190 ANDMACH NUMBERS AT SUPERSONIC SPEEDS_ Morton Cooper and Robert A. Webster_ March 1951 THEORETICAL INVESTIGATION ANDAPPLICATION OF TRANSONIC SIMILARITY TN 2191 LAWFORTWO DIMENSIONAL FLOW_ W. Perl and Milton M. Klein_ October TN 2196 EFFECT OF HEAT-CAPACITY LAGONTHEFLOW THROUGH OBLIQUE SHOCK WAVESj H. Reese Ivey and Charles W. Cline_ October 1950 PRESSURE DISTRIBUTION ANDDAMPING IN STEADY PITCHAT SUPERSONIC TN 2197 MACHNUMBERS OFFLAT SWEPT-BACK WINGS HAVING ALL EDGES SUBSONIC_ Harold J. Walker and Mary B. Ballantyne_ October 1950 TN 2200 A STUDY OF SECOND-ORDER SUPERSONIC-FLOW THEORY_ Milton D. Van Dyke_ January 1951 TN 2203 BOUNDARY-LAYER MEASUR}_4ENTS IN 3.84- BY 10-1NCH SUPERSONIC CHANNEL_ Paul F. Brinich_ October 1950 TN 2205 THEORETICAL SUPERSONIC CHARACTERISTICS OF INBOARD TRAINING-EDGE FLAPSHAVING ARBITRARY SWEEP ANDTAPER MACH LINES BEHIND FLAP LEADING ANDTRAILINGEDGES_ Julian H. Kainer and Jack E. Marte_ October 1950 GRAPHICAL METHOD FOROBTAINING FLOW FIELD IN TWO-DIMENSIONAL SUPER- TN 2206 SONICSTREAM TO WHICH HEATIS ADDED_ I. Irving Pinkel and John S.

Serafini_ November1950 FREEOSCILLATIONS OF AN ATMOSPHERE IN WHICH TEMPERATURE INCREASES TN 2209 LINEARLY WITHHEIGHT_ C. L. Pekeris_ October 1950 TN 2210 IMPACT-PRESSURE INTERPRETATION IN A RAREFIED GASAT SUPERSONIC SPEEDS_ E. D. Klane and G. J. Maslach_ October 1950 TN 2211 AN APPROXIMATE METHOD OF CALCULATING PRESSURES IN THETIP REGION OF A RECTANGULAR WING OF CIRCULAR-ARC SECTION AT SUPERSONIC SPEEDS_ K. R. Czarnecki and JamesN. Mueller_ October 1950 TN 2213 AERODYNAMIC COEFFICIENTS FORAN OSCILLATING AIRFOIL WITH HINGED FLAP_ WITH TABLES FOR A MACH NUMBER OF 0.7_ M. J. Turner and S.

Rabinowitz_ October 1950 TN 2214 FORMULAS ANDTABLES OF COEFFICIENTS FORNUMERICAL DIFFERENTIA- TION WITHFUNCTION VALUES GIVENAT UNEQUALLY SPACED POINTS AND VALUES GIVENAT UNEQUALLY SPACED POINTS ANDAPPLICATION TO SOLUTION OFPARTIALDIFFERENTIAL EQUATIONS_ Chung-HuaWu_ November1950 TN 2215 COMPRESSIBILITY CORRECTION FORTURNING ANGLES OFAXIAL-FLOW INLET GUIDEVANES_ SeymourLieblein and Donald M. Sandercock_ December TN 2216 INVESTIGATION OF 75-MILLIMETER-BORE CYLINDRICAL ROLLER BEARINGS AT HIGHSPEEDS. II - LUBRICATION STUDIES - EFFECT OF OIL-INLET LOCA- TION_ANGLE_ ANDVELOCITY FORSINGLE-JET LUBRICATION_ E. Fred Macks and Zolton N. Nemeth_November1950 TN 2220 A BALSA-DUST TECHNIQUE FORAIR-FLOW VISUALIZATION ANDITS APPLI- CATION TOFLOW THROUGH MODEL HELICOPTER ROTORS IN STATICTHRUST_ Marion K. Taylor_ November1950 INVESTIGATION OFTHEFLOW THROUGH A SINGLE-STAGE TWO-DIMENSIONAL TN 2223 NOZZLE IN THELANGLEY II-INCH HYPERSONIC TUNNEL_ Charles H. McLel- lan_ ThomasW. Williams_ and Ivan E. Beckwith_ December1950 TN 2229 THEEFFECT OF ENDPLATES ONSWEPT WINGS AT LOW SPEED_ John M. Riebe and JamesM. Watson_November1950 TN 2234 STATISTICAL EXPLANATION OF SPONTANEOUS FREEZING OF WATER DROPLETS_ Joseph Levine_ December1950 TN 2236 SUPERSONIC FLOW AROUND CIRCULAR CONES AT ANGLES OF ATTACK_ Antonio Ferri_ November1950 TN 2239 THEORETICAL INVESTIGATION OF TRANSONIC SIMILARITYFORBODIES OF REVOLUTION_ W. Perl and Milton K. Klein_ December1950 TN 2242 ANALYTICAL INVESTIGATION OFTURBULENT FLOW IN SMOOTH TUBES WITH HEATTRANSFER WITHVARIABLE FLUID PROPERTIES FORPRANDTL NUMBER OF i_ Robert G. Deissler_ December1950 TN 2244 A COMPARISON OF THEORY ANDEXPERIMENT FORHIGH-SPEED FREE-MOLECULE FLOW_ Jackson R. Stalder_ Glen Goodwin_and Marcus O. Creager_ December1950 TN 2245 CALCULATION OF COMPRESSIBLE POTENTIAL FLOW PASTSLENDER BODIES OF REVOLUTION BYAN INTEGRAL METHOD_ Milton M. Klein and W. Perk_ December1950 METHOD FORDETERMINING DISTRIBUTION OF LUMINOUS EMITTERS IN CONE TN 2246 OFLAMINAR BUNSEN FLAME_ ThomasP. Clark_ January 1951 TN 2250 AN ANALYSIS OFTHEAPPLICABILITY OF THEHYPERSONIC SIMILARITYLAW TO THESTUDY OF FLOW ABOUT BODIES OF REVOLUTION AT ZERO ANGLE OF ATTACKjDorris M. Ehret_ Vernon J. Rossow_and Victor I. Stevens_ December1950 TN 2252 FORMULAS FORSOURCE_ DOUBLET_ ANDVORTEX DISTRIBUTIONS IN SUPER- SONIC WINGTHEORY_ Harvard Lomax_Max. A. Heaslet_ and Franklyn B.

Fuller_ December1950 TN 2253 ONA SOURCE-SINKMETHOD FORTHESOLUTION OF THEPRANDTL-BUSEMANN ITERATION EQUATIONS IN TWO-DIMENSIONAL COMPRESSIBLE FLOW;Keith C.

Harder and E. B. Klunker; December1950 TN 2256 THREE-DIMENSIONAL; UNSTEADY-LIFT PROBL_SIN HIGH-SPEED FLIGHT BASICCONCEPTS; Harvard Lomax; Mas. A. Heaslet; and Franklyn B.

Fuller; December1950 TN 2261 WIND-TUNNEL INVESTIGATION OFA NUMBER OFTOTAL-PRESSURE TUBES AT HIGHANGLES OF ATTACK AT SUPERSONIC SPEEDS; William Gracey; Donald E. Coletti; and Walter R. Russell; January 1951 TN 2263 THEUSEOF A LUMINESCENT LACQUER FORTHEVISUALINDICATION OF BOUNDARY-LAYER TRANSITION; Jackson R. Stalder and Ellis G. Slack_ January 1951 TN 2264 AIRFOIL PROFILES FORMINIMUM PRESSURE DRAG AT SUPERSONIC VELOCI- TIES GENERAL ANALYSIS WITHAPPLICATION TO LINEARIZED SUPERSONIC FLOW;DeanR. Chapman_ January 1951 TN 2271 FURTHER STUDY OFMETAL TRANSFER BETWEEN SLIDINGSURFACES_ J. T.

Burwell and C. D. Strang; January 1951 TN 2273 SIMILARITYLAWS FORTRANSONIC FLOW ABOUT WINGS OF FINITE SPAN; John R. Spreiter; January 1951 TN 2274 EXTENSION OF THETHEORY OF OSCILLATING AIRFOILSOF FINITE SPAN IN SUBSONIC COMPRESSIBLE FLOW;Eric Reissner; February 1951 TN 2277 EFFECTS OF COMPRESSIBILITY ONTHEPERFORMANCE OF TWO FULL-SCALE HELICOPTER ROTORS/ Paul J. Carpenter_ January 1951 TN 2279 THREE-DIMENSIONAL COMPRESSIBLE LAMINAR BOUNDARY-LAYER FLOW;Frank- lin K. Moore_March 1951 TN 2281 DETAILED COMPUTATIONAL PROCEDURE FORDESIGN OF CASCADE BLADES WITH PRESCRIBED VELOCITY DISTRIBUTIONS IN COMPRESSIBLE POTENTIAL FLOWS_ GeorgeR. Costello_ Robert L. Cunlnings_and John T. Sinnette_ Jr._ February 1951 TN 2283 METHOD FORCALCULATING LIFT DISTRIBUTIONS FORUNSWEPT WINGS WITH FLAPSORAILERONS BYUSEOF NONLINEAR SECTION LIFT DATA(Superseded by Report I090)_ JamesC. Sivells and Gertrude C. Westrick_ January TN 2286 PRELIMINARY INVESTIGATION OFA NEW TYPEOF SUPERSONIC INLET_ Antonio Ferri and Louis M. Nucci_ April 1951 TN 2292 EXPERIMENTAL INVESTIGATION OF THEEFFECTS OF SUPPORT INTERFERENCE ONTHEDRAG OF BODIES OF REVOLUTION AT A MACH NUMBER OF 1.5_ EdwardW. Perkins_ February 1951 TN 2293 THEPHYSICAL PROPERTIES OFACTIVENITROGEN IN LOW-DENSITY FLOW_ JamesM. Benson_February 1951 TN 2295 CHORDWISE ANDCOMPRESSIBILITY CORRECTIONS TO SLENDER-WING THEORY_ Harvard Lomaxand LomaSluder_ February 1951 TN 2296 TURBULENT BOUNDARY-LAYER TEMPERATURE RECOVERY FACTORS IN TWO- DIMENSIONAL SUPERSONIC FLOW_ Maurice Tucker and Stephen H.

Maslen_ February 1951 TN 2297 EFFECT OF AN INCREASE IN ANGLE OF DEAD RISE ONTHEHYDRODYNAMIC CHARACTERISTICS OF A HIGH-LENGTH-BEAM-RATIO HULL_Walter E.

Whitakerj Jr._ and Paul W. Bryce_ Jr._ February 1951 TN 2302 CORRESPONDENCE FLOWS FORWINGS IN LINEARIZED POTENTIAL FIELDSAT SUBSONIC ANDSUPERSONIC SPEEDS_ Sidney M. Harmon_March 1951 AN ANALYTICAL ANDEXPERIMENTAL INVESTIGATION OF THESKINFRICTION TN 2305 OF THETURBULENT BOUNDARY LAYER ONA FLATPLATEAT SUPERSONIC SPEEDS_ Morris W. Rubesin_ Randall C. Maydew_ and Steven A. Varga_ February 1951 TN 2310 GENERALIZATION OF BOUNDARY-LAYER MOMENTUM-INTEGRAL EQUATIONS TO THREE-DIMENSIONAL FLOWS INCLUDING THOSE OF ROTATING SYSTEM_ Artur Mager_March 1951 TN 2311 FLIGHTINVESTIGATION OF THEVARIATION OF STATIC-PRESSURE ERROR OFA STATIC-PRESSURE TUBEWITHDISTANCE AHEAD OF A WING ANDA FUSELAGE_ William Gracey and Elwood F. Scheithauerj March 1951 TN 2314 EFFECT OF QUADRATIC TERMS IN DIFFERENTIAL EQUATIONS OFATMOSPHERIC OSCILLATIONS_ C. L. Pekeris_ March 1951 TN 2315 SUPERSONIC LIFT ANDPITCHING MOMENT OF THIN SWEPTBACK TAPERED WINGS PRODUCED BY CONSTANT VERTICAL ACCELERATION. SUBSONIC LEADING EDGES ANDSUPERSONIC TRAILINGEDGES_ Frank S. Malvestuto_ Jr._ and Dorothy M. Hoover_March 1951 TN 2317 APPLICATIONS OF VONKARMAN'S INTEGRAL METHOD IN SUPERSONIC WING THEORY_ Chieh-Chien Chang_March 1951 TN 2318 FULL-SCALE-TUNNEL INVESTIGATION OF THESTATIC-THRUST PERFORMANCE OF A COAXIAL HELICOPTER ROTOR_ Robert D. Harrington_ March 1951 TN 2326 TWO-DIMENSIONAL SUBSONIC COMPRESSIBLE FLOWS PASTARBITRARY BODIES BY THEVARIATIONAL METHOD_ Chi-Teh Wang_ March 1951 METHOD FORDETERMINING PRESSURE DROP OFMONATOMIC GASES FLOWING IN TN 2328 TURBULENT MOTION THROUGH CONSTANT-AREA PASSAGES WITHSIMULTANEOUS FRICTION ANDHEATADDITION_ M. F. Valerino and R. B. Doyle_ April TN 2331 WIND-TUNNEL INVESTIGATION OFA NUMBER OF TOTAL-PRESSURE TUBES AT HIGHANGLES OFATTACK. SUBSONIC SPEEDS_ William Gracey_ William Letko_ and Walter R. Russell_ April 1951 TN 2333 TRANSIENT AERODYNAMIC BEHAVIOR OFAN AIRFOIL DUETODIFFERENT ARBI- TRARY MODES OF NONSTATIONARY MOTIONS IN A SUPERSONIC FLOW_ Chieh- Chien Chang_ April 1951 TN 2334 ON REFLECTION OF SHOCK WAVES FROM BOUNDARY LAYERS_ H. W. Liepmann_ A. Roshko_ and S. Dhawan_ April 1951 TN 2335 A PLAN-FORM PARAMETER FOR CORRELATING CERTAIN AERODYNAMIC CHARAC- TERISTICS OF SWEPT WINGS_ Franklin W. Diederich_ April 1951 TN 2336 SOME THEORETICAL CHARACTERISTICS OF TRAPEZOIDAL WINGS IN SUPERSONIC FLOW AND A COMPARISON OF SEVERAL WING-FLAP COMBINATIONS_ Robert O. Piland_ April 1951 TN 2337 APPROXIMATE CALCULATION OF TURBULENT BOUNDARY-LAYER DEVELOPMENT IN COMPRESSIBLE FLOW_ Maurice Tucker_ April 1951 TN 2339 TRANSONIC FLOW PAST A WEDGE PROFILE WITH DETACHED BOW WAVE GENERAL ANALYTICAL METHOD AND FINAL CALCULATED RESULTS_ Walter G. Vincenti and Cleo B. Wagoner_ April 1951 TN 2343 COMPARISON OF THEORETICAL AND EXPERIMENTAL RESPONSE OF A SINGLE- MODE ELASTIC SYST_ IN HYDRODYNAMIC IMPACT_ Robert W. Miller and Kenneth F. Merten_ April 1951 TN 2344 METHOD FOR CALCULATING DOWNWASH FIELD DUE TO LIFTING SURFACES AT SUBSONIC AND SUPERSONIC SPEEDS_ Sidney M. Harmon_ April 1951 TN 2345 THE EFFECT OF AN ARBITRARY SURFACE-TEMPERATURE VARIATION ALONG A FLAT PLATE ON THE CONVECTIVE HEAT TRANSFER IN AN INCOMPRESSIBLE TURBULENT BOUNDARY LAYER_ Morris W. Rubesin_ April 1951 TN 2349 FLUCTUATIONS IN A SPRAY FORMED BY TWO IMPINGING JETS_ Marcus F.

Heidmann and Jack C. Humphreyj April 1951 TN 2350 ON THE SECOND-ORDER TUNNEL-WALL-CONSTRUCTION CORRECTIONS IN TWO- DIMENSIONAL COMPRESSIBLE FLOW, E. B. Klunker and Keith C. Harder_ April 1951 TN 2351 AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF SURFACE HEATING ON BOUNDARY-LAYER TRANSITION ON A FLAT PLATE IN SUPERSONIC FLOW_ Robert W. Higgins and Constantine C. Pappas_ April 1951 TN 2355 ACHROMATIZATION OF DEBYE-SCHERRER LINES_ Hans Ekstein and Stanley Siegel, April 1951 TN 2356 TWO-DIMENSIONAL TRANSONIC FLOW PASTAIRFOILS_Yung-Huai Kuo_May TN 2360 EFFECT OF TAIL SURFACES ONTHEBASEDRAG OF A BODY OF REVOLUTION AT MACH NUMBERS OF 1.5 AND2.0_ J. Richard Spahr and Robert R.

Dickey_ April 1951 TN 2361 TURBULENCE-INTENSITY MEASUREMENTS IN A JET OFAIR ISSUING FROM A LONG TUBE_ Barney H. Little_ Jr._ and Stafford W. Wilbur_ May 1951 TN 2363 ONTHEAPPLICATION OFMATHIEU FUNCTIONS IN THETHEORY OF SUBSONIC COMPRESSIBLE FLOW PASTOSCILLATING AIRFOILS_Eric Reissner_ May TN 2364 ON TWO-DIMENSIONAL FLOW AFTER A CURVED STATIONARY SHOCK (WITH SPECIAL REFERENCE TO THE PROBLI_ OF DETACHED SHOCK WAVES)_ S. S.

Shu 3 May 1951 TN 2368 VAPORIZATION RATES AND HEAT-TRANSFER COEFFICIENTS FOR PURE LIQUID DROPS_ Robert D. Ingebo_ July 1951 TN 2372 RECTANGULAR-WIND-TUNNEL BLOCKING CORRECTIONS USING THE VELOCITY- RATIO METHOD_ Rudolph W. Hensel_ June 1951 TN 2383 ON A SOLUTION OF THE NONLINEAR DIFFERENTIAL EQUATION FOR TRANSONIC FLOW PAST A WAVE-SHAPED WALL_ Carl Kaplanj June 1951 TN 2387 THREE-DIMENSIONAL UNSTEADY LIFT PROBLEMS IN HIGH-SPEED FLIGHT - TRIANGULAR WING_ Harvard Lomax_ Max. A. Heaslet_ and Franklyn B.

Fuller_ June 1951 TN 2388 AXISYMMETRIC SUPERSONIC FLOW IN ROTATING IMPELLERS_ Arthur W.

Goldstein_ June 1951 TN 2391 FURTHER COMPARISONS OF THEORETICAL AND EXPERIMENTAL LIFT AND PRESSURE DISTRIBUTIONS ON AIRFOILS IN CASCADE AT LOW-SUBSONIC SPEED_ S. Katzoff and Margery E. Hannah_ August 1951 TN 2393 FLOW THROUGH CASCADE IN TANDEM_ William E. Spraglin_ June 1951 TN 2399 APPLICABILITY OF THE HYPERSONIC SIMILARITY RULE TO PRESSURE DISTRI- BUTIONS WHICH INCLUDE THE EFFECTS OF ROTATION FOR BODIES OF REVOLU- TION AT ZERO ANGLE OF ATTACK_ Vernon J. Rossow_ June 1951 TN 2400 EVALUATION OF THE REDUCED-MASS METHOD OF'REPRESENTING WING-LIFT EFFECTS IN FREE-FALL DROP TESTS OF LANDING GEARS_ Benjamin Milwitzky and Dean C. Lindquist_ July 1951 TN 2401 TE_IPERATURE DISTRIBUTION IN INTERNALLY HEATED WALLS OF HEAT EX- CHANGERS WITH NONCIRCULAR FLOW PASSAGES USING COOLANTS WITH VERY LOW PRANDTL NUMBER_ E. R. G. Eckert and George M. Low_ July 1951 TN 2403 THEINDICIAL LIFT ANDPITCHING MOMENT FORA SINKINGORPITCHING TWO-DIMENSIONAL WING FLYINGAT SUBSONIC ORSUPERSONIC SPEEDS_ Harvard Lomax_Max. A. Heaslet_ and LomaSluder_ July 1951 TN 2406 APPLICATION OFX-RAYABSORPTION TOMEASURI_ENT OF SMALL AIR-DENSITY GRADIENTS_ Ruth N. Weltmannj Steven Fairweather_ and Daryl Papk% July 1951 TN 2410 ANALYTICAL INVESTIGATION OFFULLYDEVELOPED LAMINAR FLOW IN TUBES WITHHEATTRANSFER WITHFLUID PROPERTIES VARIABLE ALONG THERADIUS_ Robert G. Deissler_ July 1951 TN 2411 METHOD OF DETERMINING INITIAL TANGENTS OF CONTOURS OFFLOW VARIA- BLESBEHIND A CURVED_ AXIALLYSYMMETRIC SHOCK WAVE_ GeorgeP. Wood and Paul B. Gooderum_ July 1951 TN 2415 EXPERIMENTAL STUDY OF AN ANGLE-OF-ATTACK VANE MOUNTED AHEAD OF THE NOSE OF ANAIRPLANE FORUSEAS A SENSING DEVICE FORANACCELERATION ALLEVIATOR_ Christopher C. Kraft_ Jr._ and Arthur Assadouria% July TN 2417 PRELIMINARY STUDY OF STABILITYOFFLOW FROM TWO DUCTS DISCHARGING INTOA COMMON DUCT_ Albert I. Bellin_ D. Richard Messina_ and Paul B. Richards_ July 1951 TN 2418 FLOW SEPARATION AHEAD OF BLUNT BODIES AT SUPERSONIC SPEEDS_ W. E.

Moeckel_ July 1951 TN 2423 TI_ORETICAL AERODYNAMIC CHARACTERISTICS OF BODIES IN A FREE- MOLECULE-FLOW FIELD_ Jackson R. Stalder and Veron J. Zurick_ July TN 2426 AN INVESTIGATION OF AIRCRAFT HEATERS.XXXIV - EXPERIMENTAL DETER- MINATION OF THERMAL ANDHYDRODYNAMICAL BEHAVIOR OF AIR FLOWING BETWEEN A FLATANDA WAVE-SHAPED PLATE_ L. M. K. Boelter_ V. D.

Sanders_ G. Young_M. Morgan_ and E. H. Morrin_ August 1951 TN 2429 STUDY OF VORTEX SHEDDING AS RELATED TO SELF-EXCITED TORSIONAL OSCILLATIONS OFAN AIRFOIL_Raymond L. Chuanand Richard J. Magnus_ September 1951 TN 2431 SKIN FRICTION OF INCOMPRESSIBLE TURBULENT BOUNDARY LAYERS UNDER ADVERSE PRESSURE GRADIENTS_ Fabio R. Goldschmied_August 1951 TN 2432 TRANSFORMATIONS OFTHEHODOGRAPH FLOW EQUATION ANDTHEINTRODUCTION OF TWO GENERALIZED POTENTIAL FUNCTIONS_ Luigi Crocco_ August 1951 TN 2436 HEATDELIVERY IN A COMPRESSIBLE FLOWAND APPLICATIONS TO HOT- WIREANEMOMETRY_ Chan-Mou Tchen_ August 1951 TN 2437 SOME MEASUREMENTS OF THEEFFECT OF GASEOUS IMPERFECTIONS ONTHE CRITICALPRESSURE RATIOIN AIR ANDTHESPEED OF SOUND IN NITROGEN_ ColemanduP. Donaldson and Jim J. Jones_ August 1951 TN 2438 HEATTRANSFER TO BODIES IN A HIGH-SPEED RAREFIED-GAS STREAM_ Jackson R. Stalder_ Glen Goodwinj and Marcus O. Creager_ August TN 2441 OPTICAL METHODS INVOLVING LIGHTSCATTERING FORMEASURING SIZE AND CONCENTRATION OF CONDENSATION PARTICLES IN SUPER-COOLED HYPERSONIC FLOW_ EnochJ° Durbin_ August 1951 TN 2443 THESIMILARITYLAWFORHYPERSONIC FLOW ABOUT SLENDER THREE- DIMENSIONAL SHAPES_ Frank M. Hamaker_Stanford E. Neice_ and A. J.

Eggers_ Jr._ August 1951 TN 2446 WIDTHOFDEBYE-SCHERRER LINESFORFINITE SPECTRAL WIDTH OF PRIMARY BEAM_ Hans Ekstein_ September 1951 TN 2451 MATHEMATICAL IMPROVEMENT OFMETHOD FORCOMPUTING POISSON INTEGRALS INVOLVED IN DETERMINATION OFVELOCITY DISTRIBUTION ONAIRFOILS_ I. Fl_gge-Lotz_ October 1951 TN 2453 AN EXPERIMENTAL STUDY OFWATER-PRESSURE DISTRIBUTIONS DURING LAND_ INGSANDPLANING OFA HEAVILY LOADED RECTANGULAR FLAT-PLATE MODEL_ Robert F. Smiley_ September 1951 TN 2454 JET-BOUNDARY CORRECTIONS FORCOMPLETE ANDSEMISPAN SWEPT WINGS IN CLOSED CIRCULAR WINDTUNNELS_ JamesC. Sivells and Rachel M. Salmi_ September 1951 TN 2457 AIR FORCES ANDMOMENTS ONTRIANGULAR ANDRELATED WINGS WITHSUB- SONIC LEADING EDGES OSCILLATING IN SUPERSONIC POTENTIAL FLOW_ Charles E. Watkins_ September 1951 TN 2458 AN INSTRUMENT EMPLOYING A CORONAL DISCHARGE FORTHEDETERMINATION OF DROPLET-SIZE DISTRIBUTION IN CLOUDS_ Rinaldo J. Brun_ Joseph Levine_ and Kenneth S. Kleinknecht_ September1951 TN 2462 INFLUENCE OF REFRACTION ONTHEAPPLICABILITY OF THEZEHNDER-MACH INTERFEROMETER TO STUDIES OF COOLED BOUNDARY LAYERS_ Martin R.

Kinsler_ September 1951 TN 2463 EXPERIMENTAL INVESTIGATION OF THEPRESSURE DISTRIBUTION ABOUT A YAWED CIRCULAR CYLINDER IN THECRITICALREYNOLDS NUMBER RANGE_ William J. Bursnall and Laurence K. Loftin_ Jr._ September 1951 TN 2466 A GENERAL CORRELATION OFTEMPERATURE PROFILES DOWNSTREAM OFA HEATED-AIR JET DIRECTED PERPENDICULARLY TOAN AIR STREAM_ Edmund E. Callaghan and Robert S. Ruggeri_ September 1951 TN 2467 THEAERODYNAMIC BEHAVIOR OF A HARMONICALLY OSCILLATING FINITE SWEPT- BACK WINGIN SUPERSONIC FLOW_ Chieh-Chien Chang_October 1951 TN 2468 INVESTIGATION AT LOW SPEED OF45° AND60° SWEPTBACK_ TAPERED_ LOW- DRAG WINGS EQUIPPED WITHVARIOUS TYPES OF FULL-SPAN_ TRAILING-EDGE FLAPS_ John J. Harper3 October 1951 TN 2471 UNSTEADY LAMINAR BOUNDARY-LAYER FLOW_ Franklin K. Moore, September TN 2473 ONTHESPECTRUM OF ISOTROPIC TURBULENCE_ H. W. Liepmann_J. Laufer_ and Kate Liepmann_November1951 TN 2474 EMPIRICAL RELATION BETWEEN INDUCED VELOCITY_ THRUST_ ANDRATEOF DESCENT OFA HELICOPTER ROTOR AS DETERMINED BYWIND-TUNNEL TESTS ONFOUR MODEL ROTORS_ Walter Castles_ Jr._ and Robin B. Gray_ October 1951 SOME FEATURES OF ARTIFICIALLYTHICKENED FULLYDEVELOPED TURBULENT TN 2475 BOUNDARY LAYERS WITHZERO PRESSURE GRADIENT_ P. S. Klebanoff and Z. W. Diehl_ October 1951 A PROCEDURE FORCALCULATING THEDEVELOPMENT OF TURBULENT BOUNDARY TN 2478 LAYERS UNDER THEINFLUENCE OF ADVERSE PRESSURE GRADIENTS_ Kennedy F. Rubert and Jerome Persh_ September 1951 TABLES OF EXACT LAMINAR-BOUNDARY-LAYER SOLUTIONS WHEN THEWALLIS TN 2479 POROUS ANDFLUID PROPERTIES AREVARIABLE_ W. Byron Brownand Patrick L. Donaughe_September 1951 TN 2481 HYDRODYNAMIC CHARACTERISTICS OF A LOW-DRAG_ PLANING-TAIL FLYING- BOAT HULL_Henry B. Suydam_ January 1952 TN 2484 EFFECTS OF COMPRESSIBILITY ONTHEFLOW PASTA TWO-DIMENSIONAL BUMP_ W. F. Lindsey and Bernard N. Daley_ April 1952 EFFECT OF GROUND INTERFERENCE ONTHEAERODYNAMIC CHARACTERISTICS TN 2487 OF A 42° SWEPTBACK WING_G. Chester Furlong and ThomasV. Bolleck_ October 1951 TN 2489 AERODYNAMIC CHARACTERISTICS OF A REFINED DEEP-STEP PLANING-TAIL FLYING-BOAT HULLWITHVARIOUS FOREBODY ANDAFTERBODY SHAPES_ John M. Riebe and Rodger L. Naesethj June 1952 TN 2492 A METHOD OF SOLVING THEDIRECT ANDINVERSE PROBLEM OF SUPERSONIC FLOW ALONG ARBITRARY STREAM FILAMENTS OFREVOLUTION IN TURBO- MACHINES_ Chung-HuaWuand Eleanor L. Costilow_ September 1951 TN 2494 LIFT ANDMOMENT ONOSCILLATING TRIANGULAR ANDRELATED WINGS WITH SUPERSONIC EDGES_ Herbert C. Nelson, September 1951 TN 2497 GENERALIZED CONICAL-FLOW FIELDSIN SUPERSONIC WING THEORY_ Max. A.

Heaslet_ September 1951 TN 2499 LAMINAR FRICTION ANDHEAT TRANSFER AT MACH NUMBERS FROM I TO I0_ E. B. Klunker and F. EdwardMcLean_October 1951 TN 2500 A COMPARISON OF THETURBULENT BOUNDARY-LAYER GROWTH ONAN UNSWEPT ANDA SWEPT WING_ John M. Altman and Nora-Lee F. Hayter_ September TN 2501 EXPRESSIONS FORMEASURING THEACCURACY OF APPROXIMATE SOLUTIONS TO COMPRESSIBLE FLOW THROUGH CASCADES OF BLADES WITHEXAMPLES OF USE_ John J. Sinnette_ Jr._ GeorgeR. Costello_ and Robert L. Cummings_ October 1951 TN 2503 HYDRODYNAMIC INVESTIGATION OFA SERIES OF HULLMODELS SUITABLE FOR SMALL FLYINGBOATS ANDAMPHIBIANS_ W. C. Hugli_ Jr._ and W. C. Axt_ November1951 TN 2505 ONTHEATTACHED CURVED SHOCK IN FRONT OF A SHARP-NOSED AXIALLY SYMMETRICAL BODY PLACED IN A UNIFORM STREAM_ S. F. Shen and C. C.

Lin_ October 1951 TN 2506 AN ANALYTIC DETERMINATION OF THEFLOW BEHIND A SYMMETRICAL CURVED SHOCK IN A UNIFORM STREAM_ C. C. Lin and S. F. Shen_October 1951 TN 2508 LANDING CHARACTERISTICS IN WAVES OF THREE DYNAMIC MODELS OF FLYING BOATS_ JamesM. Benson_Robert F. Havens_and David R. Woodward_ January 1952 TN 2509 A SELF-SYNCHRONIZING STROBOSCOPIC SCHLIEREN SYST_IFORTHESTUDY OF UNSTEADY AIR FLOWS_ Leslie _. Lawrence_Stanley F. Schmidt_ and Floyd W. Looschen_October 1951 TN 25i0 EXPERIMENTAL VALUES OF THESURFACE TENSION OF SUPERCOOLED WATER_ Paul T. Hacherj October 1951 TN 2511 CALCULATION OF HIGHER APPROXIMATIONS FORTWO-DIMENSIONAL COMPRES- SIBLEFLOW BYA SIMPLIFIEDITERATION PROCESS_ W. H. Braun and M. M.

Klein_ October 1951 TN 2515 THELINEARIZED CHARACTERISTICS METHOD ANDITS APPLICATION TO PRACTICAL NONLINEAR SUPERSONIC PROBLEMS_ Antonio Ferri_ October TN 2518 CRITERIONS FORCONDENSATION-FREE FLOW IN SUPERSONIC TUNNELS_ Warren C. Burgess_ Jr._ and Ferris L. Seashore_December1951 TN 2519 A COMPARISON OF THEEXPERIMENTAL SUBSONIC PRESSURE DISTRIBUTIONS ABOUT SEVERAL BODIES OF REVOLUTION WITHPRESSURE DISTRIBUTIONS COMPUTED BY MEANS OF THE LINEARIZED THEORY_ Clarence W. Matthews_ February 1952 TN 2520 EFFECTS OF PRESSURE-RAKE DESIGN PARAMETERS ON STATIC-PRESSURE MEASUR_IENT FOR RAKES USED IN SUBSONIC FREE JETS_ Lloyd N. Krause_ October 1951 TN 2521 LAMINAR BOUNDARY LAYER ON A CIRCULAR CONE IN SUPERSONIC FLOW AT A SMALL ANGLE OF ATTACK, Franklin K. Moore, October 1951 A VELOCITY-CORRECTION FORMULA FOR THE CALCULATION OF TRANSONIC TN 2527 MACH NUMBER DISTRIBUTIONS OVER DIAMOND-SHAPED AIRFOILS_ H. Reese Ivey and Keith C. Harder_ November 1951 WIND-TUNNEL INVESTIGATION OF SIX SHIELDED TOTAL-PRESSURE TUBES AT TN 2530 HIGH ANGLES OF ATTACK. SUBSONIC SPEEDS_ Walter R. Russell_ William Gracey_ William Letko_ and Paul G. Fournier_ November 1951 TN 2531 SIMPLIFIED METHOD FOR CALCULATION OF COMPRESSIBLE LAMINAR BOUNDARY LAYER WITH ARBITRARY FREE-STREAM PRESSURE GRADIENT_ George M. Low_ October 1951 TN 2535 MINIMUM WAVE DRAG OF BODIES OF REVOLUTION WITH A CYLINDRICAL CENTER SECTION_ Franklyn B. Fuller and Benjamin R. Briggs_ October 1951 TN 2537 HEAT CAPACITY LAG IN GASES_ Richard Walker_ November 1951 TN 2539 APPLICATION OF VARIATIONAL METHODS TO TRANSONIC FLOWS WITH SHOCK WAVES_ Chi-Teh Wang and Pei-Chi Chou_ November 1951 TN 2541 STUDIES OF VON KARMAN'S SIMILARITY THEORY AND ITS EXTENSION TO COMPRESSIBLE FLOWS. A CRITICAL EXAMINATION OF SIMILARITY THEORY FOR INCOMPRESSIBLE FLOWS_ C. C. Lin and S. F. Shen_ November 1951 STUDIES OF VON KARMAN'S SIMILARITY THEORY AND ITS EXTENSION TO TN 2542 COMPRESSIBLE FLOWS. A SIMILARITY THEORY FOR TURBULENT BOUNDARY LAYER OVER A FLAT PLATE IN COMPRESSIBLE FLOW_ C. C. Lin and S. F. Shen_ November 1951 TN 2543 STUDIES OF VON KARMAN'S SIMILARITY THEORY AND ITS EXTENSION TO COMPRESSIBLE FLOWS. INVESTIGATION OF TURBULENT BOUNDARY LAYER OVER A FLAT PLATE IN COMPRESSIBLE FLOW BY THE SIMILARITY THEORY_ S. F. Shen_ November 1951 TN 2546 VISCOSITIES OF AIR AND NITROGEN AT LOW PRESSURES_ Herrick L.

Johnson_ Robert W. Mattox_ and Robert W. Powers_ November 1951 TN 2547 AN INVESTIGATION BY THE HODOGRAPH METHOD OF FLOW THROUGH A SYMMETRICAL NOZZLE WITH LOCALLY SUPERSONIC REGIONS, F. Edward Ehlers and Hirsh G. Cohen, November 1951 DETERMINATION OF SHAPES OF BOAT-TAlLBODIES OF REVOLUTION FOR TN 2550 MINIMUM WAVE DRAG_ Mac C. Adams_ November1951 TN 2552 CONSIDERATIONS ONTHEEFFECT OFWING TUNNEL WALLS ONOSCILLATING AIR FORCES FORTWO DIMENSIONAL SUBSONIC COMPRESSIBLE FLOW_ Harry L. Rumyan and Charles E. Watkins_ December1951 TN 2554 THEORETICAL AERODYNAMIC CHARACTERISTICS OFA FAMILYOF SLENDER WING TAlL BODY COMBINATIONS_ Harvard Lomaxand Paul F. Byrd_ November TN 2559 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OFCONDENSATION OF AIR IN HYPERSONIC WINDTUNNELS_ H. Guyford Stever and Kenneth C.

Rathbun_November1951 TN 2560 AN EXPERIMENTAL INVESTIGATION OF TRANSONIC FLOW PASTTWO-DIMENSIONAL WEDGE ANDCIRCULAR ARCSECTIONS USINGA MACH ZEHNDER INTERFEROMETER_ Arthur Earl Bryson_ Jr._ November1951 TN 2562 NUMERICAL DETERMINATION OF INDICIAL LIFT OFA TWO-DIMENSIONAL SINKINGAIRFOILAT SUBSONIC MACHNUMBERS FROM OSCILLATORY LIFT COEFFICIENTS WITHCALCULATIONS FORMACH NUMBER 0.7_ Bernard Mazelsky_ December1951 TN 2567 DIRECT MEASUREMENTS OF SKINFRICTION_ Satish Dhawan_ January 1952 TN 2568 EFFECT OF SLIP ONFLOW NEAR A STAGNATION POINTANDIN A BOUNDARY LAYER_ C. C. Lin and S. A. Schaaf_ December1951 COMPARISON OF AIRSPEED CALIBRATIONS EVALUATED BYTHEACCELEROMETER TN 2570 ANDRADAR METHODS_ Lindsay I. Lina and JamesP. Trant_ Jr._ January 1952 TN 2571 APPLICATION OF THEVON KARMAN MOMENTUM THEOR_TO TURBULENT BOUNDARY LAYERS_ Jerold M. Bidwell_ December1951 TN 2579 APPROXIMATE METHODS FORCALCULATING THEFLOW ABOUT NONLIFTING BODIES OF REVOLUTION AT HIGHSUPERSONIC AIRSPEEDS_ A. J. Eggers_ Jr._ and Raymond C. Savin_ December1951 AN ANALYSIS OFAN X-RAYABSORPTION METHOD FORMEASUR_ENT OF HIGH TN 2580 GAST_iPERATURES_ Ruth N. Weltmannand Perry W. Kuhns_ December TN 2582 GENERAL CONSIDERATION OF PROBLEMS IN COMPRESSIBLE FLOW USING THEHODOGRAPH METHOD_ Chieh-Chien Chang_January 1952 A SEMIEMPIRICAL PROCEDURE FORCOMPUTING THEWATER-PRESSURE DISTRI- TN 2583 BUTION ONFLATANDV-BOTTOM PRISMATIC SURFACES DURING IMPACT OR PLANING_ Robert F. Smiley_ December1951 TRANSONIC FLOW PASTA WEDGE PROFILE WITHDETACHED BOW WAVE-DETAILS TN 2588 OF AN ANALYSIS_ Walter G. Vincenti and Cleo B. Wagoner_December ORIENTATION OF ORIFICES ONBODIES OF REVOLUTION FORDETERMINATION TN 2592 OF STREAM STATICPRESSURE AT SUPERSONIC SPEEDS_ Morton Cooper and Clyde V. Hamilton_ January 1952 DESIGN OF TWO-DIMENSIONAL CHANNELS WITHPRESCRIBED VELOCITY DIS- TN 2593 TRIBUTIONS ALONG THECHANNEL WALLS 3 John D. Stanitz_ January 1952 DESIGN OF TWO DIMENSIONAL CHANNELS WITHPRESCRIBED VELOCITY TN 2595 DISTRIBUTIONS ALONG THECHANNEL WALLS. II - SOLUTION BY GREEN'S FUNCTION_ John D. Stanitz_ January 1952 INVESTIGATION OFLAMINAR BOUNDARY LAYERIN COMPRESSIBLE FLUIDSUSING TN 2597 THECORCCO METHOD_ E. R. Van Driest_ January 1952 EXPERIMENTAL DETERMINATION OF TIME CONSTANTS ANDNUSSELT NUMBERS TN 2599 FORBARE WIRETHERMOCOUPLES IN HIGHVELOCITY AIR STREAMS AND ANALYTIC APPROXIMATION OF CONDUCTION ANDRADIATION ERRORS_ Marvin D. Scadron and Isidore Warshawsky_ January 1952 BEHAVIOR OF VORTEX SYSTEM BEHIND CRUCIFORM WINGS-MOTIONS OFFULLY TN 2605 ROLLED UP VORTICES_ Alvin H. Sacks_ January 1952 SPECTRUM OF TURBULENCE IN A CONTRACTING STREAM_ H. S. Ribner and TN 2606 M. Tucker_ January 1952 TN 2607 ELECTRICAL PRESSURE INTEGRATOR_ Arleigh P. Helferj January 1952 ESTIMATE OF SLIP EFFECT ONCOMPRESSIBLE LAMINAR BOUNDARY LAYER TN 2609 SKINFRICTION_ Harold Mirels 3 January 1952 TN 2611 EXPERIMENTAL INVESTIGATION OF BASE PRESSURE ONBLUNT TRAILING EDGE WINGS AT SUPERSONIC VELOCITIES_ Dean R. Chapman_ William R.

Wimbrow,and Robert H. Kester_ January 1952 DETERMINATION OF INDICIAL LIFT ANDMOMENT OF A TWO DIMENSIONAL TN 2613 PITCHING AIRFOIL AT SUBSONIC MACH NUMBERS FROM OSCILLATORY COEFFI- CIENTS WITHNUMERICAL CALCULATIONS FORA MACH NUMBER OF0.7_ Ber- nard Mazelsky_ February 1952 ACHIEVEMENT OF CONTINUOUS WALLCURVATURE IN DESIGN OF TWO- TN 2616 DIMENSIONAL SYMMETRICAL SUPERSONIC NOZZLES_ J. C. Evvard and Lawrence R. Marcus_ January 1952 SOME R_S ONAN APPROXIMATE METHOD OF ESTIMATING THEWAVE TN 2619 DRAG DUETO THICKNESS AT SUPERSONIC SPEEDS OF THREE D]R_ENSIONAL WINGS WITHARBITRARY PROFILE_ Kenneth Margolis_ February 1952 TN 2623 COMPARISON OF SUPERSONIC MINIMUM DRAG AIRFOILSDETERMINED BY LINEARANDNONLINEAR THEORY_ E. B. Klunker and Keith C. Harder_ February 1952 TN 2627 COINCIDENCE METHOD APPLIED TO ION BEAM MEASUR_ENT_ Stanley Fultz and M. L. Pool_ February 1952 TN 2629 ANALYTICAL ANDEXPERIMENTAL INVESTIGATION OFFULLYDEVELOPED TURBULENT FLOW OF AIR IN A SMOOTH TUBEWITHHEAT TRANSFER WITH VARIABLE FLUID PROPERTIES_ R. G. Deissler and C. S. Eian_ February TN 2630 A SOLUTION OF THENAVIER STOKES EQUATION FORSOURCE ANDSINK FLOWS OF A VISCOUS NEAR CONDUCTING COMPRESSIBLE FLUID_Robert V. Hess_February 1952 TN 2631 THESIMILARITYLAW FORNONSTEADY HYPERSONIC FLOWS ANDREQUIR_IENTS FORTHEDYNAMICAL SIMILARITYOF RELATED BODIES IN FREE FLIGHT_ Frank M. Hamakerand ThomasJ. Wong_ February 1952 TN 2635 AN ANALYSIS OF LAMINAR FREECONVECTION FLOW ANDHEATTRANSFER ABOUT A FLATPLATE PARALLEL TO THEDIRECTION OF THEGENERATING BODY FORCE_ SimonAstrack_ February 1952 TN 2638 STUDY OF INADVERTENT SPEED INCREASES IN TRANSPORT OPERATION_ Henry A. Pearson_ March 1952 TN 2641 A VECTOR STUDY OFLINEARIZED SUPERSONIC FLOW APPLICATIONS TO NON- PLANAR PROBLEMS_ John C. Martin_ June 1952 TN 2646 INVISCIDFLOW ABOUT AIRFOILSAT HIGHSUPERSONIC SPEEDS_ A. J.

Eggers_ Jr._ and Clarence A. Syvertson_ March 1952 TN 2647 IMPLICATION OF THETRANSPORT EQUATION OF THESEMIEMPIRICAL TREATMENT OF SHIELDS_ Philip Schwed_ March 1952 TN 2650 RADIOAUTOGRAPHICMETHOD FOREXAMINING DISTRIBUTION OF PARTICLES IN A CYCLOTRON BEAM_ M. L. Pool and S. Fultz_ March 1952 TN 2651 SUPERSONIC CONICAL FLOW_ Stephen H. Maslen_ March 1952 TN 2655 CRITICALSTUDY OF INTEGRAL METHODS IN COMPRESSIBLE LAMINAR BOUNDARY LAYERS_ Paul A. Libby_ Morris Morduchowj and Martin Bloom_March TN 2658 LAMINAR BOUNDARY LAYER OVER FLATPLATEIN A FLOW HAVING CIRCULAR STREAMLINES_ Artur Mager and Arthur G. Hansen_March 1952 TN 2659 A MINIATURE ELECTRICAL PRESSURE GAGE UTILIZINGA STRETCHED FLAT DIAPHRA_I_ John L. Pattersonj April 1952 TN 2664 EXPERIMENTAL INVESTIGATION OF THETURBULENT BOUNDARY LAYER TEMPERATURE RECOVERY FACTOR ONBODIES OF REVOLUTION AT MACH NUMBERS FROM 2.0 TO 3.8_ HowardA. Stine and Richard Scherrer_ March 1952 TN 2666 TWO DIMENSIONAL SUBSONIC FLOW PASTELLIPTIC CYLINDER BYTHE VARIATIONAL METHOD_ G. V. R. Rao_March 1952 TN 2667 GENERALIZED LINEARIZED CONICAL FLOW_ W. D. Hayes_ R. C. Roberts_ and N. Hasser_ March 1952 TN 2669 APPROXIMATE THEORY FORCALCULATION OF LIFT OF BODIES_ AFTERBODIES_ ANDCOMBINATIONS OF BODIES_ Barry Moskowitz_ April 1952 TN 2670 HIGHSPEED SUBSONIC CHARACTERISTICS OF 16 NACA6-SERIESAIRFOIL SECTIONS_ Milton D. Van Dyke_March 1952 TN 2674 SOME EXPERIMENTS ONVISUALIZATION OF FLOW FIELD BEHIND LOW ASPECT RATIOWINGS BYMEANS OFA TUFTGRID_John D_ Bird and Donald R.

Riley_ May 1952 TN 2677 WINGBODY INTERFERENCE AT SUPERSONIC SPEEDS WITHAN APPLICATION TO COMBINATIONS WITHRECTANGULAR WINGS_ Jack N. Nielsen and William C.

Pitts_ April 1952 TN 2684 A LOW SPEED INVESTIGATION OFA FUSELAGE SIDEAIR INLETFORTHEUSE AT TRANSONIC SPEEDS; Mark R. Nichols and Edwin B. Goral_ April 1952 TN 2685 A LOWSPEED INVESTIGATION OFAN ANNULAR TRANSONIC AIR INLET_Mark R. Nichols and Donald W. Rinkoski_ April 1952 TN 2686 EXPERIMENTAL INVESTIGATION OF HEATTRANSFER THROUGH LAMINAR AND TURBULENT BOUNDARY LAYERS ONA COOLED FLATPLATEAT A MACH NUMBER OF 2.4_ Ellis G. Slack_ April 1952 TN 2687 APPLICATION OF TRANSONIC SIMILARITY_Adolf Busemann_ April 1952 TN 2688 THREE DIMENSIONAL SUPERSONIC NOZZLES ANDINLETSOF ARBITRARY EXIT CROSS SECTION_ Jacob H. Lichtenstein_ May 1952 TN 2690 CONDENSATION OFAIR IN SUPERSONIC WINDTUNNELS ANDITS EFFECTS ON FLOW ABOUT MODELS_ C. Frederick Hansenand GeorgeJ. Northwong_ April 1952 TN 2692 ONTHEFORM OFTHETURBULENT SKINFRICTIONLAW ANDITS EXTENSION TO COMPRESSIBLE FLOWS_ ColemanduP. Donaldson_May 1952 TN 2693 A THEORY ANDMETHOD FORAPPLYING INTERFEROMETRY TO THEMEASUREMENT OF CERTAIN TWO DIMENSIONAL GASEOUS DENSITY FIELD_ Walton L. Howes and Donald R. Buchele_ April 1952 TN 2694 A METHOD FORSTABILIZINGSHOCK WAVES IN CHANNEL FLOW BYMEANS OF A SURGE CHAMBERj Stanford E. Neice_ June 1953 CALCULATION OFLIFT ANDPITCHING MOMENTS DUETO ANGLE OF ATTACK AND TN 2699 STEADY PITCHING V_CITY AT SUPERSONIC SPEEDS FORTHIS SWEPTBACK T_PERED WINGS WITHSTREAMWISE TIPS ANDSUPERSONIC LEADING ANDTRAIL- ING EDGES_ John C. Martin_ Kenneth Margolis and Isabella Jeffreys_ June 1952 TN 2700 RECIPROCITY RELATIONS IN AERODYNAMICS_ Max A. Heaslet and John R.

Spreiter_ May 1952 TN 2703 ELECTRICAL TECHNIQUES FORCOMPENSATION OF THERMAL TIMELAGOF THERMOCOUPLE ANDRESISTANCE THERMOMETER EL_MENTS_ Charles E.

Shepard and Isidore Warshawsky_ May 1952 DIFFUSION OF HEATFROM A LINE SOURCE IN ISOTROPIC TURBULENCE_ TN 27i0 Mahinder S. Uberoi and Stanley Corrsin_ June 1952 FLOW CHARACTERISTICS OVER A LIFTINGWEDGE OFFINITE ASPECT RATIO TN 2712 WITHATTACHED ANDDETACHED SHOCK WAVES AT A MACH NI/MBER OF 1.40_ John H. Hilton_ Jr._ June 1952 NORMAL ACCELERATIONS ANDOPERATING CONDITIONS ENCOUNTERED BY TN 2714 A HELICOPTER IN AIRMAIL OPERATIONS_ Almer D. Crim and Marlin E.

Hagen_June 1952 THETHEORETICAL CHARACTERISTICS OF TRIANGULAR TIP CONTROL SURFACES TN 2715 AT SUPERSONIC SPEEDS.MACH LINES BEHIND TRAILINGEDGES_ Julian H.

Haimer and Mary David King_ July 1952 EFFECTS OFASPECT RATIOONAIR FLOW AT HIGHSUBSONIC MACH NUMBERS_ TN 2720 W. F. Lindsey and Milton D. Humphreys_July 1952 DISPLACI_4ENT EFFECT OF A THREE DIMENSIONAL BOUNDARY LAYER_ Franklin TN 2722 K. Moore_ June 1952 USEOF THEBOUNDARY LAYEROFA CONE TOMEASURE SUPERSONIC FLOW TN 2723 INCLINATION_ Franklin K. Moore_ June 1952 TRANSONIC SIMILARITYRULES FORLIFTINGWINGS_ Keith C. Harder_ TN 2724 June 1952 INTERACTION OF OBLIQUE SHOCK WAVES WITHREGIONS OF VARIABLE PRES- TN 2725 SURE_ ENTROPY_ ANDENERGY_ W. E. Moeckel_ June 1952 ONTHEAPPLICATION OF TRANSONIC SIMILARITYRULES_ John R. Spreiter_ TN 2726 June 1952 EXPERIMENTS IN EXTERNAL NOISEREDUCTION OF A SMALL PUSHER TYPE TN 2727 AMPHIBIAN AIRPLANE_ John P. Roberts and Leo L. Beranek_ July 1952 AN ANALYSIS OF SUPERSONIC FLOW IN THE REGION OF THE LEADING EDGE OF TN 2729 CURVED AIRFOILS_ INCLUDING CHARTS FOR DETERMINING SURFACE-PRESSURE GRADIENT AND SHOCK-WAVE CURVATURE_ Samuel Kraus_ June 1952 TN 2733 METHOD FOR CALCULATION OF HEAT TRANSFER IN LAMINAR REGION OF AIR FLOW AROUND CYLINDERS OF ARBITRARY CROSS SECTION (INCLUDING LARGE TI_4PERATURE DIFFERENCES AND TRANSPIRATION COOLING)_ E. R. G.

Eckert and John N. B. Livingood_ June 1952 TN 2739 NUMERICAL DETERMINATION OF INDICIAL LIFT AND MOMENT FUNCTIONS FOR A TWO-DIMENSIONAL SINKING AND PITCHING AIRFOIL AT MACH NUMBERS 0.5 AND 0.6_ Bernard Mazelsky and Joseph A. Drischler_ July 1952 TN 2740 EXPERIMENTAL INVESTIGATION OF THE LOCAL AND AVERAGE SKIN FRICTION IN THE LAMINAR BOUNDARY LAYER ON A FLAT PLATE AT A MACH NUMBER OF 2.4_ Randall C. Maydew and Constantine C. Pappas_ July 1952 TN 2742 BOUNDARYLAYER DEVELOPMENT AND SKIN FRICTION AT MACH NUMBER 3.05_ Paul F. Brinich and Nick S. Diaconis_ July 1952 TN 2744 PRACTICAL CALCULATION OF SECOND ORDER SUPERSONIC FLOW PAST NON- LIFTING BODIES OF REVOLUTION_ Milton D. Van Dyke_ July 1952 TN 2748 ON TRANSONIC FLOW PAST A WAVE SHAPED WALL_ Carl Kaplan_ August 1952 TN 2752 A STUDY OF THE STABILITY OF THE LAMINAR BOUNDARY LAYER AS AFFECTED BY CHANGES IN THE BOUNDARY LAYER THICKNESS IN REGIONS OF PRESSURE GRADIENT AND FLOW THROUGH THE SURFACE 3 Neal Tetervin and David A.

Levine_ August 1952 TN 2762 AERODYNAMIC CHARACTERISTICS OF THREE DEEP STEP PLANING TAlL FLYING BOAT HULLS AND A TRANSVERSE STEP HULL WITH EXTENDED AFTERBODY_ John M. Riebe and Rodger L. Naeseth, August 1952 TN 2764 ACCURACY OF APPROXIMATE METHODS FOR PREDICTING PRESSURES ON POINTED NONLIFTING BODIES OF REVOLUTION IN SUPERSONIC FLOW_ Dorris M. Ehret_ August 1952 TN 2765 A FLIGHT INVESTIGATION OF THE EFFECT OF SHAPE AND THICKNESS OF THE BOUNDARY LAYER ON THE PRESSURE DISTRIBUTION IN THE PRESENCE OF SHOCK_ Eziaslav N. Harrin_ September 1925 TN 2768 SUPERSONIC FLOW WITH WHIRL AND VORTICITY IN AXISYMMETRIC CHANNELS_ Ralph J. Eschbornj August 1952 TN 2770 STUDY OF THE PRESSURE RISE ACROSS THICK WAVES REQUIRED TO SEPARATE LAMINAR AND TURBULENT BOUNDARY LAYERS_ Richard R. Heldenfels and William M. Roberts_ August 1952 TN 2772 DRIVING STANDING WAVES BY HEAT ADDITION_ Perry L. Blackshear_ Jr._ August 1952 ANAPPROXIMATE METHOD FORDETERMINING THEDISPLAC_IENT EFFECTS AND TN 2773 VISCOUS DRAG OF LAMINAR BOUNDARY LAYERS IN TWO-DIMENSIONAL HYPER- SONIC FLOW_ Mitchel H. Bertram_ September 1952 TN 2774 A METHOD FORFINDINGA LEASTSQUARES POLYNOMIAL THATPASSES THROUGH A SPECIFIED POINTWITHSPECIFIED DERIVATIVES_ Neal Tetervin_ September 1952 USEOF A CONSOLIDATED POROUS MEDIUM FORMEASUR_ENT OF FLOW RATE TN 2783 ANDVISCOSITY OF GASES AT ELEVATED PRESSURES ANDTI_IPERATURES_ Martin B. Biles and J. A. Putnam_September 1952 METHOD OF CALCULATING COMPRESSIBLE LAMINAR BOUNDARY LAYERCHARAC- TN 2784 TERISTICSIN AXIAL PRESSURE GRADIENT WITHZERO HEAT TRANSFER_ Morris Morduchowand Joseph H. Clarke_ September 1952 AIRFOIL PROFILES FORMINIMUM PRESSURE DRAG AT SUPERSONIC VELOCITIES TN 2787 APPLICATION OF SHOCK EXPANSION THEORY_ INCLUDING CONSIDERATION OF HYPERSONIC RANGE_ DeanR. Chapman_ September 1952 FLOW STUDIES IN THEVICINITY OF A MODIFIED FLATPLATERECTANGULAR TN 2790 WINGOFASPECT RATIO0.25_ William H. Michael_ Jr._ September 1952 A METHOD FORTHEDETERMINATION OF THETIME LAGIN PRESSURE MEASUR- TN 2793 ING SYSTEMS INCORPORATION CAPILLARIES_ Archibald R. Sinclair and A° Warner Robins_ September 1952 A COMPARISON OF TWO METHODS OF LINEARIZED CHARACTERISTICS FORA TN 2794 SIMPLE UNSTEADY FLOW_ Roger D. Sullivan_ September 1952 EFFECTS OF WING SWEEP ONTHEUPWASH AT THEPROPELLER PLANES OF TN 2795 MULTI-ENGINE AIRPLANES_ Vernon L. Rogallo_ September 1952 A STUDY OF THETRANSIENT BEHAVIOR OF SHOCK WAVES IN TRANSONIC TN 2797 CHANNEL FLOWS_ Robert V. Hess_October 1952 TN 2800 SOLUTIONS OFLAMINAR BOUNDARY LAYER EQUATIONS WHICH RESULT IN SPECIFICWEIGHT FLOW PROFILES LOCALLY EXCEEDING FREESTREAM VALUES_ W. Byron Brownand John N. B. Livingood_ September 1952 INVESTIGATION WITHAN INTERFEROMETER OF THEFLOW AROUND A CIRCULAR TN 2801 ARCAIRFOIL AT MACH NUMBERS BETWEEN 0.6 AND0.9_ GeorgeP. Wood and Paul B. Gooderum_ October 1952 THEPLANING CHARACTERISTICS OFA SURFACE HAVING A BASICANGLE TN 2804 OF DEAD RISE OF 20° ANDHORIZONTAL CHINEFLARE_ Walter J. Kapryan and Irving Weinstein_ October 1952 MEASURIIMENTS OF TEMPERATURE VARIATIONS IN THEATMOSPHERE NEARTHE TN 2807 TROPOPAUSE WITHREFERENCE TOAIRSPEED CALIBRATION BYTHETEMPERA- TURE METHOD_ Lindsay J. Lina and Harry H. Ricker_ Jr._ October 1952 TN 2811 ONTHECALCULATION OFFLOW ABOUT OBJECTS TRAVELING AT HIGHSUPER- SONICSPEEDS_ A. J. Eggers_ Jr._ October 1952 TN 2818 SECOND APPROXIMATION TOLAMINAR COMPRESSIBLE BOUNDARY LAYER ON FLATPLATEIN SLIP FLOW_ Stephen H. Maslen_ November1952 TN 2823 LANGLEY FULL SCALE TUNNEL INVESTIGATION OF THEMAXIMUM LIFT AND STALLING CHARACTERISTICS OFA TRAPEZOIDAL WING OF ASPECT RATIO4 WITHCIRCULAR ARCAIRFOIL SECTIONS_ Roy H. Lange_November1952 TN 2824 EFFECTS OF INDEPENDENT VARIATIONS OF MACH NUMBER ANDREYNOLDS NUMBER ONTHEMAXIMUM LIFT COEFFICIENTS OF FOUR NACA 6-SERIES AIRFOIL SECTIONS_ Stanley F. Racisz_ November1952 TN 2825 A COMPARATIVE EXAMINATION OF SOME MEASUREMENTS OFAIRFOIL SECTION LIFT ANDDRAG AT SUPERCRITICAL SPEEDS_ Gerald E. Nitzberg and Stewart M. Crandall_ November1952 TN 2827 INVESTIGATION OFA DIFFRACTION GRATING INTERFEROMETER FORUSEIN AERODYNAMIC RESEARCH_ JamesR. Sterrelt and John R. Erwin_ November TN 2828 EFFECT OFA FINITE TRAILINGEDGE THICKNESS ONTHEDRAG OF RECTANGU- LARANDDELTA WINGS AT SUPERSONIC SPEEDS_ E. B. Klunker and Conrad Rennemann_ Jr._ November1952 TN 2829 EXPERIMENTS IN TRANSONIC FLOW AROUND WEDGES_ GeorgeP. Wood_ November1952 TN 2830 SEVERAL COMBINATION PROBES FORSURVEYING STATICANDTOTAL PRES- SURE ANDFLOW DIRECTION_ Wallace M. Schulze_ GeorgeC. Ashby_ Jr._ and John R. Erwin_ November1952 TN 2832 THEORETICAL STUDY OF THETRANSONIC LIFT OFA DOUBLE WEDGE PROFILE WITHDETACHED BOW WAVE_ Walter G. Vincenti and Cleo B. Wagoner_ December1952 TN 2836 RADIANT INTERCHANGE CONFIGURATION FACTORS_ D. C. Hamilton and W.

R. Morgan_December1952 TN 2837 CORRECTIONS FORDRAG_ LIFT_ ANDMOMENT OF ANAXIALLYSYMMETRICAL BODY PLACED IN A SUPERSONIC TUNNEL HAVING A TWO DIMENSIONAL PRES- SURE GRADIENT_ I. J. Kolodner_ F. Reiche_ and H. F. Ludloff_ November1952 TN 2839 DEVELOPMENT OF TURBULENCE MEASURING EQUIPMENT_ Leslie S. G.

f Kovasznag_ January 1953 TN 2843 AUXILIARY EQUIPMENT AND TECHNIQUES FOR ADAPTING THE CONSTANT TEMPERATURE HOT WIRE ANEMOMETER TO SPECIFIC PROBLEMS IN AIR FLOW MEASUREMENTS, James C. Lawrence and L. Gene Landes_ November 1952 TN 2844 LAMINAR BOUNDARY LAYER ONCONE IN SUPERSONIC FLOW AT LARGE ANGLE OF ATTACK_ Franklin K. Moore_ November1952 TN 2845 X-RAYINSTRUMENTATION FORDENSITY MEASUREMENTS IN A SUPERSONIC FLOW FIELD_ John Dimeff_ Ralph K. Hallett_ Jr._ and C. Frederick Hansen_ December1952 TN 2849 CORRECTIONS FORLIFT_ DRAG ANDMOMENT OF ANAIRFOIL IN A SUPERSONIC TUNNEL HAVING A GIVENSTATIC PRESSURE GRADIENT_ H. F. Ludloff and M. B. Friedman_ December1952 STUDY OF PRESSURE EFFECTS ONVAPORIZATION RATEOF DROPS IN GAS TN 2850 STREAMS_ Robert D. Ingebo_ January 1953 TN 2851 THEAERODYNAMIC DESIGN OF SUPERSONIC PROPELLERS FROM STRUCTURAL CONSIDERATIONS_ Jerome B. Hammack_ December1952 TN 2854 AVERAGE SKINFRICTION DRAG COEFFICIENTS FROM TANKTESTS OF A PARABOLIC BODY OF REVOLUTION_ Elmo J. Mottard and J. Dan Loposer_ January 1953 TN 2855 GENERAL CORRELATION OF TEMPERATURE PROFILES DOWNSTREAM OF A HEATED AIR JET DIRECTED AT VARIOUS ANGLES TO AIR STREAM_ Robert S.

Ruggeri_ December1952 ESTIMATED POWER REDUCTION BYWATER INJECTION IN A NONRETURN SUPER- TN 2856 SONIC WINDTUNNEL_ Morton Copper and John R. Sevier_ Jr._ January TN 2858 SUPERSONIC WAVE DRAG OF NONLIFTING DELAT WINGS WITHLINEARLY VARY- ING THICKNESS RATIO_Arthur Henderson_Jr._ December1952 INTERACTION BETWEEN A SUPERSONIC STREAM ANDA PARALLEL SUBSONIC TN 2860 STREAM BOUNDED BYFLUID AT REST_ Herbert S. Ribner and E. Leonard Arnoff_ December1952 LAMINAR NATURAL CONVECTION FLOW ANDHEATTRANSFER OF FLUIDSWITH TN 2863 ANDWITHOUT HARESOURCES IN CHANNELS WITHCONSTANT WALL TEMPERA- TURES_ SimonOstrach_ December1952 TN 2864 CONVECTION OFA PATTERN OFVORTICITY THROUGH A SHOCK WAVE_ H. S.

Ribner_ January 1953 TN 2867 HEATANDMOMENTUM TRANSFER BETWEEN A SPHERICAL PARTICLE ANDAIR STREAMS_ Y. S. Tang_J. M. Duncan_and H. E. Schweyer_March 1953 TN 2868 REFLECTION OF A WEAK SHOCK WAVE FROM A BOUNDARY LAYER ALONG A FLAT PLATE. I - INTERACTION OF WEAK SHOCK WAVES WITHLAMINAR ANDTURBU- LENTBOUNDARY LAYERS ANALYZED BYMOMENTUM INTEGRAL METHOD_ Alfred Ritter and Yung HuaiKuo_ January 1953 TN 2869 REFLECTION OF WEAK SHOCK WAVE FROM A BOUNDARY LAYER ALONG A FLAT PLATE. II - INTERACTION OF OBLIQUE SHOCK WAVE WITH A LAMINAR BOUNDARY LAYER ANALYZED BY DIFFERENTIAL EQUATION METHOD, Yung Hual Kuo, January 1953 TN 2870 POWER OFF FLARE UP TESTS OF A MODEL HELICOPTER ROTOR IN VERTICAL AUTOROTATION, S. E. Slaymaker and Robin B. Gray_ January 1953 TN 2871 EXPERIMENTAL INVESTIGATION OF LOADS IN AN ANNULAR CASCADE OF TURBINE NOZZLE BLADES OF FREE VORTEX DESIGN_ Hubert W. Alien, Milton G.

Kotskey and Richard E. Chamness_ January 1953 TN 2878 COMBINED EFFECT OF DAMPING SCREENS AND STREAM CONVERGENCE ON TURBU- LENCE, Maurice Tucker_ January 1953 TN 2879 UNSTEADY OBLIQUE INTERACTION OF A SHOCK WAVE WITH A PLANE DISTURB- ANCE, Franklin K. Moore_ January 1953 TN 2880 A DIGITAL AUTOMATIC MULTIPLE PRESSURE RECORDER_ Bert A. Coss_ D. R.

Daykin, Leonard Jaff and Elmer M. Sharp_ January 1953 TN 2885 SOME EXACT SOLUTIO_OF TWO DIMENSIONAL FLOWS OF COMPRESSIBLE FLUID WITH HODOGRAPH METHOD_ Chieh-Chieh Chang and Vivian O'Brien_ Feb- ruary 1953 TN 2887 ON THE STABILITY OF THE LAMINAR MIXING REGION BETWEEN TWO PARALLEL STREAMS IN A GAS_ C. C. Lin_ January 1953 TN 2888 PERFORMANCE CHARACTERISTICS OF PLANE WALL TWO DIMENSIONAL DIFFUSERS_ Elliott G. Reid_ February 1953 TN 2891 FACTORS AFFECTING LAMINAR BOUNDARY LAYER MEASUREMENTS IN A SUPER- SONIC STREAM_ Robert E. Blue and George M. Low_ February 1953 TN 289 2 A RAPID METHOD FOR ESTIMATING THE SEPARATION POINT OF A COMPRESSI- BLE LAMINAR BOUNDARY LAYER_ Laurence K. Loftin_ Jr._ and Homer B.

Wilson, Jr., February 1953 TN 2893 THEORETICAL AND MEASURED ATTENUATION OF MUFFLERS AT ROOM TEMPERATURE WITHOUT FLOW_ WITH COMMENTS ON ENGINE EXHAUST MUFFLER DESIGN_ Don D.

Davis, Jr., George L. Stevens_ Jr._ Dewey Moore and George M. Stokes_ February 1953 TN 2894 CALCULATIONS OF UPWASH IN THE REGION ABOVE OR BELOW THE WING-CHORD PLANES OF SWEPT-BACK WING-FUSELAGE-NACELLE COMBINATIONS, Vernon L.

Rogallo and John L. McCloud_ III, February 1953 TN 2895 EFFECT OF VARIABLE VISCOSITY AND THERMAL CONDUCTIVITY ON HIGH SPEED SLIP FLOW BETWEEN CONCENTRIC CYLINDERS_ T. C. Lin and R. E. Street 3 February 1953 IMPINGEMENT OF CLOUD DROPLETS ONAERODYNAMIC BODIES AS AFFECTED BY TN 2903 COMPRESSIBILITY OF AIR FLOW AROUND THEBODY_ Rinaldo J. Brun_ John S. Serafini and Helen M. Gallagher_ March 1953 IMPINGEMENT OF WATER DROPLETS ONA CYLINDER IN AN INCOMPRESSIBLE TN 2904 FLOW FIELD ANDEVALUATION OFROTATING MULTICYLINDER METHOD FOR MEASUREMENT OF DROPLET SIZE DISTRIBUTION_ VOLUME MEDIUM DROPLET SIZE_ANDLIQUID WATER CONTENT IN CLOUDS_ Rinaldo J. Brun and Harry W. Mergler_ March 1953 AN AIRBORNE INDICATOR FORMEASURING VERTICAL VELOCITY OFAIRPLANES TN 2906 AT WHEEL CONTACT_ Robert C. Dreher_ February 1953 EFFECT OF HORIZONTAL-TAIL SPAN ANDVERTICAL LOCATION ONTHEAERO- TN 2907 DYNAMIC CHARACTERISTICS OF ANUNSWEPT TAlL ASSEMBLY IN SIDESLIP_ Donald R. Riley_ February 1953 TN 29i0 AN APPLICATION OF THEMETHOD OF CHARACTERISTICS TO TWO DIMENSIONAL TRANSONIC FLOWS WITHDETACHED SHOCK WAVES_ Keith C. Harder and E.

B. Klunker_ March 1953 TN 2912 THENORMAL COMPONENT OFTHEINDUCED VELOCITY IN THEVICINITY OFA LIFTING ROTOR ANDSOME EXAMPLES OF ITS APPLICATION_ Walter Castles_ Jr._ and Jacob Henri De Leeuw_March 1953 TN 2913 ONTHEDEVELOPMENT OF TURBULENT WAKES FROM VORTEX STREETS_ Anatol Roshko_March 1953 EFFECT OF THERMAL PROPERTIES ONLAMINAR BOUNDARY LAYER CHARACTER- TN 2916 ISTICS_ E. B. Klunker and F. EdwardMcLeon_March 1953 A MODIFIED REYNOLDS ANALOGY FORTHECOMPRESSIBLE TURBULENT BOUNDARY TN 2915 LAYER ONA FLAT PLATE_ Morris Rubesin_ March 1953 EFFECTS OF PARALLEL JET MIXINGONDOWNSTREAM MACHNUMBERAND STAG- TN 2918 NATION PRESSURE WITHAPPLICATION TO ENGINE TESTING IN SUPERSONIC TUNNELSj Harry Bernstein_ March 1953 TN 2919 THEASYMMETRIC ADJUSTABLE SUPERSONIC NOZZLE FORWINDTUNNEL APPLI- CATION_ H. Julian Allen_ March 1953 THEAERODYNAMIC DESIGN ANDCALIBRATION OFAN ASYMMETRIC VARIABLE TN 2921 MACH NUMBER NOZZLE WITHA SLIDINGBLOCK FORTHEMACH NUMBER RANGE 1.27 TO 2.75_ Paige B. Burbank and Robert W. Byrn% April 1953 TN 2922 THEDESIGN OF VARIABLE MACH NUMBER ASYMMETRIC SUPERSONIC NOZZLES BY TWO PROCEDURES EMPLOYING INCLINED ANDCURVED SONIC LINES_ Clarence A. Syvertson and Raymond C. Savin_ March 1953 TN 2929 EXPERIMENTAL INVESTIGATION OF THEEFFECT OF REAR FUSELAGE SHAPE ON DITCHING BEHAVIOR_ Ellis E. McBride and Lloyd J. Fisher_ April 1953 TN 2931 A METHOD FORDETERMINING CLOUD DROPLET IMPINGEMENT ONSWEPT WINGS_ Robert G. Dorsch and Rinaldo J. Brun_ April 1953 TN 2938 ANALYSIS OF HEAVY ADDITION IN A CONVERGENT DIVERGENT NOZZLE_ Donald P. Hearth and EugenePerchonok_April 1953 TN 2940 EFFECT OF HIGHBULKTEMPERATURES ONBOUNDARY LUBRICATION OF STEEL SURFACES BY SYNTHETIC FLUIDS_S. F. Murray_ Robert L. Johnson and Edmond E. Bisson_ May 1953 TN 2941 THEDRAG OF FINITE LENGTH CYLINDERS DETERMINED FROM FLIGHTTESTS AT HIGHREYNOLDS NUMBERS FORA MACH NUMBER RANGE FROM 0.5 TO 1.3_ Clement J. Welsh_ June 1953 TN 2942 PRESSURE DISTRIBUTIONS ABOUT FINITE WEDGES IN BOUNDED ANDUNBOUNDED SUBSONIC STREAMS_ Patrick L. Donougheand Ernst I. Prasse_ May 1953 TN 2944 THEZERO LIFT DRAG OF A SLENDER BODY OF REVOLUTION AS DETERMINED FROM TESTS OF SEVERAL WINDTUNNELS ANDIN FLIGHTAT SUPERSONIC SPEEDS_ Albert J. Evans_April 1953 TN 2946 A SMALL PIRANI GAGE FORMEASUREMENTS OF NONSTEADY LOW PRESSURES_ M. John Pilny_ June 1953 TN 2949 A VARIABLE FREQUENCY LIGHTSYNCHRONIZED WITHA HIGHSPEED MOTION PICTURE CAMERA TO PROVIDE VERY SHORT EXPOSURE TIMES_Walter F.

Lindsey and Joseph Burlock_ May 1953 TN 2950 A NEW SHADOW GRAPH TECHNIQUE FORTHEOBSERVATION OF CONICAL FLOW PHENOMENA IN SUPERSONIC FLOW ANDPRELIMINARY RESULTS OBTAINED FORA TRIANGULAR WINGjEugeneS. Love and Carl E. Grigsby_ May 1953 TN 2951 FLIGHTINVESTIGATION OF THEEFFECT OF TRANSIENT WINGRESPONSE ON WING STRAINS OF A FOUR ENGINE BOMBER AIRPLANE IN ROUGH AIR_ Harold N. Murrow and Chester B. Payn% June 1953 TN 2952 IMPING_ENTOFWATER DROPLETS ONNACA 651-208 AND651-212 AIRFOILS AT 4° ANGLE OF ATTACK_ Rinaldo J. Brun_ Helen M. Gallagher and Dorothea E. Vogt_ May 1953 "TN 2954 THESTRUCTURE OF TURBULENCE IN FULLYDEVELOPED PIPE FLOW_ John Laufer_ June 1953 TN 2957 SURVEYS OF THEFLOW FIELDSAT THEPROPELLER PLANES OF SIX 40° SWEPTBACK WING FUSELAGE NACELLE COMBINATIONS_ Vernon L. Rogallo and John L. McCloud_III_ June 1953 TN 2959 THEORETICAL INVESTIGATION OF THESUPERSONIC LIFT ANDDRAG OF THIN_ SWEPTBACK WINGS WITHINCREASED SWEEP NEAR THEROOT_ Doris Cohenand Morris D. Friedman_ June 1953 TN 2960 DRAG OF CIRCULAR CYLINDERS FORA WIDERANGE OF REYNOLDS NUMBERS AND MACH NUMBERS_ Forrest E. Gowenand EdwardW. Perkins_ June 1953 TN 2965 ANALYSIS OFNORMAL ACCELERATION ANDAIRSPEED DATA FROM A FOUR ENGINE TYPEOF TRANSPORT AIRPLANE IN COMMERCIAL OPERATION ONAN EASTERN UNITED STATES ROUTE FROM NOVEMBER 1947 TOFEBRUARY 1950_ ThomasL. Coleman'andPaul W. J. Schumacher_ August 1955 TN 2967 AN ANALYSIS OF THEPOWER OFFLANDING MANEUVER IN TERMS OF THE CAPABILITIES OF THEPILOT ANDTHEAERODYNAMIC CHARACTERISTICS OF THEAIRPLANE_ Albert E. von Doenhoff and GeorgeW. Jones_ Jr._ August 1953 IMPINGEMENT OF WATER DROPLETS ONWEDGES ANDDIAMOND AIRFOILSAT TN 2971 SUPERSONIC SPEEDS_ John S. Serafini_ July 1953 TN 2972 THEORETICAL PRESSURE DISTRIBUTIONS ANDWAVE DRAGS FORCONICAL BOATTAILS_ John R. Jackj July 1953 TN 2976 A STUDY OF THESTABILITYOF THEINCOMPRESSIBLE LAMINAR BOUNDARY LAYEROF INFINITE WEDGES_ Neal Tetervin_ August 1953 THEAERODYNAMIC CHARACTERISTICS OF AN ASPECT-RATIO-20 WING HAVING TN 2980 THICKAIRFOIL SECTIONS ANDEMPLOYING BOUNDARY-LAYER CONTROL BY SUCTION_ B. W. Cocke_Jr._ M. P. Fink_ S° M. Gottlieb_ August 1953 TN 2981 THEHIGHSPEED PLANING CHARACTERISTICS OF A RECTANGULAR FLAT PLATEOVER A WIDERANGE OF TRIMANDWETTED LENGTH_ Irving Weinstein and Walter J. Kapryan_ July 1953 TN 2995 NEW EXPERIMENTS ONIMPACT-PRESSURE INTERPRETATION IN SUPERSONIC ANDSUBSONIC RAREFIED AIR STREAMS_ F. S. Sherman_September 1953 TN 3000 STUDIES OF THEUSEOFFREON-12 AS A WIND-TUNNEL TESTING MEDIUM_ Albert E. von Doenhoff_ Albert L. Braslo_ and Milton A. Schwartz- berg_ August 1953 TN 3005 HEATTRANSFER ANDSKINFRICTION BYAN INTEGRAL METHOD IN THECOM- PRESSIBLE LAMINAR BOUNDARY LAYER WITHA STREAMWISE PRESSURE GRADI- ENT_Ivan E. Beckwith_ September 1953 EFFECTS OF FINITE SPAN ON THE SECTION CHARACTERISTICS OF TWO 45 ° SWEPTBACK WINGS OF ASPECT RATIO 6_ Lynn W. Hunton_ September 1953 TN 3009 VELOCITY POTENTIAL AND AIR FORCES ASSOCIATED WITH A TRIANGULAR WING IN SUPERSONIC FLOW_ WITH SUBSONIC LEADING EDGES_ AND DEFORMING HARMONICALLY ACCORDING TO A GENERAL QUADRATIC EQUATION_ Charles E.

Watkins and Julian H. Berman_ September 1953 TN 3016 ANALYSIS OF TURBULENT HEAT TRANSFER AND FLOW IN THE ENTRANCE REGIONS OF SMOOTH PASSAGES_ Robert G. Deissler_ October 1953 TN 3020 DETERMINATION OF BOUNDARY-LAYER TRANSITION REYNOLDS NUMBERS BY SURFACE-TEMPERATURE MEASUR_4ENTS OF A i0 v CONE IN VARIOUS NACA SUPERSONIC WINDTUNNELS_ Albert O. Ross_ October 1953 TN 3028 THECOMPRESSIBLE LAMINAR BOUNDARY LAYER WITHHEATTRANSFER AND SMALL PRESSURE GRADIENT_ Lynn U. Albers_ October 1953 TN 3031 PRELIMINARY EXPERIMENTAL INVESTIGATION OF LOW-SPEED TURBULENT BOUNDARY LAYERS IN ADVERSE PRESSURE GRADIENTS_ Virgil A. Sandborn_ October 1953 TN 3032 AN ANALYTICAL STUDY OF THEEFFECT OFAIRPLANE WAKE ONTHELATERAL DISPERSION OFAERIALSPRAYS_ Wilmer H. Reed_III_ October 1953 TN 3036 THEFLOW ABOUT A SECTION OF A FINITE-ASPECT-RATIO NACA 0018 AIRFOIL ONA TRANSONIC BUMP_ Jack A. Mellenthin_ October 1953 TN 3038 LOW-SPEED DRAG OF CYLINDERS OF VARIOUS SHAPES_ Noel K. Delany and NormanE. Sorensen_November1953 TN 3042 HIGH-FREQUENCY PRESSURE INDICATORS FORAERODYNAMIC PROBLEMS_ Y. T.

Li_ November1953 TN 3044 EFFECT OFA RAPIDBLADE-PITCH INCREASE ONTHETHRUST ANDINDUCED- VELOCITY RESPONSE OF A FULL-SCALE HELICOPTER ROTOR_ Paul J.

Carpenter and Bernard Fridovich_ November1953 TN 3045 ANALOGY BETWEEN MASS ANDHEATTRANSFER WITHTURBULENT FLOW_ Edmund E. Callaghan_ October 1953 TN 3047 IMPINGEMENT OF WATER DROPLETS ONNACA 65A004AIRFOILANDEFFECT OF CHANGE IN AIRFOIL THICKNESS FROM 12 TO 4 PERCENT AT 4° ANGLE OF ATTACK_ Rinaldo J. Brun_ Helen M. Gallagher_ and Dorothea E.

Vogt_ November1953 TN 3048 EXPERIMENTAL INVESTIGATION OF THEEFFECTS OF COOLING ONFRICTION ANDONBOUNDARY-LAYER TRANSITION FORLOW-SPEED GASFLOW AT THE ENTRY OF A TUBE_ Stephen J. Kline and Ascher H. Shapiro_ November TN 3049 AN ANALYTICAL INVESTIGATION OF THEEFFECT OFTHERATEOF INCREASE OF TURBULENT KINETIC ENERGY IN THESTREAM DIRECTION ONTHEDEVELOP- MENT OF TURBULENT BOUNDARY LAYERS IN ADVERSE PRESSURE GRADIENTS_ Bernard Rashis_ November1953 TN 3050 A PHOTOGRAPHIC METHOD FORDETERMINING VERTICAL VELOCITIES OF AIR- CRAFT IMMEDIATELY PRIORTO LANDING, EmanualRind_ January 1954 TN 3052 THEEFFECT OF VERTICAL CHINESTRIPSONTHEPLANING CHARACTERISTICS OF V-SHAPED PRISMATIC SURFACES HAVINGANGLES OF DEAD RISE OF 20o AND40°_ Walter J. Kapryan and GeorgeM. Boyd_Jr._ November1953 TN 3053 A NEW METHOD OF ANALYZING EXTREME-VALUE DATA_ Julius Lieblein_ January 1954 TN 3054 INVESTIGATION AT SUPERSONIC SPEEDS OF THEWAVE DRAG OF SEVEN BOATTAIL BODIES OF REVOLUTION DESIGNED FORMINIMUM WAVE DRAG_ August F. Bromm_ Jr._ and Julia M. Goodwin_December1953 A FLIGHTINVESTIGATION OFLAMINAR ANDTURBULENT BOUNDARY LAYERS TN 3056 PASSING THROUGH SHOCK WAVES AT FULL-SCALE REYNOLDS NUMBERS_ Eziaslav N. Harrin_ December1953 TN 3058 TRANSIENT TEMPERATURE DISTRIBUTIONS IN SIMPLECONDUCTING BODIES STEADILY HEATED THROUGH A LAMINAR BOUNDARY LAYER_ HermanM. Parker_ December1953 TN 3062 A FLIGHTINVESTIGATION OF THEPRACTICAL PROBLEMS ASSOCIATED WITH POROUS-LEADING EDGE-SUCTION_ Paul A. Hunter and Harold I. Johnson_ February 1954 TN 3065 PRESENT STATUS OF INFORMATION RELATIVE TO THEPREDICTION OF SHOCK- INDUCED BOUNDARY-LAYER SEPARATION_ Roy H. Lange_February 1954 TN 3069 INCOMPRESSIBLE FLOW PASTA SINUSOIDAL WALL OFFINITE AMPLITUDE_ Carl Kaplan_ February 1954 TN 3071 THEORETICAL SUPERSONIC FORCE ANDMOMENT COEFFICIENTS ONA SIDESLIP- PINGVERTICAL- ANDHORIZONTAL-TAIL COMBINATION WITHSUBSONIC LEAD- ING EDGES ANDSUPERSONIC TRAILINGEDGES_ Franks S. Malvestuto_ Jr._ March 1954 A THEORETICAL INVESTIGATION OFTHEAERODYNAMICS OF WING-TAIL TN 3072 COMBINATIONS PERFORMING TIME-DEPENDENT MOTIONS AT SUPERSONIC SPEEDS_ John C. Martin_ Margaret S. Diederich and Percy J° Bobbitt_ May 1954 MEASUREMENTS OFPRESSURE ANDTEMPERATURE FORAPPRAISAL OF THE TN 3075 TEMPERATURE METHOD OFAIRSPEED CALIBRATION IN THELOWER STRATO- SPHERE_ Lindsay J. Lina_ March 1954 LIFT ANDMOMENT COEFFICIENTS EXPANDED TO THESEVENTH POWER OF FRE- TN 3076 QUENCY FOROSCILLATING RECTANGULAR WINGS IN SUPERSONIC FLOW AND APPLIEDTOA SPECIFICFLUTTER PROBLEM_ Herbert C. Nelson_ Ruby A.

Raine_ and Charles E. Watkins_ April 1954 TN 3079 THEHYDRODYNAMIC CHARACTERISTICS OF DODIFIED RECTANGULAR FLAT PLATES HAVING ASPECT RATIOS OF 1.00 AND0.25 ANDOPERATING NEAR A FREEWATER SURFACE_ Kenneth L. Wodlin_ John A. Romsen_ and Victor L. Vaughan_Jr._ March 1954 THEZERO-LIFTDRAG OF A 60° DELTA-WING-BODY COMBINATION (AGARD TN 3081 MODEL 2) OBTAINED FROM FREE-FLIGHT TESTS BETWEEN MACH NUMBERS OF 0.8 AND1.7_ Robert O. Piland_ April 1954 MANEUVER ACCELERATIONS EXPERIENCED BYFIVE TYPES OF COMMERCIAL TN 3086 TRANSPORT AIRPLANES DURING ROUTINE OPERATIONS_ ThomasL. Coleman and Martin R. Capp_April 1954 EXPERIMENTAL INVESTIGATION OF TWO-DIMENSIONAL TUNNEL-WALL INTER- TN 3087 FERENCE AT HIGHSUBSONIC SPEEDS_ Earl D. Knechtel_ December1953 TN 3089 ONE-DIMENSIONAL_ COMPRESSIBLE_ VISCOUS FLOW RELATIONS APPLICABLE TOFLOW IN A DUCTED HELICOPTER BLADE_ John R. Henry_ December1953 TN 3091 FLOW PROPERTIES OF STRONG SHOCK WAVES IN XENON GASAS DETERMINED FORTHERMAL EQUILIBRIUM CONDITIONS_ Alexander P. Sabol_ December TN 3092 HYDRODYNAMIC DRAG OF 12- AND21-PERCENT-THICK SURFACE-PIERCING STRUTS_ Claude W. Coffe% Jr._ and Robert E. McKann_December1953 TN 3093 EFFECT OFTYPEOF POROUS SURFACE ANDSUCTION VELOCITY DISTRIBUTION ONTHECHARACTERISTICS OF A 10.5-PERCENT-THICK AIRFOIL WITHAREA SUCTION_ Robert E. Dannenbergand JamesA. Weiberg_ December1953 TN 3094 THERESISTANCE TO AIR FLOW OF POROUS MATERIALS SUITABLE FOR BOUNDARY-LAYER-CONTROL APPLICATIONS USINGAREA SUCTION_ Robert E.

Dannenberg_ J. A. Weiberg_ and B. J. Gambucci_January 1954 TN 3095 THEAMES i0- BY 14-1NCHSUPERSONIC WINDTUNNEL_ A. J. Eggers_ Jr._ and GeorgeJ. Nothwang_January 1954 TN 3097 TURBULENT BOUNDARY-LAYER ANDSKIN-FRICTION MEASUREMENTS IN AXIAL FLOW ALONG CYLINDERS AT MACH NUMBERS BETWEEN 0.5 AND3.6_ Dean R. Chapman and Robert H. Kester_ March 1954 TN 3098 DENSITY PROFILES OF SUBSONIC BOUNDARY LAYERS ONA FLATPLATE DETERMINED BY X-RAYANDPRESSURE MEASUPd_IENTS_ Ruth N. Weltmannand Perry W. Kuhns_ February 1954 IMPINGEMENT OF WATER DROPLETS ONAN ELLIPSOID WITHFINENESS RATIO5 TN 2099 IN AXISYMMETRIC FLOW_ Robert G. Dorsch_ Rinaldo J. Brun_ and John L. Gregg_March 1954 TN 3100 STATISTICAL STUDY OF TRANSITION-POINT FLUCTUATIONS IN SUPERSONIC FLOW_ J. C. Evvard_ M. Tucker_ and W. C. Burgess_ Jr._ March 1954 TN 3102 AN ANALYTICAL ANDEXPERIMENTAL STUDY OF THETRANSIENT RESPONSE OF A PRESSURE-REFULATING RELIEFVALVEIN A HYDRAULIC CIRCUITj Harold Gold and EdwardW. Otto_ March 1954 TN 3103 COOLING REQUIR_ENTS FORSTABILITYOF LAMINAR BOUNDARY LAYER WITH SMALL PRESSURE GRADIENT AT SUPERSONIC SPEEDS, GeorgeM. Low_ March TN 3104 EXPERIMENTAL INVESTIGATION OF SUBLIMATION OF ICE AT SUBSONIC AND SUPERSONIC SPEEDS ANDITS RELATION TO HEAT TRANSFER_ Willard D.

Coles and Robert S. Ruggeri_ March 1954 TN 3105 AERODYNAMICS OF SLENDER WINGS ANDWING-BODY COMBINATIONS HAVING SWEPT TRAILINGEDGES, Harold Mirels_ March 1954 TN 3122 EXPERIMENTAL INVESTIGATION AT MACH NUMBER OF 2.41 OF AVERAGE SKIN- FRICTION COEFFICIENTS ANDVELOCITY PROFILES FORLAMINAR ANDTURBU_ LENTBOUNDARY LAYERS ANDANASSESSMENT OF PROBE EFFECTS_ Robert M. O'Donnell_ January 1954 TN 3127 THEEFFECTIVENESS AT HIGHSUBSONICMACH NUMBERS OF A 20-PERCENT- CHORD PLAIN TRAILING-EDGE FLAPONTHENACA 65-210 AIRFOIL SECTION, Louis S. Stivers_ Jr., March 1954 TN 3128 COMPARISON BETWEEN THEORY ANDEXPERIMENT FORINTERFERENCE PRESSURE FIELD BETWEEN WING ANDBODY AT SUPERSONIC SPEEDS, Williams C.

Pitts_ Jack N. Nielso_ and MauriceB. Gianfriddo_ April 1954 TN 3133 THEFREE-STREAM BOUNDARIES OF TURBULENT FLOWS, Stanley Corrsin and Alan L. Kistler_ January 1954 TN 3135 INVESTIGATION OFMUTUAL INTERFERENCE EFFECTS OF SEVERAL VERTICAL- TAlL-FUSELAGE CONFIGURATIONS IN SIDESLIP,William H. Michael_ Jr._ January 1954 TN 3140 USEOFAERODYNAMIC HEATING TOPROVIDE THRUST BY VAPORIZATION OF SURFACE COOLANTS, W. E. Moeckelj February 1954 TN 3141 COMBINED NATURAL- ANDFORCED-CONVECTION LAMINAR FLOW ANDHEAT TRANSFER OFFLUIDSWITHANDWITHOUT HEATSOURCES IN CHANNELS WITH LINEARLY VARYING WALL TEMPERATURES_ SimonOstrach, April 1954 TN 3145 ANALYSIS OFTURBULENT HEAT TRANSFER_ MASS TRANSFER_ ANDFRICTIONIN SMOOTH TUBES AT HIGHPRANDTL ANDSCHMIDT NUMBERS, Robert G. Deissler_ May 1954 TN 3146 NOTE ONTHEAERODYNAMIC HEATING OF AN OSCILLATING SURFACE_ Simon Ostrach_ April 1954 TN 3147 IMPINGI_IENT OF WATER DROPLETS ONAN ELLIPSOID WITHFINENESS RATIO i0 IN AXISYMMETRIC FLOW_ Rinaldo J. Brun and Robert G. Dorsch_ May METHOD FORRAPIDDETERMINATION OF PRESSURE CHANGE FORONE-DIMENSION- TN 3150 AL FLOW WITHHEATTRANSFER_ FRICTION_ ROTATION_ ANDAREA CHANGE_ J. E. Hubbartt_ H. O. Slon% and V. L. Arne_ June 1954 TN 3151 EXACT SOLUTIONS OF LAMINAR-BOUNDARY-LAYER EQUATIONS WITHCONSTANT PROPERTY VALUES FORPOROUS WALL WITHVARIABLE T_IPERATURE_ Patrick L. Donougheand John N. B. Livingood_ September 1954 TN 3153 VARIATION OFLOCAL LIQUID-WATER CONCENTRATION ABOUT AN ELLIPSOID OF FINENESS RATIO5 MOVING IN A DROPLET FIELD_ Robert G. Dorsch and Rinaldo J. Brun_ July 1954 TN 3155 IMPINGEMENT OFWATER DROPLETS ONNACA 65A004AIRFOIL AT 8° ANGLE OF ATTACK_ R. J. Brun_ H. M. Gallagher_ and D. E. Vogt_ July 1954 TN 3157 METHOD FORCALCULATION OF COMPRESSIBLE LAMINAR BOUNDARY LAYER WITH AXIAL PRESSURE GRADIENT ANDHEATTRANSFER_ Paul A. Libby and Morris Morduchow_ January 1954 FLIGHTINVESTIGATION AT LARGE ANGLES OF ATTACK OF THESTATIC- TN 3159 PRESSURE ERRORS OF A SERVICE PITOT-STATIC TUBEHAVING A MODIFIED ORIFICECONFIGURATION_ William Gracey and Elwood F. Scheithauer_ February 1954 TN 3162 EFFECTS OF SUBSONIC MACHNUMBER ONTHEFORCES ANDPRESSURE DISTRI- BUTIONS ONFOUR NACA64A-SERIES AIRFOIL SECTIONS AT ANGLES OF ATTACK AS HIGHAS 28°_ Louis S. Stivers_ Jr._ March 1954 TN 3163 USEOFA HOT-WIRE ANEMOMETER IN SHOCK-TUBE INVESTIGATIONS_ Darshan Singh Dosanjh_ December1954 TN 3165 PRELIMINARY INVESTIGATION OF THEEFFECTS OF HEATTRANSFER ON BOUNDARY LAYER TRANSITION OF A PARABOLIC BODY OF REVOLUTION AT A MACH NUMBER OF 1.61_ K. R. Czarnecki and Archibald R. Sinclair_ April 1954 TN 3166 AN EXTENSION OF THEINVESTIGATION OF THEEFFECTS OF HEATTRANSFER ONBOUNDARY-LAYER TRANSITION OF A PARABOLIC BODY OF REVOLUTION AT A MACH NUMBER OF 1.61_ K. R. Czarnecki_ and Archibald R. Sinclair_ April 1954 TN 3168 A NEW HODOGRAPH FORFREE-STREAMLINE THEORY_ Anatol Roshko_July TN 3169 ONTHEDRAG ANDSHEDDING FREQUENCY OF TWO-DIMENSIONAL BLUFF BODIES_ Anatol Roshko_July 1954 TN 3171 SOME NEW DRAG DATAONTHENACA RM-10MISSILEANDA CORRELATION OF THEEXISTINGDRAG MEASUREMENTS AT M = 1.6 AND3.0_ Robert J° Carros and Carlton S. James_June 1954 TN 3173 A STUDY OF HYPERSONIC SMALL-DISTURBANCE THEORYj Milton D. Van Dyke_ May 1954 TN 3175 DOWNWASH CHARACTERISTICS ANDVORTEX-SHEET SHAPE BEHIND A 63° SWEPT- BACK WING-FUSELAGE COMBINATION AT A REYNOLDS NUMBER OF 6.1xI06_ William H. Tolhurst_ Jr._ May 1954 TN 3176 WALLINTERFERENCE IN WINDTUNNELS WITHSLOTTED ANDPOROUS BOUNDAR- IES AT SUBSONIC SPEEDS_ Barrett S. Baldwin_ Jr._ John B. Turner_ and Earl D. Knechtel_ May 1954 TN 3177 ION TRACER TECHNIQUE FORAIRSPEED MEASURI_MENT AT LOW DENSITIES_ W. B. Kunkel and L. Talbot_ March 1954 TN 3178 CHARACTERISTICS OF TURBULENCE IN A BOUNDARY LAYER WITHZERO PRES- SURE GRADIENT_ P. S. Klebanoff_ July 1954 TN 3181 EXPERIMENTAL INVESTIGATION OF HEAT-TRANSFER ANDFLUID-FRICTION CHAR- ACTERISTICS OF WHITE FUMING NITRICACID_ Bruce A. Reese and Robert W. Graham_ May 1954 TN 3183 MINIMUM-WAVE-DRAG AIRFOIL SECTIONS FORARROW WINGS_ Morton Cooper and Frederick C. Grant_ May 1954 TN 3185 TABLES FORTHECOMPUTATION OFWAVE DRAG ORARROW WINGS OF ARBITRARY AIRFOIL SECTION_ Morton Cooper and Frederick C. Grant_ June 1954 TN 3186 EVALUATION OF THEACCURACY OFAN AIRCRAFT RADIO ALTIMETER FORUSE IN A METHOD OFAIRSPEED CALIBRATION_ Jim R. Thompson and Max C.

Kurbjun_ May 1954 TN 3189 MINIMUM-DRAGAND POINTED BODIES OFREVOLUTION BASED ONLINEARIZED SUPERSONIC THEORY_ HermanM. Pamker_May 1954 TN 3193 AN EXPLORATORY INVESTIGATION OF SKINFRICTION ANDTRANSITION ON THREE BODIES OF REVOLUTION AT A MACH NUMBER OF 1.61_ John H. Hilton_ Jr._ and K. R. Czarneckij June 1954 TN 3196 LIFT ANDPITCHING MOMENT AT SUPERSONIC SPEEDS DUETO CONSTANT VERTI- CALACCELERATION FORTHIN SWEPTBACK TAPERED WINGS WITHSTREAMWISE TIPS. SUPERSONIC LEADING ANDTRAILINGEDGES_ Isabella J. Cole and Kenneth Margolis_ June 1954 TN 3205 THEORETICAL INVESTIGATION AT SUBSONIC SPEEDS OF THEFLOW AHEAD OF A SLENDER INCLINED PARABOLIC-ARC BODY OF REVOLUTION ANDCORRELATION WITHEXPERIMENTAL DATAOBTAINED AT LOWSPEEDS_ William Letko and Edward C. B. Danforth_ III_ July 1954 TN 3208 HEAT_ MASS_ ANDMOMENTUM TRANSFER FORFLOW OVER A FLATPLATEWITH BLOWING ORSUCTION_ H. S. Mickley_ R. C. Ross_A. L. Squyers_ and W. E. Stewart_ July 1954 TN 3210 THEROLE OF TRIPLECOLLISIONS IN EXCITATION OFMOLECULAR VIBRATIONS IN NITROUS OXIDE_Richard A. Walker_ ThomasD. Rossing_ and Sam Legrold_ May 1954 TN 3213 TRANSONIC FLOW PASTCONE CYLINDERS_ GeorgeE. Solomon_September TN 3218 FLIGHTDETERMINATION OF THEDRAG ANDPRESSURE RECOVERY OF AN NACA 1-40-250 NOSE INLETAT MACH NUMBERS FROM 0.9 TO 1.8_ R. I. Sears and C. F. Merlet_ July 1955 TN 3219 VISCOSITY CORRECTIONS TO CONE PROBES IN RAREFIED SUPERSONIC FLOW AT A NOMINAL MACH NUMBER OF 4_ L. Talbot_ November1954 TN 3222 MEASUREMENT OF HEATTRANSFER IN THETURBULENT BOUNDARY LAYER ONA FLATPLATEIN SUPERSONIC FLOW ANDCOMPARISON WITHSKIN-FRICTION RESULTS_ C. C. Pappas_June 1954 TN 3223 AN ANALYSIS OF SHOCK-WAVE CANCELLATION ANDREFLECTION FORPOROUS WALLS WHICH OBEY AN EXPONENTIAL MASS-FLOW PRESSURE-DIFFERENCE RELATION_ Joseph M. Spiegel and Phillips J. Tunnell_ August 1954 TN 3225 AN EXPERIMENTAL STUDY OF THELIFT ANDPRESSURE DISTRIBUTION ONA DOUBLE-WEDGE PROFILE AT MACH NUMBERS NEARSHOCK ATTACHMENT_ Walter G. Vincenti_ DuaneW. Dugan_and E. Ray Phelps_ July 1954 TN 3226 SOME POSSIBILITIESOFUSINGGASMIXTURES OTHER THAN AIR IN AERODYNAMIC RESEARCH_ Dean R. Chapman 3 August 1954 TN 3229 THESMALL-DISTURBANCE METHOD FORFLOW OFA COMPRESSIBLE FLUID WITH VELOCITY POTENTIAL ANDSTREAM FUNCTION AS INDEPENDENT VARIABLES_ Carl Kaplan_ August 1954 TN 3230 INVESTIGATION OF DISTRIBUTED SURFACE ROUGHNESS ONA BODY OF REVOLU- TIONAT A MACH NUMBER OF 1.613 K. R. Czarnecki_ Ross B. Robinson_ and John H. Hilton_ Jr._ June 1954 TN 3234 REDUCTION OF HELICOPTER PARASITE DRAG_ Robert D. Harrington_ August TN 3237 HOVERING PERFORMANCE OF A HELICOPTER ROTOR USINGNACA8-H-12 AIR- FOIL SECTIONS_ Robert D. Powell_ Jr._ August 1954 TN 3238 REVIEW OF INFORMATION ONINDUCED FLOW OF A LIFTING ROTOR_ Alfred Gessow_ August 1954 TN 3241 AIRFOIL SECTION CHARACTERISTICS AT HIGHANGLES OF ATTACK_ Laurence K. Loftin_ Jr._ August 1954 PRELIMINARY RESULTS FROM FLOW-FIELD MEASUREMENTS AROUND SINGLE AND TN 3242 TANDEM ROTORS IN THELANGLEY FULL-SCALE TUNNEL_ Harry H. Heyson_ November1954 THEORETICAL ANALYSIS OF ANAIRPLANE ACCELERATION RESTRICTOR CON- TN 3243 TROLLED BYNORMAL ACCELERATION_ PITCHING ACCELERATION_ ANDPITCH- ING VELOCITY_ Christopher C. Kraft_ Jr._ September 1954 TN 3249 THEHYDRODYNAMIC CHARACTERISTICS OFAN ASPECT-RATIO-O.125 MODIFIED RECTANGULAR FLATPLATE OPERATING NEAR A FREEWATER SURFACE_ John A. Ramsen and Victor L. Vaughan_Jr._ October 1954 DESCRIPTION ANDPRELIMINARY FLIGHTINVESTIGATION OF AN INSTRUMENT FOR TN 3252 DETECTING SUBNORMAL ACCELERATION DURING TAKE-OFF_ Garland J. Morris and Lindsay J. Lina_ November1954 TN 3255 SHOCK-TURBULENCE INTERACTION ANDTHEGENERATION OF NOISE_H. S.

Ribner_ July 1954 TN 3256 EXPERIMENTAL INVESTIGATION OF TEMPERATURE RECOVERY FACTORS ONA i0 ° CONE AT ANGLE OFATTACK AT A MACH NUMBER OF 3.12_ John R° Jack and Barry Moskowitz_ July 1954 TN 3258 INVESTIGATION OFMACH NUMBER CHANGES OBTAINED BYDISCHARGING HIGH- PRESSURE PULSE THROUGH WINDTUNNEL OPERATING SUPERSONICALLY_ Rudolph C. Haefeli and Harry Bernstein_ August 1954 STARTING ANDOPERATING LIMITS OFTWO SUPERSONIC WINDTUNNELS UTILIZ- TN 3262 ING AUXILIARY AIR INJECTION DOWNSTREAM OF THETESTSECTION_ Henry R. Hunczak and Morris D. Rousso_September 1954 STUDY OF THE°MOMENTUM DISTRIBUTION OF TURBULENT BOUNDARY LAYERS IN TN 3264 ADVERSE PRESSURE GRADIENTS_ Virgil A. Sandbornand Raymond J. Slo- gar_ January 1955 VAPORIZATION RATES ANDDRAG COEFFICIENTS FORISOOCTANE SPRAYS IN TN 3265 TURBULENT AIR STREAMS_ Robert D. Ingebo_ October 1954 TN 3267 BOUNDARY-LAYER TRANSITION AT MACH 3.12 WITHANDWITHOUT SINGLE ROUGHNESS ELEMENTS_ Paul F. Brinch_ December1954 ATTENUATION IN A SHOCK TUBEDUETOUNSTEADY-BOUNDARY-LAYER ACTION_ TN 3278 Harold Mirels_ August 1956 TN 3283 AERODYNAMIC FORCES_ MOMENTS_ ANDSTABILITYDERIVATIVES FORSLENDER BODIES OF GENERAL CROSS SECTION_ Alvin H. Sacks_ November1954 EXAMINATION OF THEEXISTINGDATA ONTHEHEATTRANSFER OF TURBULENT TN 3284 BOUNDARY LAYERS AT SUPERSONIC SPEEDS FROM THEPOINTOF VIEWOF REYNOLDS ANALOGY_ Alvin Seiff_ August 1954 TN 3287 HEAT TRANSFER FROM A H]_ISPHERE-CYLINDER EQUIPPED WITH FLOW- SEPARATION SPIKES_ Jackson R. Stalder and Helmer V. Nielsen_ September 1954 TN 3289 THE MINIMIZATION OF WAVE DRAG FOR WINGS AND BODIES WITH GIVEN BASE AREA OR VOLUME_ Max. A. Heaslet 3 July 1957 TN 3296 SEPARATION 3 STABILITY_ AND OTHER PROPERTIES OF COMPRESSIBLE LAMINAR BOUNDARY LAYER WITH PRESSURE GRADIENT AND HEAT TRANSFER_ Morris Morduchow and Richard G. Grape 3 May 1955 TN 3298 A LOW-DENSITY WIND-TUNNEL STUDY OF SHOCK-WAVE STRUCTURE AND RELAXA- TION PHENOMENA IN GASES_ F. S. Sherman_ July 1955 TN 3299 MAXIMUM THEOREMS AND REFLECTIONS OF SIMPLE WAVES_ P. Germain_ June TN 3300 INVESTIGATION OF LIFT_ DRAG AND PITCHING MOMENT OF A 600 DELTA- WING-BODY COMBINATION (AGARD CALIBRATION MODEL _ IN THE LANGLEY 9-1NCH SUPERSONIC TUNNEL_ August F. Bromm_ Jr._ September 1954 TN 3303 TURBULENT-HEAT-TRANSFER MEASUREMENTS AT A MACH NUMBER OF 3.03_ Maurice J. Brevoort and Bernard Roshis 3 September 1954 TN 3304 INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF A MODEL WING- PROPELLER COMBINATION AND OF THE WING AND PROPELLER SEPARATELY AT ANGLES OF ATTACK UP TO 90°_ John W. Draper and Richard E. Kuhn_ November 1954 TN 3306 AN INVESTIGATION OF A LIFTING 10-PERCENT THICK SYMMETRICAL DOUBLE- WEDGE AIRFOIL AT MACH NUMBERS UP TO 13 Milton D. Humphreys_ November 1954 TN 3307 AN INVESTIGATION OF A WING-PROPELLER CONFIGURATION EMPLOYING LARGE- CHORD PLAIN FLAPS AND LARGE-DIAMETER PROPELLERS FOR LOW-SPEED FLIGHT AND VERTICAL TAKE-OFF 3 Richard E. Kuhn and John W. Draper_ December TN 3313 SOME MEASUREMENTS OF ATMOSPHERIC TURBULENCE OBTAINED FROM FLOW- DIRECTION VANES MOUNTED ON AN AIRPLANE_ Robert G. Chilton_ November TN 3317 DESIGN CONSIDERATIONS FOR WINGS HAVING MINIMUM DRAG DUE TO LIFT_ Warren A. Tucker 3 December 1954 TN 3320 FLIGHT MEASUREMENTS OF DRAG AND BASE PRESSURE OF A FIN-STABILIZED PARABOLIC BODY OF REVOLUTION (NACA RM-IO) AT DIFFERENT REYNOLDS NUMBERS AND AT MACH NUMBERS FROM 0.9 TO 3.3_ H. Herbert Jackson 3 Charles B. Rumsey_ and Leo T. Chauvin_ November 1954 TN 3322 AN ACCURATE ANDRAPIDMETHOD FORTHEDESIGN OF SUPERSONIC NOZZLES_ Ivan E. Beckwith and John A. Moore_ February 1955 TN 3323 CHARTS FORESTIMATING PERFORMANCE OF HIGH-PERFORMANCE HELICOPTERS_ Alfred Gessowand Robert J. Topscott_ January 1955 TN 3338 A DYE-TRACER TECHNIQUE FOREXPERIMENTALLY OBTAINING IMPINGEMENT CHARACTERISTICS OFARBITRARY BODIES ANDA METHOD FORDETERMINING DROPLET SIZE DISTRIBUTION_ UweH. von Glahn_ ThomasF. Gelder_ and William H. Smyers_Jr._ March 1955 TN 3340 GENERALIZATION OF GAS-FLOW-INTERFEROMETRY THEORY ANDINTERFEROGRAM EVALUATION EQUATIONS FORONE-DIMENSIONAL DENSITY FIELDS_Walton L. Howesand Donald R. Buchele_ February 1955 TN 3341 AN ANALYTICAL ESTIMATION OF THEEFFECT OF TRANSPIRATION COOLING ONTHEHEAT-TRANSFER ANDSKIN-FRICTION CHARACTERISTICS OFA COM- PRESSIBLE TURBULENT BOUNDARY LAYER_ Morris W, Rubesin_ December TN 3343 SUBSONIC EDGES IN THIN-WING ANDSLENDER-BODY THEORY_ Milton D.

Van Dyke_November1954 TN 3344 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OF AERODYNAMIC-HEATING ANDISOTHERMAL HEAT-TRANSFER PARAMETERS ONA HEMISPHERICAL NOSE WITHLAMINAR BOUNDARY LAYER AT SUPERSONIC MACHNUMBERS_ Howard A. Stine and Kent Wanlass_ December1954 ARRANGEMENT OFFUSIFORM BODIES TO REDUCE THEWAVE DRAG AT SUPER- TN 3345 SONICSPEEDS_ Morris D. Friedman and Doris Cohen_November1954 TN 3346 PREDICTION OF DOWNWASH BEHIND SWEPT-WING AIRPLANES AT SUBSONIC SPEED_ John DeYoungand Walter H. Barling_ Jr._ January 1955 TN 3349 APPLICATION OF THEGENERALIZED SHOCK-EXPANSION METHOD TO INCLINEDBODIES OF REVOLUTION TRAVELING AT HIGHSUPERSONIC AIRSPEEDS_ Raymond C. Savin_ April 1955 PRELIMINARY INVESTIGATION OF A STICKSHAKER AS A LIFT-MARGIN INDI- TN 3355 CATOR_ James P. Trant_ Jr._ February 1955 SOME EFFECTS OFPROPELLER OPERATION ANDLOCATION ONABILITY OF A TN 3360 WING WITHPLAINFLAPSTO DEFLECT PROPELLER SLIPSTREAMS DOWNWARD FORVERTICAL TAKE-OFF_ John W. Draper and Richard E. Kuhn_ January 1955 TN 3363 LOW-SPEED WIND-TUNNEL INVESTIGATION OF TRIANGULAR SWEPTBACK AIR INLET IN THEROOT OF A 45° SWEPTBACK WING_ Arvid L. Keith_ Jr._ and Jack Schiff_ January 1955 TN 3369 MINIMUM-DRAG BODIES OF REVOLUTION IN A NONUNIFORM SUPERSONIC FLOW FIELD_ Conard Rennemann_ Jr._ February 1955 TN 3372 FLIGHTMEASUREMENTS OF BASE PRESSURE ONBODIES OF REVOLUTION WITH ANDWITHOUT SIMULATED ROCKET CHAMBERS_ Robert F. Peck_ April 1955 TN 3374 TURBULENT-HEAT-TRANSFER MEASUREMENTS AT A MACH NUMBER OF 2.06_ Maurice J. Brevoort and Bernard Rashis_ March 1955 TN 3377 FLIGHTMEASUR_ENTS OF THEVELOCITY DISTRIBUTION ANDPERSISTENCE OF THETRAILINGVORTICES OF AN AIRPLANE_ Christopher C. Kraft_ Jr._ March 1955 TN 3381 HEAT-LOSS CHARACTERISTICS OF HOT-WIRE AN_OMETERS AT VARIOUS DENSI- TIES IN TRANSONIC ANDSUPERSONIC FLOW_ W. G. Spangenberg_May 1955 TN 3382 EXPERIMENTS WITHA ROTATING-CYLINDER VISCOMETER AT HIGHSHEAR RATES_ J. A. Cole_ R. E. Peterson# and H. W. Emmons# June 1955 TN 3383 INVESTIGATION OFTHETURBULENT BOUNDARY LAYER ONA YAWED FLATPLATE_ Harry Ashkenas and Frederick R. Riddell_ April 1955 TN 3388 A FIBROUS-GLASS COMPACT AS A PERMEABLE MATERIAL FORBOUNDARY-LAYER- CONTROL APPLICATIONS USINGAREA SUCTION_ R. E. Dannenberg_J. A.

Weiberg_ and B. J. Gambucci_January 1955 TN 3389 AXIALLYSYMMETRIC SHAPES WITHMINIMUM WAVE DRAG_ Max. A. Heaslet and Franklyn B. Fuller_ February 1955 SECOND-ORDER SUBSONIC AIRFOIL-SECTION THEORY ANDITS PRACTICAL TN 3390 APPLICATION_ Milton D. Van Dyke_March 1955 TN 3391 FREE-FLIGHT MEASUREMENTS OF TURBULENT BOUNDARY-LAYER SKINFRICTION IN THEPRESENCE OF SEVERE AERODYNAMIC HEATING MACH NUMBERS FROM 2.8 TO 7.0_ SimonC. Sommer and Barbara J. Short_ March 1955 TN 3392 TWO MINIATURE TEMPERATURE RECORDERS FORFLIGHTUSE_John V. Foster_ April 1955 TN 3393 AN EXPERIMENTAL INVESTIGATION OF THEBASE PRESSURE CHARACTERISTICS OFNON-LIFTING BODIES OF REVOLUTION AT MACHNUMBERS FROM 2.73 TO 4.98_ John O. Reller_ Jr._ and Frank M. Hamaker_March 1955 TN 7401 LAMINAR BOUNDARY LAYER BEHIND SHOCK ADVANCING INTO STATIONARY FLUID_ Harold Mirels_ March 1955 TN 3404 THECOMPRESSIBLE LAMINAR BOUNDARY WITHFLUID INJECTION_ GeorgeM.

Low#March 1955 TN 3406 A SELF-EXCITED_ ALTERNATING-CURRENT CONSTANT-T_fPERATURE HOT-WIRE AN_OMETER_ Charles E. Shepard#April 1955 TN 3411 PRESSURE WAVES GENERATED BYADDITION OF HEATIN A GASEOUS MEDIUM_ Boa-TehChu_ June 1955 TN 3416 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OF THEEFFECT OF TUNNEL WALLS ONTHEFORCES ONAN OSCILLATING AIRFOIL IN TWO-DIMENSIONAL SUBSONIC COMPRESSIBLE FLOW_ Harry L. Runyan_Donald S. Woolston_ and A. Gerald Rainey_ June 1955 TN 3418 THEZERO-LIFT WAVE DRAG OF A PARTICULAR FAMILYOFUNSWEPT_ TAPERED WINGS WITHLINEARLY VARYING THICKNESS RATIO_Arthur Henderson_Jr._ and Julia M. Goodwin_May 1955 TN 3419 NACA MODEL INVESTIGATIONS OF SEAPLANES IN WAVES_ John B. Parkinson_ July 1955 TN 3420 HYDRODYNAMIC TARES ANDINTERFERENCE EFFECTS FORA 12-PERCENT- THICKSURFACE-PIERCING STRUT ANDAN ASPECT-RATIO-0.25 LIFTING SURFACE_ John A. Ramsen and Victor L. Vaughan_Jr._ April 1955 TN 3421 AERODYNAMICS OFA RECTANGULAR WING OF INFINITE ASPECT RATIOAT HIGHANGLES OF ATTACK ANDSUPERSONIC SPEEDS_ John C. Martin and Frank S. Malvestuto_ Jr._ July 1955 TN 3424 AERODYNAMIC CHARACTERISTICS OF SEVERAL 6-PERCENT-THICK AIRFOILS AT ANGLES OFATTACK FROM 0° TO 20° AT HIGHSUBSONIC SPEEDS_ Bernard N. Daley and Douglas R. Lord_ May 1955 TN 3428 GROUND-SIMULATOR STUDY OFTHEEFFECTS OFSTICKFORCE ANDDISPLACE- MENT ONTRACKING PERFORMANCE_ Stanley Faber_ April 1955 TN 3430 ONSLENDER DELTA WINGS WITHLEADING EDGE SEPARATION_ Clinton E.

Brownand William H. Michael_ Jr._ April 1955 TN 3433 TOTAL LIFT ANDPITCHING MOMENT ONTHINARROWHEAD WINGS OSCILLATING IN SUPERSONIC POTENTIAL FLOW_ H. J. Cunningham_ May 1955 TN 3435 A STATISTICAL STUDY OF WING LIFT AT GROUND CONTACT FORFOUR TRANS- PORT AIRPLANES_ Dean C. Lindquist_ April 1955 TN 3438 ONTHEKERNEL FUNCTION OF THEINTEGRAL EQUATION RELATING LIFT AND DOWNWASH DISTRIBUTIONS OF OSCILLATING WINGS IN SUPERSONIC FLOW_ Charles E. Watkins and Julian H. Bermanj May 1955 TN 3439 ANALYSIS OF EARFORMATION IN DEEP-DRAWN CUPS_ Arthur J. McEnly_ Jr._ May 1955 TN 3440 HOVERING FLIGHTTESTS OFA FOUR-ENGINE TRANSPORT VERTICAL TAKE-OFF AIRPLANE MODEL UTILIZINGA LARGE FLAPANDEXTENSIBLE VANES FOR REDIRECTING THEPROPELLER SLIPSTREAM_ Louis P. Tostiand Edwin E.

Davenport_ May 1955 TN 3441 AN NACA VANE-TYPE ANGLE-OF-ATTACK INDICATOR FORUSEAT SUBSONIC ANDSUPERSONIC SPEEDS_ Jesse L. M. Mitchell and Robert F. Peck_ May 1955 TN 3442 A PRELIMINARY INVESTIGATION OF AERODYNAMIC CHARACTERISTICS OF SMALL INCLINED AIR OUTLETS AT TRANSONIC MACH NUMBERS_ Paul E. Dewey_ May 1955 TN 3451 ANALYSIS OF FULLYDEVELOPED TURBULENT HEATTRANSFER ANDFLOW IN AN ANNULUS WITHVARIOUS ECCENTRICITIES_ Robert G. Deissler and Maynard F. Taylor_ May 1955 TN 3453 LONGITUDINAL TURBULENT SPECTRUM SURVEY OF BOUNDARY LAYERS IN AD- VERSE PRESSURE GRADIENTS_ Virgil A. Sandborn and RaymondJ. Slogar_ May 1955 TN 3454 EFFECT OF A DISCONTINUITY ONTURBULENT BOUNDARY-LAYER-THICKNESS PARAMETER WITHAPPLICATION TO SHOCK-INDUCED SEPARATION_ Eli Reshotko and Maurice Tucker_ May 1955 TN 3455 RECOVERY ANDTIME-RESPONSE CHARACTERISTICS OF SIX THERMOCOUPLE PROBES IN SONIC ANDSUPERSONIC FLOW_ TrumanM. Stickney_ July 1955 TN 3561 TURBULENT-HEAT-TRANSFER MEASUR_ENTS AT A MACHNUMBER OF 1.62_ Maurice J. Brevoort and Bernard Rashis_ June 1955 TN 3466 AN INVESTIGATION OF THEDISCHARGE ANDDRAG CHARACTERISTICS OF AUXILIARY-AIR OUTLETS DISCHARGING INTOA TRANSONIC STREAM_ Paul E.

Deweyand Alley R. Vick_ July 1955 TN 3468 EFFECTS OF SWEEP ONTHEMAXIMUM-LIFT CHARACTERISTICS OFFOUR ASPECT-RATIO-4 WINGS AT TRANSONIC SPEEDS_ ThomasR. Turner_ July TN 3469 SUMMARY OF RESULTS OBTAINED BY TRANSONIC-BUMP METHOD ONEFFECTS OF PLANFORM ANDTHICKNESS ONLIFT ANDDRAG CHARACTERISTICS OF WINGS AT TRANSONIC SPEEDS_ Edward C. Polhamus_November1955 TN 3472 FLOW STUDIES ONFLAT-PLATE DELTA WINGS AT SUPERSONIC SPEED_ William H. Michael_ Jr._ July 1955 TN 3476 CALCULATED SPANWISE LIFT DISTRIBUTIONS ANDAERODYNAMIC INFLUENCE COEFFICIENTS FORSWEPT WINGS IN SUBSONIC FLOW_ Franklin W. Diederich and Martin Zlotnick_ October 1955 TN 3477 HYDRODYNAMIC PRESSURE DISTRIBUTIONS OBTAINED DURING A PLANING INVESTIGATION OF FIVE RELATED PRISMATIC SURFACES_ Walter J. Kapryan and GeorgeM. Boyd_ Jr._ September 1955 TN 3478 ONBOATTAIL BODIES OF REVOLUTION HAVING MINIMUM WAVE DRAG_ Keith C. Harder and Conrad Rennemann_ Jr._ August 1955 TN 3482 SUPPL_ENTARY CHARTS FORESTIMATING PERFORMANCE OF HIGH-PERFORMANCE HELICOPTERS_ Robert J. Topscott and Alfred Gessow_ July 1955 TN 3485 AN APPROXIMATE SOLUTION FORAXIALLYSYMMETRIC FLOW OVER A CONE WITH AN ATTACHED SHOCK WAVE_ Richard A. Hord_ October 1955 TN 3486 MEASUREMENTS OFTURBULENT SKINFRICTION ONA FLATPLATEAT TRAN- SONICSPEEDSj Raimo J. Hakkinen_ September 1955 TN 3487 ACOUSTIC RADIATION FROM TWO-DIMENSIONAL RECTANGULAR CUTOUTS IN AERODYNAMIC SURFACES_ K. Krishnamurtz_ August 1955 TN 3489 CONTRIBUTIONS ONTHEMECHANICS OF BOUNDARY-LAYER TRANSITION_ G. B.

Schubauer and P. S. Klebanoff_ September 1955 TN 3494 SOUND PROPAGATION INTOTHESHADOW ZONE IN A T_>IPERATURE-STRATIFIED ATMOSPHERE ABOVE A PLANEBOUNDARY_ David C. Pridmore-Brown and Uno Ingard_ October 1955 EXPLORATORY INVESTIGATION OF AN AIRFOILWITHAREASUCTION APPLIED TN 3498 TO A POROUS_ ROUND TRAILINGEDGE FITTEDWITHA LIFT-CONTROL VANE_ Robert E. Donnenbergand JamesA. Weibergj April 1955 TN 3499 CALCULATION OF THESUPERSONIC PRESSURE DISTRIBUTION ONA SINGLE- CURVED TAPERED WINGIN REGIONS NOTINFLUENCED BYTHEROOT ORTIP_ Walter G. Vincenti and Newman H. Fisher_ Jr._ June 1955 .TN3501 THETFANSONIC CHARACTERISTICS OF 22 RECTANGULAR_ SYMMETRICAL WING MODELSOF VARYING ASPECT RATIOANDTHICKNESS_ Warren H. Nelson and John B. McDevitt_ June 1955 TN 3502 THETRANSONIC CHARACTERISTICS OF 38 CAMBERED RECTANGULAR WINGS OF VARYING ASPECT RATIOANDTHICKNESS AS DETERMINED BYTHETRANSONIC- BUMP TECHNIQUE_ Warren H. Nelson and Walter J. Krunma_ June 1955 TN 3503 REDUCTION OF PROFILE DRAG AT SUPERSONIC VELOCITIES BYTHEUSEOF AIRFOIL SECTIONS HAVING A BLUNT TRAILINGEDGE_ Dean R. Chapman_ September 1955 TN 3504 EFFECT OFTRAILING-EDGE THICKNESS ONLIFT AT SUPERSONIC VELOCITIES_ Dean R. Chapman and Robert H. Hester_ June 1955 TN 3505 AN EXPERIMENTAL INVESTIGATION OF REGIONS OF SEPARATED LAMINAR FLOW_ Donald E. Gault_ September 1955 TN 3507 PRACTICAL CONSIDERATIONS IN SPECIFIC APPLICATIONS OF GAS-FLOW INTERFEROMETRY_ Walton L. Howesand Donald R. Buchele_ July 1955 TN 3508 LAMINAR FREECONVECTION ONA VERTICAL PLATE WITHPRESCRIBED NON- UNIFORM WALL HEATFLUXORPRESCRIBED NONUNIFORM WALL TEMPERATURE_ E. M. Sparrow_ July 1955 A STUDY OF BOUNDARY-LAYER TRANSITION ANDSURFACE TI_[PERATURE DIS- TN 3509 TRIBUTIONS AT MACH 3.12_ Paul F. Brinich_ July 1955 AN AUTOMATIC VISCOMETER FORNON-NEWTONIAN MATERIALS_ Ruth N. Welt- TN 35i0 mannand Perry W. Kuhns_ August 1955 EXTRAPOLATION TECHNIQUES APPLIEDTOMATRIX METHODS IN NEUTRON DIF- TN 3511 FUSION PROBLEMS_ Robert R. McCready_July 1955 HEAT TRANSFER AT THEFORWARD STAGNATION POINTOF BLUNT BODIES_ TN 3513 Eli Reshotko and Clarence B. Cohen_July 1955 ROTATING-STALL CHARACTERISTICS OF A ROTOR WITHHIGHHUB-TIPRADIUS TN 3518 RATIO_Eleanor L. Costilow and Merle C. Huppert_ August 1955 MEASUREMENTS OF THEEFFECTS OF FINITE SPAN ONTHEPRESSURE DISTRI- TN 3522 BUTION OVER DOUBLE-WEDGE WINGS AT MACH NUMBERS NEARSHOCK ATTACH- MENT_ Walter G. Vincenti_ September 1955 VORTEX INTERFERENCE ONSLENDER AIRPLANES_ Alvin H. Sacks_ November TN 3525 FLIGHTCALIBRATION OF FOUR AIRSPEED SYSTEMS ONA SWEPT-WING AIR- TN 3526 PLANE AT MACH NUMBERS UP TO 1.04 BYTHENACA RADAR-PHOTO-THEODOLITE METHOD_ Jim Rogers Thompson_ Richard S. Bray_ and George E.

Cooper_November1955 A SECOND-ORDER SHOCK-EXPANSION METHOD APPLICABLE TO BODIES OF REVO- TN 3527 LUTIONNEAR ZERO LIFT_ Clarence A. Syvertson and David H. Dennis_ January 1956 A THEORETICAL STUDY OF THEAERODYNAMICS OF SLENDER CRUCIFORM-WING TN 3528 ARRANGEMENTS ANDTHEIRWAKES_ John R. Spreiter and Alvin H. Sacks_ March 1956 TN 3529 THETRANSONIC CHARACTERISTICS OF 36 SYMMETRICAL WINGS OF VARYING TAPER_ ASPECT RATIO_ANDTHICKNESS AS DETERMINED BY THETRANSONIC- BUMP TECHNIQUE_ Warren H. Nelsonj Edwin C. Allen_ and Walter J° Krumm_December1955 MINIMUM WAVE DRAG FORARBITRARY ARRANGEMENTS OF WINGS ANDBODIES_ TN 3530 Robert T. Jones# February 1966 EXPLORATORY INVESTIGATION OF BOUNDARY-LAYER TRANSITION ONA HOLLOW TN 3546 CYLINDER AT A MACH NUMBER OF 6.9_ Mitchel H. Bertram_ May 1966 TN 3548 FLIGHTINVESTIGATION AT MACHNUMBERS FROM 0.6 TO 1.7 TO DETERMINE DRAG ANDBASE PRESSURES ONA BLUNT-TRAILING-EDGE AIRFOILANDDRAG OF DIAMOND ANDCIRCULAR-ARC AIRFOILSAT ZERO LIFT_ John D. Moore_ Ellis Katz_ November1955 FLIGHTINVESTIGATION AT MACH NUMBERS FROM 0.8 TO 1.5 TO DETERMINE TN 3549 THEEFFECTS OFNOSE BLUNTNESS ONTHETOTAL DRAG OF TWO FIN- STABILIZED BODIES OF REVOLUTION_ Roger G. Hart_ December1955 TN 3550 MEASUREMENTS OF THEEFFECT OF TRAILING-EDGE THICKNESS ONTHEZERO- LIFT DRAG OF THIN LOW-ASPECT-RATIO WINGS_ John D. Morrow_ November TN 3555 A METHOD FORCALCULATING THECONTOUR OF BODIES OF REVOLUTION WITHA PRESCRIBED PRESSURE GRADIENT AT SUPERSONIC SPEED WITHEXPERIMENTAL VERIFICATION_ Paige B. Burbank_March 1966 TN 3559 LAMINAR SEPARATION OVER A TRANSPIRATION-COOLED SURFACE IN COMPRES- SIBLEFLOW_ Morris Morduchow_December1955 TN 3561 INTENSITY_ SCALE_ ANDSPECTRA OF TURBULENCE IN MIXINGREGION OF FREESUBSONIC JET_ JamesC. Laurence_ September 1955 TN 3562 VARIATION OF BOUNDARY-LAYER TRANSITION WITHHEATTRANSFER ONTWO BODIES OF REVOLUTION AT A MACH NUMBER OF 3.12_ John R. Jack and Nick S. Diaconis_ September 1955 TN 3563 HEATLOSS FROM YAWED HOTWIRES AT SUBSONIC MACH NUMBERS_ Virgil A.

Sandborn_ and JamesC. Laurence_ September 1955 TN 3568 AVERAGING OFPERIODIC PRESSURE PULSATIONS BYA TOTAL-PRESSURE PROBE_ R. C. Johnson_ October 1955 TN 3569 COMPRESSIBLE LAMINAR BOUNDARY LAYER ANDHEATTRANSFER FORUNSTEADY MOTIONS OF A FLATPLATE_ SimonOstrach_ November1955 TN 3570 AN EXPERIMENTAL COMPARISON OF THELAGRANGIAN ANDEULERIAN CORRELA- TION COEFFICIENTS IN HOMOGENEOUS ISOTROPIC TURBULENCE_ William R.

Mickelsen_ October 1955 TN 3571 LIFT HYSTERESIS AT STALLAS AN UNSTEADY BOUNDARY-LAYER PHENOMENON_ Franklin K. Moore_ November1955 TN 3583 CHARTS OF BOUNDARY-LAYER MASS FLOW ANDMOMENTUM FORINLETPERFORM- ANCE ANALYSIS MACH NUMBER RANGE_ 0.2 TO 5.0_ Paul C. Simonand Kenneth L. Kowalski_ November1955 TN 3588 SUMMARY OF LAMINAR-BOUNDARY-LAYER SOLUTIONS FORWEDGE-TYPE FLOW OVER CONVECTION- ANDTRANSPIRATION-COOLED SURFACES_ John N. B.

Livingood_ Patrick L. Donoughe_December1955 TN 3592 AN OIL-STREAM PHOTOMICROGRAPHIC AEROSCOPE FOROBTAINING CLOUD LIQUID-WATER CONTENT ANDDROPLET SIZE DISTRIBUTIONS IN FLIGHT_ Paul T. Hacker_ January 1956 TN 3599 TURBULENT HEAT-TRANSFER MEASUREMENTS AT A MACH NUMBER OF 0.87_ Maurice J. Brevoot and Bernard Rashis_ December1955 TN 3601 PRESSURE RISE ASSOCIATED WITHSHOCK-INDUCED BOUNDARY-LAYER SEPARA- TION_EugeneS. Love_ December1955 TN 3606 TABULATION OF THEFUNCTIONS WHICH OCCUR IN THEAERODYNAMIC THEORY OF OSCILLATING WINGS IN SUPERSONIC FLOW_ Vera Huckel_ February 1956 TN 3607 EFFECT OFTHICKNESS_ CAMBER_ ANDTHICKNESS DISTRIBUTION ONAIRFOIL CHARACTERISTICS AT MACH NUMBERS UP TO 1.0_ Bernard N. Daley and Richard S. Dick_ March 1956 LINEARIZED LIFTING-SURFACE ANDLIFTING-LINE EVALUATIONS OF SIDEWASH TN 3609 BEHIND ROLLING TRIANGULAR WINGS AT SUPERSONIC SPEEDS_ Percy J.

Bobbitt_ March 1956 TN 3613 THEPROBLEM OF REDUCING THESPEED OFA JET TRANSPORT IN FLIGHT_Don D. Davis_ Jr._ December1955 TN 3614 FLOW STUDIES ONDROOPED-LEADING-EDGE DELTA WINGS AT SUPERSONIC SPEED_ William H. Michael_ Jr._ January 1956 TN 3615 AN EXPERIMENTAL INVESTIGATION OF THESCALE RELATIONS FORTHEIMPING- ING WATER SPRAY GENERATED BYA PLANING SURFACE_ Ellis E. McBride_ February 1956 TN 3617 THEORETICAL ANALYSIS OF LINKEDLEADING-EDGE ANDTRAILING-EDGE FLAP-TYPE CONTROLS AT SUPERSONIC SPEEDS_ E. Carson Yates_ Jr._ March 1956 TN 3623 CORRELATION OF SUPERSONIC CONVECTIVE HEAT-TRANSFER COEFFICIENTS FROM MEASUR_ENTS OF THESKINTEMPERATURE OF A PARABOLIC BODY OF REVOLU- TION (NACA RM-IO)_ Leo T. Chauvin and Carlos A. de Moraes_ March TN 3624 INVESTIGATION OFTHEUSEOF THETHERMAL DECOMPOSITION OF NITROUS OXIDETOPRODUCE HYPERSONIC FLOW OF A GASCLOSELY RESEMBLING AIR_ Alexander P. Sabol and John S. Evans_March 1956 TN 3626 EXPERIMENTAL INVESTIGATION OF THEFLOW AROUND LIFTING SYMMETRICAL DOUBLE-WEDGE AIRFOILSAT MACH NUMBERS OF 1.30_ Paul B. Gooderum_ GeorgeP. Wood_March 1956 TN 3627 BOUNDARY-LAYER GROWTH ANDSHOCK ATTENUATION IN A SHOCK TUBE WITH ROUGHNESS_ Paul W. Huber and Donald R. McFarland_ March 1956 TN 3628 AN ANALYSIS OF ESTIMATED ANDEXPERIMENTAL TRANSONIC DOWNWASH CHARACTERISTICS AS AFFECTED BYPLANFORM ANDTHICKNESS FORWINGAND WING-FUSELAGE CONFIGURATIONS_ Joseph Weil_ George S. Campbell_ and Margaret S. Diederich_ April 1956 TN 3629 INVESTIGATION OF THEEFFECTS OF GROUND PROXIMITY ANDPROPELLER POSITION ONTHEEFFECTIVENESS OFA WING WITHLARGE-CHORD SLOTTED FLAPSIN REDIRECTING PROPELLER SLIPSTREAMS DOWNWARD FORVERTICAL TAKE-OFF_ Richard E. Kuhn_March 1956 TN 3630 HOVERING-FLIGHT TESTS OF A MODEL OFA TRANSPORT VERTICAL-TAKE-OFF AIRPLANE WITHTILTINGWING ANDPROPELLERS_ Powell M. Lovell_ Jr._ Lysle P. Parlett_ March 1956 TN 3634 CALCULATIONS OF THERATEOFTHERMAL DISSOCIATION OF AIR BEHIND NORMAL SHOCK WAVES AT MACH NUMBERS OF I0_ 12_ AND14_ George P.

Wood_April 1956 TN 3637 FLIGHTINVESTIGATION OFTHEEFFECTIVENESS OFAN AUTOMATIC AILERON TRIM CONTROL DEVICE FORPERSONAL AIRPLANES_ William H. Phillips_ Helmutt A. Kuehnel_ and James B. Whitten_ April 1956 TN 3639 APPROXIMATE INDICIAL LIFT FUNCTIONS FORSEVERAL WINGS OF FINITE SPAN IN INCOMPRESSIBLE FLOW AS OBTAINED FROM OSCILLATORY LIFT COEFFICIENTS_ Joseph A. Drischler_ May 1956 TN 3641 WIND-TUNNEL INVESTIGATION OFA NUMBER OF TOTAL-PRESSURE TUBES AT HIGHANGLES OF ATTACK. SUBSONIC_ TRANSONIC_ ANDSUPERSONIC SPEEDS_ William Gracey_May 1956 EFFECT OF SHALLOW WATER ONTHEHYDRODYNAMIC CHARACTERISTICS OF A TN 3642 FLAT-BOTTOM PLANING SURFACE_ Kenneth W. Christopher_ April 1956 TN 3643 MEASURH_ENT OF AERODYNAMIC FORCES FORVARIOUS MEAN ANGLES OF ATTACK ONAN AIRFOIL OSCILLATING IN PITCHANDONTWO FINITE-SPAN WINGS OSCILLATING IN BENDING WITHEMPHASIS f_ DAMPING IN THESTALL_ A. Gerald Rainey_ May 1956 LIFT ANDMOMENT COEFFICIENTS FORAN OSCILLATING RECTANGULAR WING- TN 3644 AILERON CONFIGURATION IN SUPERSONIC FI_W_Julian H. Berman_July INVESTIGATION OF BOUNDARY-LAYER TRANSITION ONI0° CONE IN LANGLEY TN 3648 4- BY4-FOOTSUPERSONIC PRESSURE TUNNEL AT MACH NUMBERS OF 1.41_ 1.61_ AND2.01_ Archibald R. Sinclair and K. R. Czarnecki_ May 1956 TN 3650 RESULTS OF A FLIGHTINVESTIGATION TO DETERMINE THEZERO-LIFTDRAG CHARACTERISTICS OFA 60° DELTA WING WITHNACA65-006 AIRFOIL SECTION ANDVARIOUS DOUBLE-WEDGE SECTIONS AT MACH NUMBERS FROM 0.7 TO 1.6_ Clement J. Welsh_ April 1956 TN 3651 CROSS FLOWS IN LAMINAR INCOMPRESSIBLE BOUNDARY LAYERS_ Arthur G.

Hansenand HowardZ. Herzig 3 February 1956 TN 3652 EXPERIMENTAL INVESTIGATION OFAIR-FLOW UNIFORMITY ANDPRESSURE LEVELONWIRECLOTH FORTRANSPIRATION-COOLING APPLICATIONS_ Patrick L. Donougheand Ray A. McKinnon_January 1956 TN 3653 SOME EFFECTS OF BLUNTNESS ONBOUNDARY LAYER TRANSITION ANDHEAT TRANSFER AT SUPERSONIC SPEEDS_ W. E. Moeckel_ March 1956 EFFECT OFLEADING-EDGE GEOMETRY ONBOUNDARY-LAYER TRANSITION AT TN 3659 MACH 3.1_ Paul F. Brinich_ Jr._ March 1956 TN 3661 SELFSHIELDING IN RECTANGULAR ANDCYLINDRICAL GEOMETRIES_ Harold Schneider_ Paul G. Saper_ and Charles F. Kadow_April 1956 BODIES OF REVOLUTION HAVING MINIMUM DRAG AT HIGHSUPERSONIC AIR- TN 3666 SPEEDS_ A. J. Eggers_ Meyer M. Resnikoff_ and Davis H. Dennis_ February 1956 TN 3667 WING-BODY COMBINATIONS WITHCERTAIN GEOMETRIC RESTRAINTS HAVING LOW ZERO-LIFT WAVE DRAG AT LOWSUPERSONIC MACH NUMBERS_ Harvard Lomax_ February 1956 TN 3670 DETERMINATION OF VORTEX PATHS BYSERIESEXPANSION TECHNIQUE WITH APPLICATION TO CRUCIFORM WINGS_ Alberta Y. Alksne_ April 1956 TN 3671 WIND-TUNNEL INVESTIGATION OF THEEFFECT OF CLIPPINGTHETIPS OF TRIANGULAR WINGS OF DIFFERENT THICKNESS_ CAMBER, ANDASPECT RATIO - TRANSONIC BUMP METHOD_ Horace F. Emerson_June 1956 TN 3672 INVESTIGATION AT HIGHSUBSONIC SPEEDS OFA BODY-CONTOURING METHOD FORALLEVIATING THEADVERSE INTERFERENCE AT THEROOT OFA SWEPTBACK WING_ John B. McDevitt and William M. Haire_ April 1956 TN 3673 ONTHERANGE OFAPPLICABILITY OF THETRANSONIC AREA RULE_ John R.

Spreiter_ May 1956 TN 3674 THEORETICAL PRESSURE DISTRIBUTIONS FORSOME SLENDER WING-BODY COM- BINATIONS AT ZERO LIFT_ Paul F. Byrd_ April 1956 TN 3675 THEEFFECTS OF COMPRESSIBILITY ONTHEUPWASH AT THEPROPELLER PLANES OF A FOUR-ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING A WING WITH40° OF SWEEPBACK ANDAN ASPECT RATIOOF i0 _ Armando E. Lopez and Jerald K. Dickson_ July 1956 TN 3680 INTERACTION OF GRIDS WITHTRAVELING SHOCK WAVES_ Darshan Singh Dosanjh_ September 1956 TN 3682 TIME CORRELATOR FORPROBLEMS IN AERODYNAMICS_ George Tolmie Skinner_ June 1956 I_ 3689 INVESTIGATION BYTHETRANSONIC-BUMP METHOD OFA 35° SWEPTBACK SEMI- SPAN MODEL EQUIPPED WITHA FLAPOPERATED BYA SERIESOF SERVOVANES LOCATED AHEAD OF ANDGEARED TO THEFLAP_William H. Phillips and Robert F. Thompson_ April 1956 TN 3691 ANALYSIS ANDCOMPARISON WITHTHEORY OFFLOW-FIELD MEASUREMENTS NEAR A LIFTING ROTOR IN THELANGLEY FULL-SCALE TUNNEL_ Harry H.

Heyson_April 1956 TN 3692 INVESTIGATION AT ZERO FORWARD SPEED OF A LEADING-EDGE SLATAS A LONGITUDINAL CONTROL DEVICE FORVERTICALLY RISINGAIRPLANES THAT UTILIZE THEREDIRECTED-SLIPSTREAM PRINCIPLE_ Richard E. Kuhn_May PRELIMINARY INVESTIGATION OF THEEFFECTIVENESS OF A SLIDINGFLAP TN 3693 IN DEFLECTING A PROPELLER SLIPSTREAM DOWNWARD FORVERTICAL TAKE- OFF_Richard E. Kuhn_May 1956 TN 3697 FLIGHTTESTS AT SUPERSONIC SPEEDS TO DETERMINE THEEFFECT OF TAPER ONTHEZERO-LIFTDRAG OF SWEPTBACK LOW-ASPECT-RATIO WINGS_ Murray Pittel_ June 1956 TN 3700 ONSUBSONIC FLOW PASTA PARABOLOID OF REVOLUTION_ Carl Kaplan_ February 1957 TN 3702 MEASUREMENTS OF ATMOSPHERIC TURBULENCE OVER A WIDERANGE OF WAVE- LENGTH FORONE METEOROLOGICAL CONDITION_ Harold L. Crane and Robert G. Chilton_ June 1956 THEFLOW PASTAN UNSWEPT- ANDA SWEPT-WING-BODY COMBINATION AND TN 3703 THEIREQUIVALENT BODIES OF REVOLUTION AT MACH NUMBERS NEAR1.0_ Walter F. Lindsey_ June 1956 TN 3704 MINIMUM-DRAG DUCTED ANDCLOSED THREE-POINT BODY OF REVOLUTION BASED ONLINEARIZED SUPERSONIC THEORY_ HermanH. Parker_ December1956 TN 3706 INVESTIGATION OF THELAMINAR AERODYNAMIC HEAT-TRANSFER CHARACTERIS- TICS OFA HEMISPHERE-CYLINDER IN THELANGLEY II-INCH HYPERSONIC TUNNEL AT A MACH NUMBER OF 6.8_ Davis H. Crawford and William D.

McCauley_July 1956 INVESTIGATION AT SUPERSONIC SPEEDS OF THEVARIATION WITHREYNOLDS TN 3708 NUMBER ANDMACH NUMBER OF THETOTAL_ BASE_ ANDSKIN-FRICTION DRAG OF SEVEN BOATTA!L BODIES OF REVOLUTION DESIGNED FORMINIMUM WAVE DRAG_ August F. Brumm_ Jr._ Julia M. Goodwin_June 1956 TN 3709 AERODYNAMIC INVESTIGATION OF A PARABOLIC BODY OF REVOLUTION AT MACH NUMBER OF 1.92 ANDSOME EFFECTS OF AN ANNULAR SUPERSONIC JET EXHAUSTING FROM THEBASE_ Ellis E. McBride_ July 1956 BOUNDARY LAYER BEHIND SHOCK ORTHIN EXPANSION WAVE MOVING INTO TN 3712 STATIONARY FLUID_ Harold Mirels_ May 1956 THREE-DIMENSIONAL TRANSONIC FLOW THEORY APPLIED TO SLENDER WINGS TN 3717 ANDBODIES_ Max. A. Heaslet and John R. Spreiter_ July 1956 THEORETICAL WAVE DRAG OF SHROUDED AIRFOILSANDBODIES_ Paul F. Byrd_ TN 3718 June 1956 TN 3719 APPLICATION OF SCATTERING THEORY TOTHEMEASUREMENT OFTURBULENT DENSITY FLUCTUATIONS BYAN OPTICAL METHOD_ HowardA. Stine and Warren Winovich_ June 1956 TN 3720 COMPARISON BETWEEN EXPERIMENTAL ANDPREDICTED DOWNWASH AT A MACH NUMBER OF 0.25 BEHIND A WING-BODY COMBINATION HAVING A TRIANGULAR WINGOFASPECT RATIO2.0j NormanE. Sorensen and Edward J. Hopkins_ May 1956 TN 3721 AN EVALUATION OF FOUR EXPERIMENTAL METHODS FORMEASURING MEAN PROPER- TIES OFA SUPERSONIC TURBULENT BOUNDARY LAYER_ George J. Nothwang_ June 1956 TN 3722 GENERAL THEORY OF WAVE-DRAG REDUCTION FORCOMBINATIONS EMPLOYING QUASI-CYLINDRICAL BODIES WITHAN APPLICATION TO SWEPT-WING AND BODY COMBINATIONS_ Jack N. Nielson and William C. Pitts_ September TN 3723 CALCULATIONS OF THEFLOW OVER AN INCLINED FLATPLATEAT FREESTREAM MACH NUMBER I_ Walter G. Vincenti_ Cleo B. Wagoner_and Newman H.

Fusher_ Jr._ August 1956 TN 3725 AERODYNAMIC INTERFERENCE OF SLENDER WING-TAlLCOMBINATIONS_ Alvin H. Sachs_January 1957 TN 3734 TURBULENT-HEAT-TRANSFER MEASUR_IENTS AT A MACH NUMBER OF 3.90_ Maurice J. Brevoort_ July 1956 TN 3744 SUPERSONIC FLOW PASTNONLIFTING BUMPED ANDINDENTED BODIES OF REVOLUTION_ F. EdwardMcLeanand Conard Rennemann_ Jr._ September TN 3745 TRANSITION-FLIGHT TESTS OFA MODEL OFA LOW-WING TRANSPORT VERTICAL- TAKE-OFF AIRPLANE WITHTILTINGWING ANDPROPELLERS_ Powell M. Lovell_ Jr._ and Lysle P. Parlett_ September 1956 TN 3750 AN ANALYSIS OFAIRSPEED, ALTITUDEjANDACCELERATION DATAOBTAINED FROM A TWIN-ENGINE TRANSPORT AIRPLANE OPERATED OVER A FEEDER-LINE ROUTE IN THEROCKY MOUNTAINS_ Martin R. Coppand Mary W. Fetner_ October 1956 TN 3753 AERODYNAMIC CHARACTERISTICS ANDFLYINGQUALITIES OF A TAILLESS TRIANGULAR-WING AIRPLANE CONFIGURATION AS OBTAINED FROM FLIGHTS OF ROCKET-PROPELLED MODELS AT TRANSONIC ANDLOW SUPERSONIC SPEEDS_ Grady L. Mitcham and Joseph E. Stevens_ November1956 TN 3760 AERODYNAMIC MIXINGDOWNSTREAM FROM LINE SOURCE OF HEATIN HIGH- INTENSITY SOUND FIELD_ William R. Mickelsen and Lionel V. Baldwin_ August 1956 TURBULENT SHEAR SPECTRA ANDLOCALISOTROPY IN THELOW-SPEED BOUNDARY TN 3761 LAYER_ Virgil A. Sandbornand Willis H. Braun# September 1956 DRAG COEFFICIENTS FORDROPLETS ANDSOLIDSPHERES IN CLOUDS ACCELER- TN 3762 ATINGIN AIR-STREAMS_ Robert D. Ingebo# September 1956 ONPOSSIBLE SIMILARITYSOLUTIONS FORTHREE-DIMENSIONAL INCOMPRESSI- TN 3768 BLELAMINAR BOUNDARY LAYERS. I - SIMILARITYWITHRESPECT TO STATIONARY RECTANGULAR COORDINATES_ Arthur G. Hansenand HowardZ.

Herzig_ October 1956 HEAT-TRANSFER MEASUREMENTS ONTWO BODIES OF REVOLUTION AT A MACH TN 3776 NUMBER OF 3.12_ John R. Jack and Nick S. Diaconis_ October 1956 TENTATIVE METHOD FORCALCULATION OF THESOUND FIELD ABOUT A SOURCE TN 3779 OVER GROUND CONSIDERING DIFFRACTION ANDSCATTERING INTO SHADOW ZONES_ David C. Pridmore-Brown and Uno Ingard_ September 1956 TN 3789 THERESULTS OF WIND-TIFNNEL TESTS TOA MACH NUMBER OF 0.90 OF A FOUR- ENGINE PROPELLER-DRIVEN AIRPLANE CONFIGURATION HAVING A WING WITH 40° OF SWEEPBACK ANDAN ASPECT RATIOOF i0_ George G. Edwards_ Jerald K. Dickson_ Fred B. Sutton_ September 1956 ANALYSIS OF WIND-TUNNEL TESTS TOA MACH NUMBER OF 0.90 OF A FOUR- TN 3790 ENGINE PROPELLER-DRIVEN AIRPLANE CONFIGURATION HAVING A WING WITH 40° OF SWEEPBACK ANDAN ASPECT RATIOOF i0_ George G. Edwards_ Jerald K. Dickson_ Fred B. Sutton_ Fred A. Demele_September 1956 A THEORETICAL ANALYSIS OF HEATTRANSFER IN REGIONS OF SEPARATED TN 3792 FLOWjDean R. Chapman_ October 1956 DRAG INTERFERENCE BETWEEN A POINTED CYLINDRICAL BODY ANDTRIANGULAR TN 3794 WINGS OFVARIOUS ASPECT RATIOS AT MACH NUMBERS OF 1.50 AND2.02_ Curt A. Holzhauser and Leo P. Hall_ October 1956 LIFT ANDPITCHING-MOMENT INTERFERENCE BETWEEN A POINTED CYLINDRICAL TN 3795 BODY ANDTRIANGULAR WINGS OF VARIOUS ASPECT RATIOS AT MACH NUMBERS OF 1.50 AND2.02_ Elliott D. Katzen and GeorgeE. Kaattari_ Novem- ber 1956 THEORETICAL LIFT DUETO WINGINCIDENCE OF SLENDER WING-BODY-TAIL TN 3796 COMBINATIONS AT ZERO ANGLE OF ATTACK_ Alvin H. Sacks_ November1956 A THEORETICAL ESTIMATE OFTHEEFFECTS OF COMPRESSIBILITY ONTHE TN 3798 PERFORMANCE OF A HELICOPTER ROTOR IN VARIOUS FLIGHTCONDITIONS_ Alfred Gessowand Almer D. Crim_ October 1956 AN AIR-FLOW-DIRECTION PICKUP SUITABLE FORTELEMETERING USEON TN 3799 PILOTLESS AIRCRAFT_ Wallace L. Ikard_ October 1956 TN 3800 EXPLORATORY INVESTIGATION OF THEEFFECTIVENESS OF BIPLANE WINGS WITHLARGE-CHORD DOUBLE SLOTTED FLAPSIN REDIRECTING A PROPELLER SLIPSTREAM DOWNWARD FORVERTICAL TAKE-OFF_ Robert H. Kirby_ October TN 3804 A FACTOR AFFECTING TRANSONIC LEADING-EDGE FLOW SEPARATION_ George P. Woodand Paul B. Gooderum_ October 1956 TN 3807 CONVERSION OF INVISCIDNORMAL-FORCE COEFFICIENTS IN HELIUM TO EQUIVALENT COEFFICIENTS IN AIR FORSIMPLESHAPES AT HYPERSONIC SPEEDS_ JamesN. Mueller_ October 1956 TN 3808 WIND-TUNNEL CALIBRATION OF A COMBINED PITOT-STATIC TUBEANDVANE- TYPEFLOW-ANGULARITY INDICATOR AT MACH NUMBERS OF 1.61 AND2.01_ Archibald R. Sinclair and William D. Mace_October 1956 TN 3811 CHARTS ADAPTED FROM VANDRIEST'STURBULENT FLAT-PLATE THEORY FOR DETERMINING VALUES OF TURBULENT AERODYNAMIC FRICTION ANDHEAT- TRANSFER COEFFICIENTS_ Dorothy B. Lee and Max. A. Faget_ October TN 3815 ONSLENDER-BODY THEORY ANDTHEAREA RULEAT TRANSONIC SPEEDS_ Keith C. Harder_ E. Bernard Klunker_ November1956 TN 3819 BASE PRESSURE AT SUPERSONIC SPEEDS ONTWO-DIMENSIONAL AIRFOILSAND ONBODIES OF REVOLUTION WITHANDWITHOUT FINS HAVING TURBULENT BOUNDARY LAYERS_ EugeneS. Lovej January 1957 TN 3820 SOME OBSERVATIONS ONMAXIMUM PRESSURE RISE ACROSS SHOCKS WITHOUT BOUNDARY-LAYER SEPARATION ONAIRFOILSAT TRANSONIC SPEEDS_ Walter f F. Lindsey and Patrick J. Johnston_ November 1956 TN 3821 FLIGHT TECHNIQUES FOR DETERMINING AIRPLANE DRAG AT HIGH MACH NUM- BERS_ De Elroy Beeler_ Donald R. Bellman_ and Edwin J. Saltzman_ August 1956 TN 3832 ON POSSIBLE SIMILARITY SOLUTIONS FOR THREE-DIMENSIONAL INCOMPRES- SIBLE LAMINAR BOUNDARY LAYERS. II - SIMILARITY WITH RESPECT TO STATIONARY POLAR COORDINATES_ Howard Z. Herzig and Arthur G. Han- sen_ November 1956 TN 3835 A STUDY OF SPRAYS FORMED BY TWO IMPINGING JETS_ Marcus F. Heidmann_ Richard J. Priem_ and Jack C. Humphrey_ March 1957 TN 3836 SPREADING CHARACTERISTICS OF A JET EXPANDING FROM CHOKED NOZZLES AT MACH 1.91_ Morris D. Rovsso and L. Eugene Baughman_ December TN 3837 INVESTIGATION OFHEATTRANSFER FROM A STATIONARY ANDROTATING ELLIPSOIDAL FORBODY OFFINENESS RATIO3_ JamesP. Lewis and Robert S. Ruggeri_ November1956 TN 3840 ANALYSIS OF PARTICLE MOTIONS FORA CLASS OF THREE-DIMENSIONAL INCOMPRESSIBLE LAMINAR BOUNDARY LAYERS_ Arthur G. Hansenand HowardZ. Herzfg_ November1956 TN 3841 DISTRIBUTION OFNORMAL COMPONENT OF INDUCED VELOCITY IN LATERAL PLANE OF A LIFTING ROTOR_ Walter Castles_ Jr._ and HowardL.

Durham_Jr._ December1956 TN 3845 INVESTIGATION OF THEEFFECTS OF LEADING EDGE CHORD-EXTENSIONS AND FENCES IN COMBINATION WITHLEADING-EDGE FLAPSONTHEAERODYNAMIC CHARACTERISTICS AT MACH NUMBERS FROM 0.40 TO 0.93 OF A 45° SWEPT- BACK WING OF ASPECT RATIO4_ Kenneth D. Spreemanand William J.

Alford_ Jr.# April 1957 TN 3846 EXPERIMENTAL INVESTIGATION OF THEFORCE ANDMOMENTS DUETO SIDESLIP OFA SERIES OF TRIANGULAR VERTICAL- ANDHORIZONTAL-TAIL COMBINA- TIONSAT MACH NUMBERS OF 1.62_ 1.93# AND2.41j Donald E. Coletti_ March 1957 TN 3850 EXPERIMENTAL INVESTIGATION ONTHELANGLEY HELICOPTER TESTTOWER OF COMPRESSIBILITY EFFECTS ONA ROTOR HAVING NACA 632-015 AIRFOIL SECTIONS_ JamesP. Shivers and Paul J. Carpenter_ December1956 TN 3852 FLIGHTMEASUREMENTS OF THEVIBRATIONS ENCOUNTERED BYA TANDEM HELICOPTER ANDA METHOD FORMEASURING THECOUPLED RESPONSE IN FLIGHT_John E. Yeates_ Jr._ December1956 TN 3858 A LOW-SPEED EXPERIMENTAL INVESTIGATION OF THEEFFECT OF A SANDPAPER TYPEOF ROUGHNESS ONBOUNDARY-LAYER TRANSITION_ Albert E. von Doen- hoff and Elmer A. Horton_ October 1956 TN 3860 METHOD FORCALCULATING EFFECTS OF DISSOCIATION ONFLOW VARIABLES IN THERELAXATION ZONE BEHIND NORMAL SHOCK WAVES_ John S. Evans_ December1956 TN 3861 AERODYNAMIC CHARACTERISTICS OFA CIRCULAR CYLINDER AT MACH NUMBER 6.86 ANDANGLES OF ATTACK UP TO 90°_ Jim A. Penland_ January 1957 TN 3863 WIND-TUNNEL INVESTIGATION AT LOW SPEEDS TODETERMINE THEEFFECT OFASPECT RATIOANDENDPLATES ONA RECTANGULAR WING WITHJET FLAPSDEFLECTED 85°_ John G. Lowry and RaymondD. Vogler_ December TN 3865 WIND-TUNNEL INVESTIGATION OF JET-AUG_ENTED FLAPSONA RECTANGULAR WINGTO HIGHMOMENTUM COEFFICIENTS_ V. E. Lockwood_T. R. Turner_ and J. M. Riebe_ December1956 WIND-TUNNEL INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS IN TN 3867 PITCH OF WING-FUSELAGE COMBINATIONS AT HIGH SUBSONIC SPEEDS. TAPER -RATIO SERIES_ Thomas J. King_ Jr._ and Thomas B. Pasteur_ Jr._ December 1956 TN 3868 PARTICULAR SOLUTIONS FOR FLOWS AT MACH NUMBER I_ Max. A. Heaslet and Franklyn B. Fuller_ November 1956 TN 3869 INVESTIGATION OF SEPARATED FLOWS IN SUPERSONIC AND SUBSONIC STREAMS WITH EMPHASIS ON THE EFFECT OF TRANSITION_ Dean R. Chapman_ Donald M. Keuhn_ and Howard K. Larson_ March 1957 TN 3872 EXPERIMENTAL DETERMINATION OF THE RANGE OF APPLICABILITY OF THE TRANSONIC AREA RULE FOR WINGS OF TRIANGULAR PLAN FORM_ William A.

Page_ December 1956 TABLES OF CHARACTERISTIC FUNCTIONS FOR SOLVING BOUNDARY-VALUE TN 3873 PROBLEMS OF THE WAVE EQUATION WITH APPLICATION TO SUPERSONIC INTER- FERENCE_ Jack N. Nielson_ February 1957 TN 3875 THE SIMILARITY RULES FOR SECOND-ORDER SUBSONIC AND SUPERSONIC FLOW_ Milton D. Van Dyke_ January 1957 AN INVESTIGATION AT LOW SPEED OF THE FLOW OVER A SIMULATED FLAT TN 3876 PLATE AT SMALL ANGLES OF ATTACK USING PITOT-STATIC AND HOT-WIRE PROBES_ Donald E, Gault_ March 1957 ON STOKES' STREAM FUNCTION IN COMPRESSIBLE SMALL-DISTURBANCE THEORYj TN 3877 Milton D. Van Dyke_ February 1957 TN 3881 WIND-TUNNEL TECHNIQUE FOR SIMULTANEOUS SIMULATION OF EXTERNAL FLOW FIELD ABOUT NACELLE INLET AND EXIT AIRSTREAMS AT SUPERSONIC SPEEDS_ Gerald W. Englert and Roger W. Luidense_ January 1957 INVESTIGATION OF TRANSIENT POOL BOILING DUE TO SUDDEN LARGE POWER TN 3885 SURGE_ Robert Cole_ December 1956 AVERAGE PROPERTIES OF COMPRESSIBLE LAMINAR BOUNDARY LAYER ON FLAT TN 3886 PLATE WITH UNSTEADY FLIGHT VELOCITY_ Franklin K. Moore and Simon Ostrach_ December 1956 TN 3888 SIMPLIFIED METHOD FOR ESTIMATING COMPRESSIBLE LAMINAR HEAT TRANSFER WITH PRESSURE GRADIENT_ El. Reshotko_ December 1956 ON POSSIBLE SIMILARITY SOLUTIONS FOR THREE-DIMENSIONAL INCOMPRESSI- TN 3890 BLE LAMINAR BOUNDARY LAYERS. III - SIMILARITY WITH RESPECT TO STATIONARY POLAR COORDINATES FOR SMALL ANGLE VARIATION_ Howard Z. Herzig and Arthur G. Hansen_ January 1957 THEORY ANDDESIGN OF A PNEUMATIC TEMPERATURE PROBE ANDEXPERIMENTAL TN 3893 RESULTS OBTAINED IN A HIGH-TEMPERATURE GASSTREAM_ Frederick S.

Sirmnons and GeorgeE. Glawe, January 1957 TN 3895 OBLIQUE-SHOCK RELATIONS AT HYPERSONIC SPEEDS FORAIR IN CHEMICAL EQUILIBRIUM_ Wolfgang E. Moeckel_ January 1957 TN 3898 WIND-TUNNEL INVESTIGATION OF AN EXTERNAL-FLOW JET-AU_ENTED SLOTTED FLAPSUITABLE FORAPPLICATION TOAIRPLANES WITHPOD-MOUNTED JET ENGINES_ John P. Campbell and Joseph L. Johnson_ Jr._ December1956 TN 3900 INVESTIGATION OF VERTICAL DRAG ANDPERIOD-AIRLOADS ACTING ONFLAT PANELS IN A ROTOR SLIPSTREAM_ Robert A. Makofsk and GeorgeF.

Menkick_ December1956 TN 3903 AN EXPERIMENTAL HYDRODYNAMIC INVESTIGATION OF THEINCEPTION OF VORTEX VENTILATION_ John A. Ramsen_ April 1957 INVESTIGATION OF THEEFFECTIVENESS OF BOUNDARY-LAYER CONTROL BY TN 3904 BLOWING OVER A COMBINATION OF SLIDINGANDPLAINFLAPSIN DEFLECTING A PROPELLER SLIPSTREAM DOWNWARD FORVERTICAL TAKE-OFF_ Kenneth P.

Spreemann and Richard E. Kuhn_ December1956 TN 3905 DIFFERENTIAL EQUATIONS OFMOTION FORCOMBINED FLAPWISE BENDING_ CHORDWISE BENDING_ ANDTORSION OF TWISTED NONUNIFORM ROTOR BLADES_ John C. Houbolt and GeorgeW. Brooks_ February 1957 SIMILITUDERELATIONS FORFREE-MODEL WIND-TUNNEL STUDIES OF STORE- TN 3907 DROPPING PROBLEMS_ Carl A. Sandahl and Max H. Faget_ January 1957 TN 3908 HYDRODYNAMIC CHARACTERISTICS OVER A RANGE OF SPEEDS UP TO 80 FEET PERSECOND OF A RECTANGULAR MODIFIED FLATPLATEHAVING AN ASPECT RATIOOF0.25 ANDOPERATING AT SEVERAL DEPTHS OF SUBMERSION_ Victor L. Vaughan_Jr._ and John A. Ramsen_ April 1957 TN 3917 EFFECT OF PROPELLER LOCATION ANDFLAPDEFLECTION ONTHEAERODYNAMIC CHARACTERISTICS OF A WING-PROPELLER COMBINATION FORANGLES OF ATTACK FROM 0° TO 80°_ William A. Newsom_ Jr._ January 1957 TN 3918 WIND-TUNNEL INVESTIGATION OF EFFECT OF PROPELLER SLIPSTREAMS ON AERODYNAMIC CHARACTERISTICS OF A WING EQUIPPED WITHA 50-PERCENT- CHORD SLIDINGFLAPANDA 30-PERCENT-CHORD SLOTTED FLAPj Richard E.

Kuhn and William C. Hayes_ Jr._ February 1957 TN 3919 INVESTIGATION OF EFFECTIVENESS OF A WING EQUIPPED WITHA 50-PERCENT- CHORD SLOTTED FLAP_ANDA 30-PERCENT-CHORD SLATIN DEFLECTING PRO- PELLER SLIPSTREAMS DOWNWARD FORVERTICAL TAKE-OFF_ Richard E. Kuhn_ January 1957 APPROXIMATE SOLUTION FORSTREAMLINES ABOUT A LIFTING ROTOR HAVING rN 3921 UNIFORM LOADING ANDOPERATING IN HOVERING ORLOW-SPEED VERTICAL- ASCENT FLIGHTCONDITIONS_ Walter Castles_ Jr._ February 1957 TN 3928 BOUNDARY-LAYER TRANSITION AT MACH 3.12 AS AFFECTED BY COOLING AND NOSE BLUNTING_ NickS. Diaconis and John R. Jack_ January 1957 TN 3934 EXPERIMENTAL STUDY OF HEATTRANSFER TO SMALL CYLINDERS IN A SUB- SONIC_ HIGH-TEMPERATURE GASSTREAM_ GeorgeE. Glawe_Robert C.

Johnson_ and Richard S. Brokaw_May 1957 TN 3935 HYDROGEN-OXYGEN EXPLOSIONS IN EXHAUST DUCTING_ Paul M. Ordin_ April 1957 TN 3938 SIDEWASH IN THEVICINITY OF LIFTING SWEPT WINGS AT SUPERSONIC SPEEDS_ Peter J. Maxie_ Jr._ February 1957 TN 3942 INVESTIGATION OF VARIATION IN BASE PRESSURE OVER THEREYNOLDS NUMBER RANGE IN WHICH WAKE TRANSITION OCCURS FORNONLIFTING BODIES OF REVOLUTION ATMACH NUMBERS FROM 1.62 TO 2.62_ Vernon Van Hise_ January 1957 TN 3943 A POWER-SERIES SOLUTION FORTHEUNSTEADY LAMINAR BOUNDARY-LAYER FLOW IN AN EXPANSION WAVE OF FINITE WIDTH MOVING THROUGH A GAS INITIALLY AT REST_ Nathaniel B. Cohen_June 1957 TN 3944 AN INTEGRAL SOLUTION TO THEFLAT-PLATE LAMINAR BOUNDARY-LAYER FLOW EXISTINGINSIDEANDAFTER EXPANSION WAVES ANDAFTERSHOCK WAVES MOVING INTOQUIESCENT FLUID WITHPARTICULAR APPLICATION TO THE COMPLETE SHOCK-TUBE FLOW_ Robert L. Trimpi_ Nathaniel B. Cohen_ June 1957 TN 3950 CHARTS FORTHEANALYSIS OFFLOW IN A WHIRLING DUCT_ Robert A.

Makofski_ May 1957 TN 3951 INVESTIGATION OF THEPLANING LIFT OFA FLATPLATEAT SPEEDS UP TO 170 FEETPERSECOND_ Kenneth W. Christopher_ March 1957 TN 3958 ANALYSIS OF STATIC-AEROELASTIC BEHAVIOR OFLOW-ASPECT-RATIO RECTANGULAR WINGS_ John M. Hedgepeth and Paul G. Waner_Jr._ April TN 3960 EXPECTED NUMBER OFMAXIMA ANDMINIMAOF A STATIONARY RANDOM PROCESS WITHNON-GAUSSIAN FREQUENCY DISTRIBUTION_ Franklin W. Diederich_ April 1957 TN 3962 THEEROSION OF METEORS ANDHIGH-SPEED VEHICLES IN THEUPPER ATMOS- PHERE_ C. Frederick Hansen_March 1957 TN 3963 A CORRELATION OF LOW-SPEED_ AIRFOIL-SECTION STALLING CHARACTERISTICS WITHREYNOLDS NUMBER ANDAIRFOIL GEOMETRY_ Donald E° Gault_ March THELINEARIZED SUBSONIC FLOW ABOUT SYMMETRICAL NONLIFTING WING- TN 3964 BODY COMBINATIONS_ John B. McDevitt_ April 1957 MEASUREMENTS OFTHENONLINEAR VARIATION WITHTEMPERATURE OFHEAT- TN 3965 TRANSFER RATE FROM HOTWIRES IN TRANSONIC ANDSUPERSONIC FLOW_ Warren Winovich and HowardA. Stine_ April 1957 TN 3966 THEORETICAL INVESTIGATION OF THEEFFECTS OF CONFIGURATION CHANGES ONTHECENTER-OF-PRESSURE SHIFTOF A BODY-WING-TAIL COMBINATION DUETOANGLE OF ATTACK ANDMACH NUMBER AT TRANSONIC ANDSUPERSONIC SPEEDS_ J. Richard Spahr_ May 1957 TN 3967 CHARACTERISTICS OF A 40° CONE FORMEASURING MACH NUMBER_ TOTAL PRESSURE_ ANDFLOW ANGLES AT SUPERSONIC SPEEDS_ Frank J. Centolanzi_ May 1957 A THEORETICAL STUDY OF THEEFFECT OF UP-STREAM TRANSPIRATION COOL- TN 3969 ING ONTHEHEAT TRANSFER ANDSKIN-FRICTION CHARACTERISTICS OFA COMPRESSIBLE_ LAMINAR BOUNDARY LAYER_ Morris W. Rubesin_ May 1957 THINAIRFOIL THEORY BASED ONAPPROXIMATE SOLUTION OF THETRANSONIC TN 3970 FLOW EQUATION_ John R. Spreitter and Alberta Y. Alksne_ May 1957 ONFLOW OF ELECTRICALLY CONDUCTING FLUIDSOVER A FLATPLATEIN THE TN 3971 PRESENCE OFA TRANSVERSE MAGNETIC FIELD_Vernon J. Rossow_ May 1957 FURTHER EXPERIMENTS ONTHESTABILITYOFLAMINAR ANDTURBULENT TN 3977 HYDROGEN-AIR FLAMES AT REDUCED PRESSURES_ Burton D. Fine_ April 1957 SURVEY OF THEACOUSTIC NEAR FIELD OF THREE NOZZLES AT A PRESSURE TN 3978 RATIOOF 30_ Harold R. Mull and John C. Erickson_ April 1957 EFFECT OF BLUNTNESS ONTRANSITION FORA CONE ANDA HOLLOW CYLINDER TN 3979 AT MACH 3.1_ Paul F. Brinich_ Jr._ and NormanSands_May 1957 TABLES OF VARIOUS MACH NUMBER FUNCTIONS FORSPECIFIC-HEAT RATIOS TN 3981 FROM 1.28 TO 1.38_ Lewis Laboratory Computing Staff_ April 1957 EXPLORATORY STUDY OF GROUND PROXIMITY EFFECTS ONTHRUST OFANNULAR TN 3982 ANDCIRCULAR NOZZLES_ UweH. von Glahn_ April 1957 TN 3986 COMPRESSIBLE LAMINAR BOUNDARY LAYER OVER A YAWED INFINITE CYLINDER WITHHEATTRANSFER ANDARBITRARY PRANDTL NUMBER_ Ivan E. Beckwith_ June 1957 TN 3988 EXPERIMENTAL ANDCALCULATED HISTORIES OFVAPORIZING FUELDROPS_ R. J. Priem_ G. L. Borman_ M. M. EI-Wakil_ O. A. Uyehara_August A NOTE ONTHEEFFECT OF HEAT TRANSFER ONPEAKPRESSURE RISEASSO- TN 3997 CIATED WITHSEPARATION OF TURBULENT BOUNDARY LAYER ONA BODY OF REVOLUTION (NACA RM-10) AT A MACH NUMBER OF 1.61_ K. R. Czarnecki and A. R. Sinclair_ April 1957 TN 3999 EXPERIMENTAL INFLUENCE COEFFICIENTS AND VIBRATION MODES OF A BUILT-UP 45 ° DELTA-WING SPECIMEN_ Eldon E. Kordes_ Edwin T. Krusze- wski_ Deene J. Weidman_ May 1957 TN 4001 SOME CONSIDERATIONS OF HYSTERESES EFFECT ON TIRE MOTION AND WHEEL SHIMMY_ Robert E. Smiley_ June 1957 TN 4002 INTERACTION OF MOVING SHOCKS AND HOT LAYERS_ Robert V. Hess_ May TN 4006 INVESTIGATION AT TRANSONIC SPEEDS OF DEFLECTORS AND SPOILERS AS GUST ALLEVIATE ON A 35 ° SWEPT WING. TRANSONIC-BUMP METHOD_ Delwin R. Croom and Jarrett K. Huffman_ June 1957 TN 4013 LOW-SPEED EXPERIMENTAL INVESTIGATION OF THE MAGNUS EFFECT ON VARI- OUS SECTIONS OF A BODY OF REVOLUTION WITH AND WITHOUT A PROPELLER_ M. J. Queijo and Herman S. Fletcher_ August 1957 TN 4017 MOMENTUM TRANSFER FOR FLOW OVER A FLAT PLATE WITH BLOWING_ H. S.

Mickley and R. S. Davis_ November 1957 TN 4018 INFLUENCE OF TURBULENCE ON TRANSFER OF HEAT FROM CYLINDERS_ Joseph Kestin and Paul F. Maeder_ October 1957 TN 4021 NONUNIFORMITIES IN SHOCK-TUBE FLOW DUE TO UNSTEADY-BOUNDARY-LAYER ACTION_ Harold Mirels and Willis H. Braum_ May 1957 TN 4022 ESTIMATION OF COMPRESSIBLE BOUNDARY-LAYER GROWTH OVER INSULATED SURFACES WITH PRESSURE GRADIENT_ Gerald W. Englert_ June 1957 TN 4029 TURBULENCE MEASUREMENTS IN MULTIPLE INTERFERING AIR JETS_ James C. Laurence and Jean M. Benninghoff_ December 1957 TN 4033 SCREEN-TYPE NOISE REDUCTION DEVICES FOR GROUND RUNNING OF TURBOJET ENGINES_ Willard D. Coles and Warren J. North_ July 1957 TN 4037 STABILITY OF LAMINAR BOUNDARY LAYER NEAR A STAGNATION POINT OVER AN IMPERMEABLE WALL AND A WALL COOLED BY NORMAL FLUID INJECTION_ Morris Mordochow_ Richard G. Grape_ and Richard P. Shaw_ August TN 4038 PERFORATED SHEETS AS THE POROUS MATERIAL FOR A SUCTION-FLAP APPLI- CATION_ R. E. Dannenberg_ J. A. Weiberg_ and B. J. Gambucci_ May TN 4039 INVESTIGATION OF THE EFFECTS OF PROFILE SHAPE ON THE AERODYNAMIC AND STRUCTURAL CHARACTERISTICS OF THIN_ TWO-DIMENSIONAL AIRFOILS AT SUPERSONIC SPEEDS_ Elliott D. Katzen_ Donald M. Kuehn_ and William A. Hill_ Jr._ September 1957 ESTIMATION OF INCREMENTAL PITCHING MOMENTS DUETO TRAILING-EDGE TN 4040 FLAPSONSWEPT ANDTRIANGULAR WINGS_ Harry J. Jamesand Lynn W.

Hunton_ July 1957 THESUBSONIC STATICAERODYNAMIC CHARACTERISTICS OF AN AIRPLANE TN 4041 MODEL HAVING A TRIANGULAR WING OF ASPECT RATIO3. I - EFFECTS OF HORIZONTAL-TAlL LOCATION ANDSIZE ONTHELONGITUDINAL CHARAC- TERISTICS_ Bruce E. Tinling and ArmandoE. Lopez_ July 1957 THESUBSONIC STATICAERODYNAMIC CHARACTERISTICS OFAN AIRPLANE MODEL TN 4042 HAVING A TRIANGULAR WING OF ASPECT RATIO3. II - LATERAL AND DIRECTIONAL CHARACTERISTICS_ HowardF. Savage_Bruce E. Tinling_ August 1957 THESUBSONIC STATICAERODYNAMIC CHARACTERISTICS OF AN AIRPLANE TN 4043 MODEL HAVING A TRIANGULAR WING OF ASPECT RATIO3. III - EFFECTS OF TRAILING-EDGE FLAPS_ Bruce E. Tinling and A. V. Karpen_ July GROUND EFFECTS ONTHELONGITUDINAL CHARACTERISTICS OFTWO MODELS TN4044 WITHWINGS HAVING LOW ASPECT RATIOANDPOINTED TIPS_ Donald A.

Buell and Bruce E. Tinling_ July 1957 ELLIPTIC CONES ALONE ANDWITHWINGS AT SUPERSONIC SPEEDS_ Leland TN 4045 H. Jorgensen_ October 1957 A COMPARATIVE ANALYSIS OF THEPERFORMANCE OFLONG-RANGE HYPER- TN 4046 VELOCITY VEHICLES_ Alfred J. Eggers_ Jr._ Harry J. Allen_ and Stanford E. Neice_ October 1957 INVESTIGATION AT LOWSPEEDS OFDEFLECTORS ANDSPOILERS AS GUST TN4057 ALLEVIATORS ONA MODEL OF THEBELLX-5 AIRPLANE WITH35° SWEPT WINGS ANDONA HIGH-ASPECT-RATIO 35 ° SWEPT-WING-FUSELAGE MODEL_ Delwin R. Croom_Jarrett K. Huffman_ June 1957 TN 4060 A WIDE_FREQUENCY-RANGE AIR-JET SHAKER_ Robert W. Herr_ June 1957 FLIGHTMEASUREMENTS OF BOUNDARY-LAYER TEMPERATURE PROFILES ONA TN4061 BODY OF REVOLUTION (NACA RM-10)AT MACH NUMBERS FROM 1.2 TO 3.5_ Andrew G. Swanson_ JamesJ. Buglia_ and Leo T. Chavvin_ July 1957 TN 4063 EQUATIONS_ TABLES_ ANDFIGURES FORUSEIN THEANALYSIS OF HELIUM FLOW AT SUPERSONIC ANDHYPERSONIC SPEEDS_ JamesN. Mueller_ September 1957 EFFECT OF ANGLE OF ATTACK ANDTHICKNESS'ON AERODYNAMIC COEF_ICIENTS TN4069 OF A RIGID WING OSCILLATING AT VERY LOW FREQUENCIES IN TWO- DIMENSIONAL SUPERSONIC FLOW_ Frank S. Malvestuto_ Jr._ and Julia M. Goodwin_January 1958 FLIGHT-TEST INVESTIGATION ONTHELANGLEY CONTROL-LINE FACILITY OF TN 4070 A MODEL OF A PROPELLER-DRIVEN TAIL-SITTER-TYPE VERTICAL-TAKE-OFF AIRPLANE WITHDELTA WINGDURING RAPIDTRANSITIONS_ Robert O. Schade_ August 1957 EXPERIMENTAL INVESTIGATION OFATTENUATION OF STRONG SHOCK WAVES IN TN 4072 A SHOCK TUBE WITHHYDROGEN ANDHELIUM AS DRIVER GASES_ Jim J. Jones_ July 1957 A DISCUSSION OF CONE ANDFLAT-PLATE REYNOLDS NUMBERS FOREQUAL TN 4078 RATIOS OF THELAMINAR SHEAR TO THESHEAR CAUSED BY SMALL VELOCITY FLUCTUATIONS IN A LAMINAR BOUNDARY LAYER_ Neal Tetervin_ August WIND-TUNNEL INVESTIGATION OF EXTERNAL-FLOW JET-AU_ENTED DOUBLE TN 4079 SLOTTED FLAPSONA RECTANGULAR WING AT AN ANGLE OF ATTACK OF 0° TO HIGHMOMENTUM COEFFICIENTS_ Edwin E. Davenport_ September 1957 DISCRETE POTENTIAL THEORY FORTWO-DIMENSIONAL LAPLACE ANDPOISSON TN 4086 DIFFERENCE EQUATIONS_ Charles Saltzer_ January 1958 ANALYSIS OF SHOCK MOTION IN DUCTS DURING DISTURBANCES IN DOWNSTREAM TN 4090 PRESSURE_ Herbert G. Hurrell_ September 1957 EXPERIMENTAL INVESTIGATION OF TRANSPIRATION COOLING FORA TURBULENT TN4091 BOUNDARY LAYERIN SUBSONIC FLOW USINGAIR AS A COOLANT_ William E.

Brunk_ October 1957 EXPERIMENTAL DROPLET IMPING_ENTONFOUR BODIES OF REVOLUTION_ TN 4092 JamesP. Lewis and Robert S. Ruggeri_ December1957 INVESTIGATION OF HEATTRANSFER FROM A STATIONARY ANDROTATING CONI- TN 4093 CALFOREBODY_ Robert S. Ruggeri and JamesP. Lewis_ October 1957 EFFECTS OF EXTRI_IE SURFACE COOLING ONBOUNDARY-LAYER TRANSITION_ TN 4094 John R. Jack_ R. J. Wisniewski_ and N. S. Diaconis_ October 1957 FLOW-TURNING LOSSES ASSOCIATED WITHZERO-DRAG EXTERNAL-COMPRESSI_ON TN 4096 SUPERSONIC INLETS_Rudolph C. Meyer_ October 1957 HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONTWO BLUNT BODIES AT TN 4099 MACH NUMBER 3.12_ Nick S. Diaconis_ Richard J. Wisniewski_ and John R. Jack_ October 1957 VELOCITY ANDFRICTIONCHARACTERISTICS OF LAMINAR VISCOUS BOUNDARY- TN 4102 LAYER ANDCHANNEL FLOW OVER SURFACES WITHEJECTION ORSUCTIONj E. R. G. Eckert_ P. L. Donoughe_and Betty Jo Moore_ December1957 THEUSEOFPURE TWISTFORDRAG REDUCTION ONARROW WINGS WITHSUB- TN 4104 SONIC LEADING EDGES_ Frederick C. Grant_ August 1957 TN 4105 A METHOD OF COMPUTING THETRANSIENT TEMPERATURE OF THICKWALLS FROM ARBITRARY VARIATION OFADIABATIC-WALL TEMPERATURE ANDHEATTRANSFER COEFFICIENT_ Paul R. Hill_ October 1957 TN4107 EFFECTS OFAIRPLANE FLEXIBILITYONWINGSTRAINS IN ROUGH AIR AT 5_000 FEETAS DETERMINED BYFLIGHTTESTS OF A LARGE SWEPT-WING AIRPLANE_ Richard H. Rhyneand Harold N. Murrow_ September 1957 TN 4108 A THERMAL SYSTEM FORCONTINUOUS MONITORING OFLAMINAR ANDTURBULENT BOUNDARY-LAYER FLOWS DURING ROUTINE FLIGHT_NormanR. Richardson and Elmer A. Horton_ September 1957 TN 4116 WIND-TUNNEL INVESTIGATION AT LOW SPEEDS TODETERMINE FLOW-FIELD CHARACTERISTICS ANDGROUND INFLUENCE ONA MODEL WITHJET-AUGMENTED FLAPS_ Raymond D. Vogler and ThomasR. Turner_ September 1957 TN 4117 EXPERIMENTAL INVESTIGATION OF LIFTj DRAG_ ANDPITCHING MOMENT OF FIVE ANNULAR AIRFOILS_HermanS. Fletcher_ October 1957 TN4120 THEORETICAL CALCULATIONS OF SUPERSONIC WAVE DRAG AT ZERO LIFT FOR A PARTICULAR STORE ARRANGEMENT_ Kenneth Margolis_ Frank S. Malves- tuto_ Jr._ andPeter J. Maxis_ Jr._ Jsnuary 1958 TN4121 THEORY ANDAPPARATUS FORMEAS_ENT OFEMISSIVITYFORRADIATIVE COOLING OF HYPERSONIC AIRCRAFT WITHDATAFORINCONEL ANDINCONEL X_ William J. O'Sullivan_ Jr._ and William R. Wade_October 1957 TN4125 HEATTRANSFER ANDRECOVERY TEMPERATURES ONA SPHERE WITHLAMINAR_ TRANSITIONAL_ ANDTURBULENT BOUNDARY LAYERS AT MACH NUMBERS OF 2.00 AND4.15_ Ivan E. Beckwith and JamesJ. Gallagher_ December TN4127 THEMEASUREMENT OFPRESSURE ALTITUDE ONAIRCRAFT_ William Gracey_ October 1957 TN4131 TRANSITION-FLIGHT INVESTIGATION OFA FOUR-ENGINE-TRANSPORT VERTICAL-TAKE-OFF AIRPLANE MODEL UTILIZING A LARGE FLAPANDEXTEN- SIBLE VANES FORREDIRECTING THEPROPELLER SLIPSTREAM_ Louis P.

Tost_ December1957 TN4133 BOUNDARY-LAYER DISPLACEMENT EFFECTS IN AIR AT MACH NUMBERS OF 6.8 AND9.6_ Mitchel H. Bertram_ February 1958 TN4135 INFLUENCE OF SOLID-BODY ROTATION ONSCREEN-PRODUCED TURBULENCE_ Stephen Traugott_ August 1958 TN 4139 WALL PRESSURE FLUCTUATIONS IN A TURBULENT BOUNDARY LAYER_ William W. Willmarth_ March 1958 TN 4140 TURBULENT SHEARING STRESS IN THEBOUNDARY LAYER OFYAWED FLAT PLATES_ Harry Ashkenas_April 1958 TN 4142 EFFECTS OF LEADING-EDGE BLUNTING ONTHELOCAL HEATTRANSFER AND PRESSURE DISTRIBUTIONS OVER FLATPLATES IN SUPERSONIC FLOW_ Marcus O. Crager_ December1957 TN 4143 DEVELOPMENT OFA PISTON-COMPRESSOR TYPELIGHT-GAS GUN FORTHE LAUNCHING OFFREE-FLIGHT MODELS AT HIGHVELOCITY_ Alex Co Charters_ Jr._ B. Pat Denardo_ and Vernon J. Rossow_November1957 TN4144 EFFECT OF OXYGEN RECOMBINATION ONONE-DIMENSIONAL FLOW AT HIGH MACH NUMBERS_ Steve P. Heims_ January 1958 TN 4145 AN ANALYSIS OF THEOPTIMIZATION OFA BEAM RIDER MISSILE SYSTEM_ Marvin Shinbrat and Grace C. Carpenter_ March 1958 TN 4146 CONTRIBUTION OF THEWINGPANELS TO THEFORCES ANDMOMENTS OF SUPERSONIC WING-BODY COMBINATIONS AT COMBINED ANGLES_ J. Richard Spahr_ January 1958 TN 4147 MEASURED ANDPREDICTED DYNAMIC RESPONSE CHARACTERISTICS OFA FLEXI- BLEAIRPLANE TO ELEVATOR CONTROL OVER A FREQUENCY RANGE INCLUDING THREE STRUCTURAL MODES_ Henry A. Cole_ Jr._ and Euclid C. Holleman_ February 1958 TN 4149 AN ANALYSIS OF THETURBULENT BOUNDARY-LAYER CHARACTERISTICS ONA FLATPLATE WITHDISTRIBUTED LIGHT-GAS INJECTION_ Morris W. Rubesin and Constantine C. Pappas_February 1958 TN 4150 APPROXIMATIONS FORTHETHERMODYNAMIC ANDTRANSPORT PROPERTIES OF HIGH-TEMPERATURE AIR_ C. Frederick Hanson_March 1958 TN4152 LAMINAR BOUNDARY LAYER WITHHEATTRANSFER ONA CONE AT ANGLE OF ATTACK IN A SUPERSONIC STREAM_ Eli Reshotko_ December1957 TN 4153 EFFECT OFWALLCOOLING ONINLETPARAMETERS OFA SCOOP OPERATING IN A TURBULENT BOUNDARY LAYER ONA FLATORCONICAL SURFACE FORMACH NUMBERS 2 TO i0_ Adrew Beke_March 1958 TN 4154 APPROXIMATE CALCULATION OF THECOMPRESSIBLE TURBULENT BOUNDARY LAYER WITHHEATTRANSFER ANDARBITRARY PRESSURE GRADIENT_ Eli Reshotko and Maurice Tucker_ December1957 TN 4155 AERODYNAMIC EFFECTS CAUSED BY ICING OFAN UNSWEPT NACA65A004AIR- FOIL_ Vernon H. Gray and UweH. von Glahn_ February 1958 TN4167 A RAPIDMETHOD FORPREDICTING ATTACHED-SHOCK SHAPE_ Eugene S.

Love and Ronald H. Long_ October 1957 TN4168 A METHOD FORCALCULATION OF HYDRODYNAMIC LIFT FORSUNMERGED ANDPLANING RECTANGULAR LIFTING SURFACES_ Kenneth L. Wadlin and Kenneth W. Christopher_ January 1958 TN 4169 ATMOSPHERIC T_PERATURE OBSERVATIONS TO i00_000 FEETFORSEVERAL CLIMATOLOGICAL REGIONS OF THENORTHERN HEMISPHERE_ Harold B. Tolef- son_ November1957 A RE-EXAMINATION OF THEUSEOF SIMPLECONCEPTS FORPREDICTING THE TN4170 SHAPE ANDLOCATION OF DETACHED SHOCK WAVES_ EugeneS. Love_ December1957 TN 4180 INVESTIGATION OF SPOILERS AT A MACH NUMBER OF 1.93 TODETERMINE THEEFFECTS OF HEIGHT ANDCHORDWISE LOCATION ONTHESECTION AERO- DYNAMIC CHARACTERISTICS OFTWO-DIMENSIONAL WINGjJamesN. Mueller_ February 1958 INVESTIGATION OF THEEFFECTS OF PROPELLER DIAMETER ONTHEABILITY TN 4181 OF A FLAPPED WING_ WITHANDWITHOUT BOUNDARY-LAYER CONTROL_ TO DEFLECT A PROPELLER SLIPSTREAM DOWNWARD FORVERTICAL TAKE-OFF_ Kenneth P. Spreeman_December1957 PHYSICAL CHARACTERISTICS ANDTESTCONDITIONS OFAN ETHYLENE-HEATED TN 4182 HIGH-TEMPERATURE JET_Eldred H. Heltonj January 1958 INVESTIGATION OF EFFECTS OF DISTRIBUTED SURFACE ROUGHNESS ONA TN 4183 TURBULENT BOUNDARY LAYER OVER A BODY OF REVOLUTION AT A MACH NUMBER OF 2.01_ John R. Sevier_ Jr._ and K. R. Czarnecki_ February MEASURI_IENT OF STATICPRESSURE ONAIRCRAFT_ William Gracey_Novem- TN 4184 ber 1957 HEATTRANSFER IN ISOTROPIC TURBULENCE DURING THEFINAL PERIOD OF TN 4186 DECAY_ D. W. Dunnand W. H. Reid_ June 1958 HIGH-SPEED HYDRODYNAMIC CHARACTERISTICS OFA FLATPLATE AND20o TN4187 DEAD-RISE SURFACE IN UNSYMMETRICAL PLANING CONDITIONSj Daniel Savitsky_ Robert E. Prowse_ and D. H. Lueders_ June 1958 LIFT ANDMOMENT ONTHINARROWHEAD WINGS WITHSUPERSONIC EDGES TN 4189 OSCILLATING IN SYMMETRIC FLAPPING ANDROLLANDAPPLICATION TO THE FLUTTER OF AN ALL-MOVABLE CONTROL SURFACE_ H. J. Cunningham_ January 1958 SHAPE OF INITIAL PORTION OF BOUNDARY OFSUPERSONIC AXISYMMETRIC TN4195 FREEJETSAT LARGE JET PRESSURE RATIOS_ EugeneS. Love and Louise P. Lee_ January 1958 EFFECTS OF AIRPLANE FLEXIBILITY ONWINGSTRAINS IN ROUGH AIR AT TN 4198 35_000FEETAS DETERMINED BYA FLIGHTINVESTIGATION OF A LARGE SWEPT-WING AIRPLANE_ Richard H. Rhyne_January 1958 TN 4200 EFFECTIVENESS OF BOUNDARY-LAYER CONTROL_ OBTAINED BY BLOWING OVER A PLAIN REAR FLAPIN COMBINATION WITHA FORWARD SLOTTED FLAP_IN DEFLECTING A SLIPSTREAM DOWNWARD FORVERTICAL TAKE-OFF_ Kenneth P. Spreemann_ February 1958 TN4201 COLLECTION OF ZERO-LIFTDRAG DATA ONBODIES OF REVOLUTION FROM FREE-FLIGHT INVESTIGATIONS_ William E° Stoney_ Jr._ January 1958 TN4203 FLIGHTINVESTIGATION OF EFFECTS OF ATMOSPHERIC TURBULENCE AND MODERATE MANEUVERS ONBENDING ANDTORSIONAL MOMENTS ENCOUNTERED BYA HELICOPTER ROTOR BLADE_ LeRoy H. Ludi_ February 1958 TN 4204 COMPILATION OF INFORMATION ONTHETRANSONIC ATTACHMENT OF FLOWS AT THELEADING EDGES OFAIRFOILS_Walter F. Lindsey and Emma J.

Landrum_February 1958 TN 4208 TURBULENT BOUNDARY LAYER ONA YAWED CONE IN A SUPERSONIC STREAM_ Willis H. Braun_ January 1958 TN 4211 FRICTIONSTUDIES OF VARIOUS MATERIALS IN LIQUID NITROGEN_ D. W.

Wisander_ W. F. Hady_ and R. L. Johnson_February 1958 TN 4213 RECOVERY T_q_PERATURES ANDHEATTRANSFER NEAR TWO-DIMENSIONAL ROUGHNESS ELEMENTS AT MACH 3.1j Paul F. Brinich_ Jr._ February TN 4214 BOUNDARY-LAYER TRANSITION ONAN OPEN-NOSE CONE ATMACH3.1_ Paul F. Brinich_ Jr._ February 1958 TN 4217 EFFECT OF JET TEMPERATURE ONJET-NOISEGENERATION_ Vern Gordon Rollin_ March 1958 TN 4221 TURBULENT FLOW THROUGH POROUS RESISTANCES SLIGHTLY INCLINEDTO THE FLOW DIRECTION_ Albert L. Loeffler_ Jr._ and Morris Perlmutter_ February 1958 TN 4226 ANALYSIS OF HARMONIC FORCES PRODUCED AT HUBBY IMBALANCES IN HELI- COPTER ROTOR BLADES_ Morris Morduchow and A. Muzyka_April 1958 TN 4227 DRAG MINIMIZATION FORWINGS IN SUPERSONIC FLOW_ WITHVARIOUS CONSTRAINTS_ Max. A. Heaslet and Franklyn B. Fuller_ February 1958 TN4228 EFFECTS OFFIXING BOUNDARY-LAYER TRANSITION FORAN UNSWEPT-WING MODEL ANDAN EVALUATION OF POROUS TUNNEL-WALL INTERFERENCE FORMACH NUMBERS FROM 0.60 TO 1.40_ Louis S. Stivers_ Jr._ and Garth W.

Lippmann_April 1958 TN4229 STAGNATION-POINT HEAT TRANSFER TO BLUNT SHAPES IN HYPERSONIC FLIGHT_ INCLUDING EFFECTS OFYAW_ Alfred J. Eggers_ Jr._ C. Frederick Hansen_Bernard E. Cunningham_ April 1958 TN 4230 PRANDTL-MEYER EXPANSION OF CHEMICALLY REACTING GASES IN LOCAL CHEMICAL ANDTHERMODYNAMIC EQUILIBRIUM_ Steve P. Heims_March 1958 TN4231 SKIN-FRICTION MEASUREMENTS IN INCOMPRESSIBLE FLOW_ Donald W. Smith and John H. Walker_ March 1958 TN 4232 A METHOD FORTHE'CALCULATION OF WAVE DRAG ONSUPERSONIC-EDGED WINGS ANDBIPLANES_ Harvard Lomaxand LomaE. Sluder_ March 1958 TN 4233 EXPERIMENTAL STUDY OFTHEEQUIVALENCE OF TRANSONIC FLOW ABOUT SLENDER CONE-CYLINDERS OF CIRCULAR ANDELLIPTIC CROSS SECTION_ William A. Page_April 1958 TN 4235 OBSERVATIONS OF TURBULENT-BURST GEOMETRY ANDGROWTH IN SUPERSONIC FLOW_ Carlton S. James_April 1958 EFFECTS OFMACH NUMBER ANDWALL-TEMPERATURE RATIOONTURBULENT HEAT TN 4236 TRANSFER AT MACH NUMBERS FROM 3 TO 5_ Thorval Tendeland_April 1958 NORMAL COMPONENT OF INDUCED VELOCITY FORENTIRE FIELD OF A UNIFORM- TN4238 LY LOADED LIFTINGROTOR WITHHIGHLY SWEPT WAKE AS DETERMINED BY ELECTROMAGNETIC ANALOG_ Walter Castles_ Jr._ HowardL. Durham_ Jr._ and Jirair Kevorkian_ June 1958 EXPERIMENTAL INVESTIGATION OF THEDRAG OFFLATPLATES ANDCYLINDERS TN 4239 IN THESLIPSTREAM OFA HOVERING ROTOR_ John W. McKeeand Rodger L.

Naeseth_ April 1958 AN APPROXIMATE METHOD FORDESIGN ORANALYSIS OF TWO-DIMENSIONAL SUB- TN 4241 SONIC FLOW PASSAGES_ E. Floyd Valentine_ April 1958 GENERAL SOLUTIONS FORFLOW PAST SLENDER CAMBERED WINGS WITHSWEPT TN4242 TRAILINGEDGES ANDCALCULATION OFADDITIONAL LOADING DUETO CONTROL SURFACES_ E. B. Klunker and Keith C. Harder_ May 1958 TN4243 AN EXPERIMENTAL STUDY OF THETURBULENT BOUNDARY LAYER ONA SHOCK- TUBE WALL_ Paul B. Gooderum_ June 1958 SUMMARY OF EXPERIMENTAL HEAT-TRANSFER MEASUREMENTS IN TURBULENT TN 4248 FLOW FORA MACH NUMBER RANGE FROM 0.87 TO 5.05_ Maurice J. Rrevoort and Barbara D. Arabian_ May 1958 TN4251 AN EXPERIMENTAL INVESTIGATION OF WAKE EFFECTS ONHYDRO-SKIS_ Ellis E. McBride and Lloyd J. Fisher_ Jr._ May 1958 FLIGHTINVESTIGATION OF EFFECTS OF RETREATING-BLADE STALLONBEND- TN4254 ING ANDTORSIONAL MOMENTS ENCOUNTERED BYA HELICOPTER ROTOR BLADE_ LeRoy H. Ludi_ May 1958 TN 4255 WIND-TUNNEL INVESTIGATION AT LOWSPEEDS OFFLIGHTCHARACTERISTICS OF A SWEPTBACK WING JET-TRANSPORT AIRPLANE MODEL EQUIPPED WITHAN EXTERNAL-FLOW JET-AUGMENTED SLOTTED FLAP_Joseph L. Johnson_ Jr._ July 1958 TN 4257 RESULTS OF AN EXPERIMENTAL INVESTIGATION OF SMALL VISCOUS DAMPERS_ Milton A. Silveira_ DomenicJ. Maglieri_ and GeorgeW. Brooks_ June 1958 TN 4258 A NUMERICAL METHOD FOREVALUATING WAVE DRAG_ GeorgePreston_ Gerard J. Pesman_ February 1958 TN 4259 TEMPERATURE-PRESSURE-TIME RELATIONS IN A CLOSED CRYOGENIC CONTAIN- ER_Sidney C. Huntley_ February 1958 TN 4260 GROUND REFLECTION OF JET NOISE_ Walton L. Howes_April 1958 TN 4262 ANALYSIS OFTURBULENT FLOW ANDHEATTRANSFER ONA FLATPLATEAT HIGHMACH NUMBERS WITHVARIABLE FLUID PROPERTIES_ Robert G. Deiss- ler and A. L. Loeffler_ Jr._ April 1958 TN 4265 COMPOSITION ANDTHERMODYNAMIC PROPERTIES OFAIR IN CH_ICAL EQUILIBRIUM_ W. E. Moeckel and Kenneth C. Weston_April 1958 TN 4268 DROPLET IMPINGEMENT ANDINGESTION BYSUPERSONIC NOSE INLET IN SUB- SONIC TUNNEL CONDITIONS_ ThomasF. Gelder_ May 1958 TN 4269 TRANSONIC DRAG OF SEVERAL JET-NOISESUPPRESSORS_ Warren J. North_ April 1958 TN 4270 A PERFORMANCE ANALYSIS OFMETHODS FORHANDLING EXCESS INLETFLOW AT SUPERSONIC SPEEDS_ Donald P. Hearth and JamesF. Connors_May TN4271 MAXIMUM THEORETICAL TANGENTIAL VELOCITY COMPONENT POSSIBLE FROM STRAIGHT-BACK CONVERGING ANDCONVERGING-DIVERGING STATORS AT SUPERCRITICAL PRESSURE RATIOS_ ThomasP. Moffitt_ April 1958 TN 4272 USEOF THECOANDA EFFECT FOROBTAINING JET DEFLECTION ANDLIFT WITH A SINGLE FLAT-PLATE DEFLECTION SURFACE_ UweH. von Glahn_ June 1958 TN4273 ONPAIRSOF SOLUTIONS OF A CLASS OF INTERNAL VISCOUS FLOW PROBLEMS WITHBODY FORCES_ SimonOstrach and Lynn V. Albers_ June 1958 TN4274 MEASUREMENT OF THEEFFECT OFAN AXIALMAGNETIC FIELD ONTHEREYNOLDS NUMBER OF TRANSITION IN MERCURY FLOWING THROUGH A GLASS TUBE_ Michel Bader and William C. A. Carlson_ May 1958 TN 4277 A BODY MODIFICATION TO REDUCE DRAG DUETO WEDGE ANGLE OF WING WITH UNSWEPT TRAILINGEDGE_ William C. Pitts and Jack N. Nielson_ July TN 4278 APPLICATION OF STATISTICAL THEORY TO BEAM-RIDER GUIDANCE IN THE PRESENCE OF NOISE. II - MODIFIED WIENER FILTERTHEORY_ Elwood C.

Stewart_ June 1958 TN4279 EFFECTS OF FIXING TRANSITION ONTHETRANSONIC AERODYNAMIC CHARAC- TERISTICS OF A WING-BODY CONFIGURATION AT REYNOLDS _BERS FROM 2.4 TO 12 MILLION_Lynn W. Hunton_ July 1958 TN4281 SECOND-ORDER SLENDER-BODY THEORY - AXISYMMETRIC FLOW_ Milton Van Dyke_ September1958 TN4282 BOUNDARY-LAYER STABILITYDIAGRAMS FORELECTRICALLY CONDUCTING FLUIDS IN THEPRESENCE OFA MAGNETIC FIELD_ Vernon J. Rossow_August 1958 FULL-SCALE WIND-TUNNEL TESTS OF A 35° SWEPTBACK-WING AIRPLANE WITH TN4283 BLOWING FROM THESHROUD AHEAD OF THETRAILING-EDGE FLAPSjWilliam H. Tolhurst_ Jr._ July 1958 TN4288 TURBULENCE ANDTEMPERATURE FLUCTUATIONS BEHIND A HEATED GRID_R.

R. Mills_ Jr._ A. L. Kistler_ V. O'Brien_ and S. Corrsinj August TN 4289 BOUNDARY-INDUCED DOWNWASH DUETO LIFT IN A TWO-DIMENSIONAL SLOTTED WINDTIPNNEL_ SamuelKatzoff and Raymond L. Barger_ June 1958 TN 4290 A FUSELAGE ADDITION TO INCREASE DRAG-RISEMACH NUMBER OF SUBSONIC AIRPLANES AT LIFTING CONDITIONS_ Richard T. Whitcomb_June 1958 TN 4293 SPECIAL BODIES ADDED ONA WINGTO REDUCE SHOCK-INDUCED BOUNDARY- LAYER SEPARATION AT HIGHSUBSONIC SPEEDS_ Richard T. Whitcomb_ June 1958 TN 4294 EFFECTS OFNOSE SHAPE ANDSPRAY CONTROL STRIPSONEMERGENCE AND PLANING SPRAY OF HYDRO-SKI MODELS_ John R. McGehee_ July 1958 REFLECTION ANDTRANSMISSION OF SOUND BYA SLOTTED WALLSEPARATING TN 4295 TWO MOVING FLUID STREAMS_ Raymond L. Barger_ June 1958 TN4298 EXPLORATORY WIND-TUNNEL INVESTIGATION TO DETERMINE THELIFT EFFECTS OF BLOWING OVER FLAPS FROM NACELLES MOUNTED ABOVE THEWING_ John M. Riebe and Edwin E. Davenport_ June 1958 TN4299 EFFECTS OF FABRICATION-TYPE ROUGHNESS ONTURBULENT SKINFRICTION AT SUPERSONIC SPEEDS_ K. R. Czarnecki_ John R. Sevier_ Jr._ and Melvin M. Carmel_ July 1958 TN4300 HEAT-TRANSFERAND PRESSURE MEASUREMENTS ONFLAT-FACED CYLINDERS AT A MACH NUMBER OF 2_ William E. Stoney_ Jr._ and J. ThomasMarkley_ July 1958 EFFECTS OF BOUNDARY-LAYER DISPLACEMENT ANDLEADING-EDGE BLUNTNESS ON TN 4301 PRESSURE DISTRIBUTION_ SKINFRICTION_ ANDHEATTRANSFER OF BODIES AT HYPERSONIC SPEEDS_ Mitchel H. Bertram and Arthur Henderson_Jr._ July 1958 TN 4302 ANALYTICAL ANDEXPERIMENTAL INVESTIGATION OFAERODYNAMIC FORCES AND MOMENTS ONLOW-ASPECT-RATIO WINGS UNDERGOING FLAPPING OSCILLATIONS_ D. S. Woolston_ S. A. Clevenson_ and S. A. Leadbetter_ August 1958 TN 4308 TRANSIENT TEMPERATURE DISTRIBUTION IN A TWO-COMPONENT SEMI-INFINITE COMPOSITE SLABOFARBITRARY MATERIALS SUBJECTED TOAERODYNAMIC HEATING WITHA DISCONTINUOUS CHANGE IN EQUILIBRIUM TEMPERATURE OR HEAT-TRANSFER COEFFICIENT_ Robert L. Trimpi_ September 1958 TN 4311 PRANDTL NUMBER EFFECTS ONUNSTEADY FORCED-CONVECTION HEATTRANSFER_ Ephraim M. Sparrow and John L. Gregg_June 1958 TN 3212 INTERNAL CHARACTERISTICS ANDPERFORMANCE OFAN AERODYNAMICALLY CONTROLLED_ VARIABLE-DISCHARGE CONVERGENT NOZZLE_ Jack G. McArdle_ July 1958 TN 4313 EFFECT OFFAVORABLE PRESSURE GRADIENTS ONTRANSITION FORSEVERAL BODIES OFREVOLUTION AT MACH 3.12_ John R. Jack_ July 1958 TN 4315 AN ESTIMATE OFTHEFLUCTUATING SURFACE PRESSURES ENCOUNTERED IN THE REENTRY OFA BALLISTICMISSILE_Edmund E. Callaghan_ July 1958 TN 4316 FRICTION ANDWEAR WITHREACTIVE GASES AT T_MPERATURES UP TO 1200 ° F_ GordenP. Allen_ Donald H. Buckley_ and Robert L. Johnson_ September 1958 TN 4320 COMPRESSIBLE LAMINAR FLOW ANDHEATTRANSFER ABOUT A ROTATING ISOTHERMAL DISK_ SimonOstrach and Philip R. Thornton_ August 1958 TN 4321 AN ANALYTICAL STUDY OF TURBULENT ANDMOLECULAR MIXINGIN ROCKET COMBUSTION_ David Ao Bittker 3 September 1958 TN 4322 ORDINATES ANDTHEORETICAL PRESSURE-DISTRIBUTION DATAFORNACA6- AND 6A-SERIES AIRFOIL SECTIONS WITHTHICKNESSES FROM 2 TO 21 ANDFROM 2 TO 15 PERCENT CHORD_ RESPECTIVELY_ Elizabeth W. Patterson and Albert L. Braslow_ September 1958 TN 4325 A MACH 4 ROCKET-POWERED SUPERSONIC TUNNEL USINGAMMONIA-OXYGEN AS WORKING FLUID_Robert W. Graham_Eleanor Guentert_ and Vearl N.

Huff_ September 1958 TN4327 HYPERSONIC VISCOUS FLOW OVER SLENDER CONES 3 Lawerance Talbot_ Toyoki Koga_ Pauline M. Sherman_September 1958 TN 4330 FLOW INDUCED BY A ROTOR IN POWER-ON VERTICAL DESCENT_ Walter Castles_ Jr._ July 1958 TN 4333 EFFECT OF SOME EXTERNAL CROSSWISE STIFFENERS ONTHEHEAT TRANSFER ANDPRESSURE DISTRIBUTION ONA FLAT PLATE AT MACH NUMBERS OF 0.77_ 1.39_ AND1.98_ HowardS. Carter_ September 1958 TN 4336 EXPERIMENTAL INVESTIGATION OFAXIAL ANDNORMAL FORCE CHARACTERIS- TICS OF SKEWED NOZZLES_ David J. Cartor_ Jr._ and Allen R. Vick_ September 1958 TN 4337 AN INVESTIGATION OF SOME PHENOMENA RELATING TO AURAL DETECTION OF AIRPLANES_ Harvey H. Hubbardand DomenicJ. Maglieri_ September TN 4343 A COMPARISON OF TWO METHODS FORCAL(_JLATING TRANSIENT TEMPERATURES FORTHICKWALLS_ JamesJo Buglia and Helen Brinkworth_ August 1958 TN 4345 SIMILARSOLUTIONS FORTHECOMPRESSIBLE BOUNDARY LAYER ONA YAWED CYLINDER WITHTRANSPIRATION COOLING_ Ivan E. Beckwith_ September TN4347 A NONLINEAR THEORY FORPREDICTING THEEFFECTS OFUNSTEADY LAMINAR_ TURBULENT_ ORTRANSITIONAL BOUNDARY LAYERS ONTHEATTENUATION OF SHOCK WAVES IN A SHOCK TUBE WITHEXPERIMENTAL COMPARISON_ Robert Lo Trimpi and Nathaniel Bo Cohen_September 1958 TN 4350 THEORETICAL DISTRIBUTION OF LAMINAR-BOUNDARY-LAYER THICKNESS_ BOUNDARY-LAYER REYNOLDS NUMBER ANDSTABILITYLIMIT_ ANDROUGHNESS REYNOLDS NUMBER FORA SPHERE ANDDISK IN INCOMPRESSIBLE FLOWjNeal Tetervin_ September 1958 TN 4351 SUMMARY OFMETHODS OFMEASURING ANGLE OF ATTACK ONAIRCRAFT, William Gracey_ August 1958 TN 4352 TABLES ANDGRAPHS OFNORMAL-SHOCK PARAMETERS AT HYPERSONIC MACH NUMBERS ANDSELECTED ALTITUDES_ Paul W. Huber_ September 1958 EXPLORATORY WIND-TUNNEL INVESTIGATION AT HIGHSUBSONIC ANDTRAN- TN4353 SONICSPEEDS OF JET FLAPSONUNSWEPT RECTANGULAR WINGS_ Vernard E.

Lockwoodand Raymond D. Vogler_ August 1958 TN4354 MEASUREMENTS IN A SHOCK TUBE OF HEAT-TRANSFER RATES AT THESTAGNA- TION POINTOF A 1.O-INCH-DIAMETER SPHERE FORREAL-GAS TEMPERATURES UP TO 7_900 ° R_ Alexander P. Sabol_ August 1958 TN 4355 LOW TIP MACH NUMBER STALLCHARACTERISTICS ANDHIGHTIP MACH NUMBER COMPRESSIBILITY EFFECTS ONA HELICOPTER ROTOR HAVING AN NACA 0009 TIP AIRFOIL SECTION_ Robert D. Powell_ Jr._ and Paul J. Carpenter_ July 1958 EFFECTS OF COMPRESSIBILITY ONROTOR HOVERING PERFORMANCE ANDSYN- TN 4356 THESIZED BLADE-SECTION CHARACTERISTICS DERIVED FROM MEASURED ROTOR PERFORMANCE OF BLADES HAVING NACA 0015 AIRFOIL TIP SECTIONS_ James P. Shivers and Paul J. Carpenter_ September 1958

LIFT ANDPROFILE-DRAG CHARACTERISTICS OF ANNACA0012 AIRFOIL TN 4357 SECTION AS DERIVED FROM MEASURED HELICOPTER-ROTOR HOVERING PERFORMANCE_ Paul J. Carpenter_ September 1958 TN 4359 A REVIEW OF THETHERMODYNAMIC_ TRANSPORT_ ANDCHEMICAL REACTION RATE PROPERTIES OFHIGH-TEMPERATURE AIR_ Frederick C. Hansenand Steve P. Heims_July 1958 TN 4360 MEASUREMENTS OFTHEEFFECTS OFWALLOUTFLOW ANDPOROSITY ONWAVE ATTENUATION IN A TRANSONIC WINDTUNNEL WITHPERFORATED WALLS_ Joseph M. Spiegel_ Phillips J. Tunnell_ and Warren S. Wilson_ August 1958 TN 4361 IDEALIZED WINGS ANDWING-BODIES AT A MACH NUMBER OF 3_ Elliott D.

Katzen_ July 1958 TN 4362 FORCE ANDPRESSURE MEASUR_ENTS AT TRANSONIC SPEEDS FORSEVERAL BODIES HAVING ELLIPTICALCROSS SECTIONS_ John B. McDevitt and Robert A. Taylor_ September 1958 SI_IPLIFIEDMETHOD FORDETERMINATION OF CRITICALHEIGHT OF DIS- TN 4363 TRIBUTED ROUGHNESS PARTICLES FORBOUNDARY-LAYER TRANSITION AT MACH NUMBERS FROM 0 TO 5_ Albert L. Braslow and EugeneC. Knox_ September AN INVESTIGATION OF SUPERSONIC TURBULENT BOUNDARY LAYERS ONSLENDER TN 4364 BODIES OF REVOLUTION IN FREEFLIGHTBYUSEOFA MACH-ZEHNDER INTER- FEROMETER ANDSHADOW-GRAPHS_ Alvin Seiff and Barbara J. Short_ September 1958 LARGE-SCALE WIND-TUNNEL TESTS OF AN AIRPLANE MODEL WITHAN UNSWEPT TN4365 ASPECT-RATIO-10 WING_ TWO PROPELLERS_ ANDAREA-SUCTION FLAPS_ J. A. Weiberg_ R. N. Griffin_ Jr._ and G. L. Florman_ September TN 4366 THEEFFECTS OF AN INVERSE-TAPER LEADING-EDGE FLAPONTHEAERODYNAMIC CHARACTERISTICS IN PITCHOF A WING-BODY COMBINATION HAVING AN ASPECT RATIOOF 3 AND45° OF SWEEPBACK AT MACH NUMBERS TO0.92_ Fred A.

Demeleand K. HarmonPowell_ August 1958 WIND-TUNNEL TESTS OFA FULL-SCALE HELICOPTER ROTOR WITHSYMMETRICAL TN 4367 ANDWITHCAMBERED BLADE SECTIONS AT ADVANCE RATIOS FROM 0.3 TO 0.4_ John L. McCloud_III_ and George B. McCullough_ September 1958 TN 4368 A STUDY OF SEVERAL THEORETICAL METHODS FORCOMPUTING THEZERO-LIFT WAVE DRAG OFA FAMILYOF OPEN-NOSED BODIES OF REVOLUTION IN THEMACH NUMBER RANGE OF 2.0 TO4.0_ Leroy L. Presley_ _nmett A. Mossman_ September 1958 TN4369 SLIP-FLOW HEATTRANSFER FROM CYLINDERS IN SUBSONIC AIRSTREAMS_ Lionel V. Baldwin_ September 1958 TN 4370 SOME NUMERICAL SOLUTIONS OF SIMILARITYEQUATIONS FORTHREE- DIMENSIONAL LAMINAR INCOMPRESSIBLE BOUNDARY-LAYER FLOWS_ Peggy L.

Yohner and Authur G. Hansonj September 1958 TN4374 RATE OF REACTION OF GASEOUS FLUORINE WITHWATER VAPOR AT 35° C_ Vernon A. Slabey and EdwardA. Fletcher_ September 1958 TN4375 APPROXIMATE SOLUTIONS OFA CLASS OF SIMILARITYEQUATIONS FORTHREE- DIMENSIONAL LAMINARINCOMPRESSIBLE BOUNDARY-LAYER FLOWS_ Arthur G.

Hanson and HowardZ. Herzig_ September 1958 TN 4376 ANALYTICAL ANDEXPERIMENTAL INVESTIGATION OF T_q_PERATURE RECOVERY FACTORS FORFULLYDEVELOPED FLOW OFAIR IN A TUBE_ R. G. Deissler_ W. F. Weiland_ Jr._ and W. H. Lowdermilk_ September 1958 TN4377 USEOF THECOANDA EFFECT FORJET DEFLECTION ANDVERTICAL LIFT WITH MULTIPLE-FLAT-PLATE ANDCURVED-PLATE DEFLECTION SURFACES. APPEN- DIX B: ESTIMATED PERFORMANCE OFMULTIPLE-FLAT-PLATE DEFLECTORS_ UweH. von Glahn and ThomasF. Gelder_ September 1958 TN 4378 PRELIMINARY HEAT-TRANSFER STUDIES ONTWO BODIES OF REVOLUTION AT ANGLE OF ATTACK AT A MACH NUMBER OF 3.12_ NormanSandsand John R. Jack# September 1958 TN4380 APPROXIMATE METHOD FORCALCULATION OF LAMINAR BOUNDARY LAYER WITH HEATTRANSFER ONA CONE AT LARGE ANGLE OFATTACK IN SUPERSONIC FLOW_ William E. Brunk_ September 1958 TN4382 INVESTIGATION OF BOILINGBURNOUT ANDFLOW STABILITYFORWATER FLOW- ING IN TUBES_ Warren H. Lowdermilk_ Chester D. Lanzo_ and Byron L. Siegel_ September 1958 TN 4383 A COOLED-GAS PYROMETER FORUSEIN HIGH-TEMPERATURE GASSTREAMS_ L. N. Krause_ R. C. Johnson_ and G. E. Glawe# September 1958 TN 4384 ANALYSIS OFTURBULENT FLOW ANDHEATTRANSFER IN NONCIRCULAR PASSAGES_ Robert G. Deissler and Maynard F. Taylor_ September 1958 TN 4385 COMPARISON OF SHOCK-EXPANSION THEORY WITHEXPERIMENT FORTHELIFT_ DRAG# ANDPITCHING-MOMENT CHARACTERISTICS OF TWO WING-BODY COMBINA- TIONSAT M = 5.0_ Raymond C. Savin_ September 1958 TN4388 EFFECTS OF NOSE ANGLE ANDMACH NUMBER ONTRANSITION ONCONES AT SUPERSONIC SPEEDS# Mary W. Jackson_ September 1958 TN4389 EFFECT OF ADVANCE RATIOONFLIGHTPERFORMANCE OFA MODIFIED SUPER- SONIC PROPELLER_ Jerome B. Hammack and ThomasC. O'Bryan_ September TN 4391 MASS TRANSFER COOLING NEAR THESTAGNATION POINT_Leonard Roberts_ September 1958 A THEORETICAL STUDY OF STAGNATION-POINT ABLATION_ Leonard Roberts_ TN 4392 September 1958 MEASUREMENTS OFAERODYNAMIC FORCES ANDMOMENTS AT SUBSONIC SPEEDS TN 4402 ONA SIMPLIFIEDT-TAlL OSCILLATING IN YAW ABOUT THEFIN MIDCHORD_ ShermanA. Clevenson and SumnerA. Leadbetter_ September 1958 EFFECTS OF PROPELLER POSITION ANDOVERLAP ONTHESLIPSTREAM DEFLEC- TN 4404 TION CHARACTERISTICS OFA WING-PROPELLER CONFIGURATION EQUIPPED WITHA SLIDINGANDFOWLER FLAP_William C. Hayes_ Jr._ Richard F.

Kuhn_ and Irving R. Sherman_September 1958 FREE-FLIGHT INVESTIGATION TO DETERMINE THEDRAG OFFLAT- ANDVEE- TN 4405 WINDSHIELD CANOPIES ONA PARABOLIC FUSELAGE WITHANDWITHOUT TRANSONIC INDENTATION BETWEEN MACH NUMBERS OF0.75 AND1.35_ Walter L. Kouyoumjian and SherwoodHoffman_ September 1958 TN 4407 EFFECTS OF GROUND PROXIMITY ONTHETHRUST OFA SIMPLEDOWNWARD- DIRECTED JET BENEATH A FLAT SURFACE_ Kenneth D. Spreemannand Irving R. Sherman_September 1958 THETHEORY OF DIFFUSION IN STRAINED SYSTEMS_ Louis A. Girifalco TN 4408 and Hubert H. Grimes_ September 1958 Applicable NASA Memoranda (Memo) MEMO 2-5-59E AN EQUATION FOR THE MEAN VELOCITY DISTRIBUTION OF BOUNDARY LAYERS, V. A. Sandborn, February 1959 Equations are given for the velocity profile, boundary layer thickness, and momentum thickness for both the laminar and turbulent boundary layers. The equations were achieved assuming incompressible flow and were based on channel flow.

These equations were not derived based on the Blasius flat plate solution, but the velocity distributions achieved in each method were compared.

Results i. The proposed equation fitted measured turbulent boundary- layer velocity profiles quite well.

2. The relation for turbulent boundary layers agreed with the present concepts of similarity in the outer region of the boundary layer in that a one-parameter family of profiles was obtained.

3. The results were in reasonable agreement with available experimental data over the whole profile, including the region near the wall. It was demonstrated that the logarithmic pro- file did not represent all experimental data.

4. A unique relation between the profile form factor and the ratio of displacement thickness to boundary-layer thickness was obtained from the equations presented for turbulent separation.

5. The general equation reduced to a laminar profile which accurately represented the Blasius flow.

Not Applicable NASA Memoranda (Memo) MEMO I0-I-58E TURBULENT HEAT-TRANSFER COEFFICIENTS IN THE VICINITY OF SURFACE PROTURBERANCES, Richard J. Wisniewski, October 1958 MEMO I0-I-58H LIFT AND DRAG OF SWEPT-WING FIGHTER AIRPLANE AT TRANSONIC AND SUPERSONIC SPEEDS (WITH LIST OF REFERENCES), Jack Nugent, January 1959 MEMO I0-2-58L AERODYNAMIC CHARACTERISTICS FOR COMBINED ANGLES OF ATTACK AND SIDESLIP OF LOW-ASPECT-RATIO CRUCIFORM-WING MISSILE CONFIGURA- TION EMPLOYING VARIOUS CANARD AND TRAILING-EDGE FLAP CONTROLS AT MACH NUMBER OF 2.01, Ross B. Robinson and M. Leroy Spearman, October 1958 MEMO I0-3-58A INCLINED BODIES OF VARIOUS CROSS SECTIONS AT SUPERSONIC SPEEDS, Leland H. Jorgensen, November 1958 MEMO I0-5-58A KIFT, DRAG, AND PITCHING MOMENT OF AN ASPECT-RATIO-2 TRIANGULAR WING WITH LEADING-EDGE FLAPS DESIGNED TO SIMULATE CONICAL CAMBER, Gene P. Menees, December 1958 MEMO I0-5-58L SOME EFFECTS OF HORIZONTAL-TAIL POSITION ON THE VERTICAL-TAIL PRESSURE DISTRIBUTIONS OF A COMPLETE MODEL IN SIDESLIP AT HIGH SUBSONIC SPEEDS, William J. Alford, Jr., October 1958 MEMO I0-6-58E A THREE-DIMENSIONAL FLOW EXPANDER AS A DEVICE TO INCREASE THE MACH NUMBER IN A SUPERSONIC WIND TUNNEL, Reino J. Salmi, December 1958 MEMO I0-8-58A AN INVESTIGATION OF THE DRAG CHARACTERISTICS OF A TAILLESS DELTA-WING AIRPLANE IN FLIGHT, INCLUDING COMPARISON WITH WIND- TUNNEL DATA, L. Stewart Rolls and Rodney C. Wingrove, November MEMO I0-8-58L EFFECTS OF YAW ON THE HEAT TRANSFER TO A BLUNT CONE-CYLINDER CONFIGURATION AT A MACH NUMBER OF 1.98, Roland D. English, November 1958 MEMO I0-9-58E HEAT-TRANSFER AND FRICTION MEASUREMENTS WITH VARIABLE PROPERTIES FOR AIRFLOW NORMAL TO FINNED AND UNFINNED TUBE BANKS, Robert G.

Ragsdale, December 1958 MEMO I0-I0-58L EFFECT OF NOSE LENGTH, FUSELAGE LENGTH, AND NOSE FINENESS RATIO ON THE LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF TWO COMPLETE MODELS AT HIGH SUBSONIC SPEEDS, Kenneth W. Goodson, October 1958 MEMO I0-II-58L AERODYNAMIC CHARACTERISTICS IN SIDESLIP OF A LARGE-SCALE 49 ° SWEPTBACK WING-BODY-TAIL CONFIGURATION WITH BLOWING APPLIED OVER THE FLAPS AND WING LEADING EDGE, H. Clyde McLemore, October MEMO I0-12-58L TESTS OFAERODYNAMICALLY HEATED MULTIWEB WING STRUCTURES IN A FREEJET AT MACH NUMBER 2. THREE MODELS OF 20-INCH CHORD AND SPAN CONSTRUCTED FROM MAGNESIUM, TITANIUM,ANDALUMINUM ALLOYS, RESPECTIVELY, John R. Davidson and Richard Rosecrans, October MEMO I0-13-58L LOW-SPEED AERODYNAMIC ANDHYDRODYNAMIC CHARACTERISTICS OFA PROPOSED SUPERSONIC MULTIJET WATER-BASED HYDRO-SKI AIRCRAFT WITHUPWARD-ROTATING ENGINES, William W. Petynia, De!win R.

Croom, and Edwin E. Davenport, October 1958 MEMO I0-15-58L TABULATED DATAFROM PRESSURE-DISTRIBUTION INVESTIGATION AT MACH NO. 2.1 OF 45° SWEPTBACK-WING AIRPLANE MODEL AT COMBINED ANGLES OFATTACK ANDSIDESLIP(WITHLIST OF REFERENCES), John P. Gapcynski and Emma Jean Landrum, November1958 MEMO I0-20-58L BASICPRESSURE MEASUREMENTS AT TRANSONIC SPEEDS ONA THIN 45° SWEPTBACK HIGHLY TAPERED WING WITHSYSTEMATIC SPANWISE TWIST VARIATIONSUNTWISTED WING,John P. Mugler, Jr., December1958 MEMO I0-23-58L EFFECTS OF BODY SHAPE ONTHEDRAG OF A 45° SWEPTBACK-WING-BODY CONFIGURATION AT MACH NUMBERS FROM 0.90 TO 1.43, Walter B.

Olstad and ThomasL. Fischetti, November1958 MEMO I0-25-58L HEAT-TRANSFER MEASUREMENTS OF 2 WING-BODY CONFIGURATIONS AT 8° ANGLE OFATTACK FROM FLIGHTTESTFORMACH NUMBERS TO 4.86 AND REYNOLDS NUMBERS TO 19.2 x 106 Katherine C Speegle, December MEMO I0-28-58L AERODYNAMIC CHARACTERISTICS OF SOME FAMILIESOF BLUNT BODIES AT TRANSONIC SPEEDS, Lewis R. Fisher, Arvid L. Keith, Jr. and Joseph R. DiCamil, November1958 HEATTRANSFER IN THETURBULENT INCOMPRESSIBLE BOUNDARY LAYER.

MEMO 12-I-58W I - CONSTANT WALL TEMPERATURE, W. C. Reynolds, W. M. Kays, and S. J. Kline, December1958 IN THETURBULENT INCOMPRESSIBLE BOUNDARY LAYER.

MEMO 12-2-58W HEATTRANSFER II - STEPWALL-TEMPERATURE DISTRIBUTION, W. C. Reynolds, W. M.

Kays, and S. J. Kline, December1958 MEMO 12-3-58A LARGE-SCALE WIND-TUNNEL TESTS OF ANAIRPLANE MODEL WITHAN UNSWEPT, ASPECT-RATIO-10 WING,TWO PROPELLERS, ANDBLOWING FLAPS,Roy N. Griffin, Jr., Curt A. Holzhauser, and JamesA.

Weiberg, December1958 MEMO 12-3-58W HEATTRANSFER IN THETURBULENT INCOMPRESSIBLE BOUNDARY LAYER.

III - ARBITRARY WALL T_MPERATURE ANDHEATFLUX, W. C. Reynolds, W. M. Kays, and S. J. Kline, December1958 MEMO 12-4-58A THREE-DIMENSIONAL ORBITS OF EARTH SATELLITES, INCLUDING EFFECTS OF EARTH OBLATENESS ANDATMOSPHERIC ROTATION, Jack N. Nielsen, Frederick K. Goodwin, and William A. Mersman,December1958 MEMO 12-4-58W HEATTRANSFER IN THETURBULENT INCOMPRESSIBLE BOUNDARY LAYER.

IV - EFFECT OFLOCATION OF TRANSITION ANDPREDICTION OF HEAT TRANSFER IN A KNOWN TRANSITION REGION, W. C. Reynolds, W. M.

Kays, and S. J. Kline, December1958 MEMO 12-5-58L HEATING ANDIMPACT TESTSONINSULATED ANDUNINSULATED BALLISTIC MISSILE FUSE MECHANISMS SUBJECTED TO SIMULATED REENTRY AERODYNA- MIC HEATING (WITHLIST OFREFERENCES), Willie L. Nix, January MEMO 12-5-58W INTERACTION EFFECTS PRODUCED BY JET EXHAUSTING LATERALLY NEAR BASE OF OGIVE-CYLINDER MODEL IN SUPERSONIC MAINSTREAM, P. W.

vinson, J. L. Amick, and H. P. Liepman, February 1959 MEMO 12-14-58WSTRUCTURE OF WEAK SHOCK WAVES IN A MONATOMIC GAS, L. Talbot and F. S. Sherman,January 1959 MEMO 12-15-58L FREE-FLIGHT INVESTIGATION OF A ROCKET-PROPELLED MODEL TO DETER- MINETHEAERODYNAMIC HEATING ONA THIN, UNSWEPT, UNTAPERED, MULTISPAR, ALUMINUM-ALLOY WING AT MACH NUMBERS UP TO 2.22, Emily W. Stephens, January 1959 MEMO 12-21-58E EXPERIMENTAL INVESTIGATION OF COAXIAL JET MIXINGOF TWO SUBSONIC STREAMS AT VARIOUS TEMPERATURE, MACH NUMBER, ANDDIAMETER RATIOS FORTHREE CONFIGURATIONS, Richard R. Burley and Lively Bryant, February 1959 MEMO 12-21-58L THETOTAL-PRESSURE RECOVERY ANDDRAG CHARCTERISTICS OF SEVERAL AUXILIARYINLETSAT TRANSONIC SPEEDS, John S. Dennard, March MEMO 12-25-58A BOUNDARY-LAYER-TRANSITION MEASUREMENTS ONHEMISPHERFS OFVARIOUS SURFACE ROUGHNESSES IN A WINDTUNNEL AT MACH NUMBERS FROM 2.48 TO 3.55, Angelo Bandettini and Walter E. Isler, March 1959 MEMO 12-26-58A THEEFFECT OFLEADING-EDGE SWEEP ANDSURFACE INCLINATION ONTHE HYPERSONIC FLOW FIELD OVER A BLUNT FLATPLATE,Marcus O. Creager, January 1959 MEMO 12-27-58A THEEFFECT OFLOWER SURFACE SPOILERS ONTHETRANSONIC TRIM CHANGE OF A WIND-TUNNEL MODEL OF A FIGHTER AIRPLANE HAVING A MODIFIED DELTA WING,Robert C. Robinson, February 1959 MEMO 12-27-58L WATER-FILM COOLING OF AN 80 ° TOTAL-ANGLE CONE AT AMACH NUMBER OF 2 FOR AIRSTREAM TOTAL TEMPERATURES UP TO 3,000°R, Howard S.

Carter, January 1959 MEMO 12-28-58L BASICPRESSURE MEASUREMENTS AT TRANSONIC SPEEDS ONA THIN45° SWEPTBACK HIGHLY TAPERED WING WITHSYSTEMATIC SPANWISE TWIST VARIATIONS. WING WITHLINEARSPANWISE TWISTVARIATIONS, John P. Mugler, Jr., January 1959 MEMO 12-31-58L FREE-FLIGHT HEAT-TRANSFER INVESTIGATION AT SUPERSONIC SPEEDS AT 2 SLENDER CONE-CYLINDER BODIES AT ANGLE OFATTACK OF 8 ° WITH ONE BODY ROTATING, Ralph A. Falanga, January 1959 MEMO I-2-59E AERODYNAMIC CHARACTERISTICS OF SEVERAL FLAT-BOTTOM CONFIGURA- TIONS AT MACH 3.0 AND 3.5 (WITH LIST OF REFERENCES), Murray Dryer and Roger W. Luidens, January 1959 MEMO I-2-59L A METHOD FOR COMPUTING TURBULENT HEAT TRANSFER IN THE PRESENCE OF A STREAMWISE PRESSURE GRADIENT FOR BODIES IN HIGH-SPEED FLOW, Nathaniel B. Cohen, March 1959 MEMO I-3-59L MEASUREMENTS OF LOCAL HEAT TRANSFER AND PRESSURE ON SIX 2-1NCH- DIAMETER BLUNT BODIES AT A MACH NUMBER OF 4.95 AND AT REYNOLDS NUMBERS PER FOOT UP TO 81 x 106 , Morton Cooper and Edward E.

Mayo, March 1959 MEMO I-4-59L EFFECT OF AFTERBODY-EJECTOR CONFIGURATIONS ON PERFORMANCE AT TRANSONIC SPEEDS OF PYLON-SUPPORTED NACELLE MODEL HAVING HOT- JET EXHAUST, John M. Swihart, Charles E. Meracer and Harry T.

Norton, Jr., February 1959 MEMO I-6-59L INVESTIGATION OF SPHERICAL-WAVE-INITIATED FLOW FIELDS AROUND BODIES, Donald R. McFarland, February 1959 MEMO I-8-59A AERODYNAMIC PERFORMANCE AND STATIC STABILITY AT MACH NUMBERS UP TO 5 OF 2 AIRPLANE CONFIGURATIONS WITH FAVORABLE LIFT INTER- FERENCE (WITH LIST OF REFERENCES), David H. Dennis and Richard H. Petersen, January 1959 MEMO I-8-59L WIND-TUNNEL INVESTIGATION OF SUBNONIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A TILTABLE-WING VERTICAL-TAKE-OFF-AND- LANDING SUPERSONIC BOMBER CONFIGURATION INCLUDING TURBOJET POWER EFFECTS, Robert F. Thompson, Raymond D. Vogler, and William C. Moseley,Jr., January 1959 MEMO I-I0-59A TWO-DIMENSIONAL, SUPERSONIC, LINEARIZED FLOW WITH HEAD ADDITION, Harvard Lomax, February 1959 MEMO I-I0-59E PRESSURE DRAG OF AXISYMMETRIC COWLS HAVING LARGE INITIAL LIP ANGLES AT MACH NUMBERS FROM 1.90 TO 4.90, Nick E. Samanich, January 1959 EXPERIMENTAL INVESTIGATION OF AERODYNAMIC EFFECTS OF EXTERNAL MEMO I-II-59E COMBUSTION IN AIRSTREAM BELOW TWO-DIMENSIONAL SUPERSONIC WING AT MACH 2.5 AND 3.0, Robert G. Dorsch, John S. Serafini, Edward A. Fletcher and I. Irving Pinkel, March 1959 MEMO 1-16-59A A NUMERICAL METHOD FORCALCULATING THEWAVE DRAG OFA CONFIGURA- TION FROM THESECOND DERIVATIVE OF THEAREADISTRIBUTION OF A SERIES OF EQUIVALENT BODIES OF REVOLUTION, Lionel L. Levy, Jr.

and Kenneth K. Yoshikawa, April 1959 MEMO 1-16-59L SEMIEMPIRICAL PROCEDURE FORESTIMATING LIFT ANDDRAG CHARAC- TERISTICS OF PROPELLER-WING-FLAP CONFIGURATIONS FORVERTICAL- ANDSHORT-TAKE-OFF-AND-LANDING AIRPLANES, Richard E. Kuhn, February 1959 MEMO 1-19-59A FINISHINGANDINSPECTION OF MODEL SURFACES FORBOUNDARY-LAYER- TRANSITION TESTS,Max E. Wilkins and John F. Darsow, February TRAJECTORY CONTROL FORVEHICLES ENTERING THEEARTH'S ATMOSPHERE MEMO 1-19-59L AT SMALL FLIGHT-PATH ANGLES, John M. Eggleston and John W.

Young, February 1959 MEMO 1-20-59A BOUNDARY-LAYER TRANSITION ONHOLLOW CYLINDERS IN SUPERSONIC FREE FLIGHTAS AFFECTED BY MACH NUMBER ANDA SCREW-THREAD TYPEOF SURFACE ROUGHNESS, Carlton S. James, February 1959 MEMO 1-20-59L MEASUREMENTS OF TOTAL HEMISPHERICAL EMISSIVITYOF SEVERAL STABLY OXIDIZED METALS ANDSOME REFRACTORY OXIDECOATINGS, William R.

Wade, January 1959 MEMO 1-21-59A EXPERIMENTAL INVESTIGATION OF THEPRESSURE RISE REQUIRED FORTHE INCIPIENTSEPARATION OF TURBULENT BOUNDARY LAYERS IN TWO- DIMENSIONAL SUPERSONIC FLOW,Donald M. Kuehn, February 1959 MEMO 1-22-59A PRESSURE DISTRIBUTIONS AT TRANSONIC SPEEDS FORBUMPY ANDINDENTED MIDSECTIONS OF A BASICPARABOLIC-ARC BODY,Robert A. Taylor, February 1959 MEMO 1-23-59A LOW-SPEED WIND-TUNNEL INVESTIGATION OF BLOWING BOUNDARY-LAYER CONTROL ONLEADING- ANDTRAILING-EDGE FLAPSOF A LARGE-SCALE, LOW-ASPECT-RATIO, 45° SWEPT-WING AIRPLANE CONFIGURATION, Ralph L. Maki, January 1959 MEMO 1-23-59L MAXIMUM MEAN LIFT COEFFICIENT CHARACTERISTICS AT LOW TIP MACH NUMBERS OF A HOVERING HELICOPTER ROTOR HAVING ANNACA641A012 AIRFOIL SECTION, Robert D. Powell, Jr., February 1959 MEMO 1-24-59L STATICLIFT, DRAG,ANDPITCHING-MOMENT CHARACTERISTICS OF WINGS WITHARROW ANDMODIFIED-DIAMOND PLANFORMS COMBINED WITHSEVERAL DIFFERENT BODIES AT MACH NUMBERS OF 2.97, 3.35, AND3.71, Dennis F. Hasson and John G. Presnell, Jr,, January 1959 MEMO 1-25-59L EFFECT OF CONVEX LONGITUDINAL CURVATURE ONTHEPLANING CHARAC- TERISTICS OFA SURFACE WITHOUT DEAD RISE, Elmo J. Mottard, February 1959 MEMO 1-26-59L FLIGHTINVESTIGATION OF THESURFACE PRESSURE DISTRIBUTION AND FLOW FIELDAROUND ANELLIPTICALSPINNER, Lovic P. ThomasIII, February 1959 MEMO 1-27-59E DESIGN ANDOPERATING CRITERIAFORFLUORINE DISPOSAL BY REACTION WITHCHARCOAL, Harold W. Schmidt, February 1959 MEMO 1-27-59L LOW-SPEED WIND-TUNNEL INVESTIGATION TO DETERMINE THEAERODYNAMIC CHARACTERISTICS OF A RECTANGULAR WING EQUIPPED WITHA FULL-SPAN ANDAN INBOARD HALF-SPAN JET-AUGMENTED FLAPDEFLECTED 55° , Thomas G. Gainer, February 1959 MEMO 1-31-59L PARASITE-DRAG MEASUREMENTS OF FIVE HELICOPTER ROTOR HUBS,Gary B. Churchill and Robert D. Harrington, February 1959 MEMO 2-5-59E AN EQUATION FORTHEMEAN VELOCITY DISTRIBUTION OF BOUNDARY LAYERS, V. A. Sandborn, February 1959 MEMO 2-5-59L FREE-FLIGHT TESTOFA TECHNIQUE FORINFLATING AN NASA 12-FOOT- DIAMETER SPHERE AT HIGHALTITUDES, Alan B. Kehlet and Herbert G. Patterson, January 1959 MEMO 2-5-59W HEATTRANSFER IN A LIQUID METAL FLOWING TURBULENTLY THROUGH A CHANNEL WITHA STEPFUNCTION BOUNDARY TEMPERATURE, H. F.

Poppendiek, March 1959 MEMO 2-8-59L AN INVESTIGATION OF THEEFFECT OF A HIGHLY FAVORABLE PRESSURE GRADIENT ONBOUNDARY-LAYER TRANSITION AS CAUSED BYVARIOUS TYPES OF ROUGHNESSES ONA 10-FOOT-DIAMETER HEMISPHERE AT SUBSONIC SPEEDS, John B. Peterson, Jr., and Elmer A. Horton, April 1959 MEMO 2-9-59L AN EXPERIMENTAL STUDY AT A MACH NUMBER OF 3 OFTHEEFFECT OF TURBULENCE LEVELANDSANDPAPER-TYPE ROUGHNESS ONTRANSITION ON A FLATPLATE,Robert A. Jones, March 1959 MEMO 2-12-59A THEEFFECTS OF TARGET ANDMISSILECHARACTERISTICS ONTHEORETICAL MINIMUM MISSDISTANCE FORA BF_M-RIDER GUIDANCE SYSTEM IN THE PRESENCE OFNOISE, Elwood C. Stewart, Frank Druding, and Togo Nishiura, March 1959 MEMO 2-13-59A THESYNTHESIS OF OPTIMUM HOMING MISSILEGUIDANCE SYSTEMS WITH STATISTICAL INPUTS,Elwood C. Stewart and Gerald L. Smith, April 1959 MEMO 2-13-59L EXTERNAL INTERFERENCE EFFECTS OF FLOW THROUGH STATIC-PRESSURE ORIFICES OFAN AIRSPEED HEAD AT SEVERAL SUPERSONIC MACH NUMBERS ANDANGLES OFATTACK, NormanS. Silsby, March 1959 MEMO 2-17-59W USEOF A STANTON TUBEFORSKIN-FRICTION MEASUREMENTS, S. S.

Abarbanel, R. J. Hakkinen, and L. Trilling, March 1959 MEMO 2-18-59W THEINTERACTION OFAN OBLIQUE SHOCK WAVE WITHA LAMINAR BOUNDARY LAYER,R. J. Hakkinen, I. Greber, L. Trilling, and S. S.

Abarbanel, March 1959 MEMO 2-20-59A FULL-SCALE WIND-TUNNEL INVESTIGATION OFA JET FLAPIN CONJUNC- TIONWITHA PLAINFLAPWITHBLOWING BOUNDARY-LAYER CONTROL ON A 35° SWEPTBACK-WING AIRPLANE, Kiyoshi Aoyagi and David H.

Hickey, March 1959 MEMO 2-20-59E A 20,000-KILOWATT NUCLEAR TURBOELECTRIC POWER SUPPLY FORMANNED SPACE VEHICLES, Robert E. English, Henry O. Slone, Daniel T.

Bernatowicz, Elmer H. Davison, and SeymourLieblein, March 1959 MEMO 2-20-59L TABLES FORTHERAPIDESTIMATION OF DOWNWASH ANDSIDEWASH BEHIND WINGS PERFORMING VARIOUS MOTIONS AT SUPERSONIC SPEEDS, Percy J.

Bobbitt, May 1959 MEMO 2-23-59W EXPLORATORY STUDY OF VENTILATED FLOWS ABOUT YAWED SURFACE- PIERCING STRUTS, John P. Breslin and Richard Skalak, April 1959 MEMO 2-24-59A THEEFFECT OFMOMENT-OF-AREA-RULE MODIFICATIONS ONTHEDRAG,LIFT, ANDPITCHING-MOMENT CHARACTERISTICS OF AN UNSWEPT ASPECT-RATIO-6 WING ANDBODY COMBINATION, Robert R. Dickey, March 1959 MEMO 2-24-59L BASICPRESSURE MEASUREMENTS AT TRANSONIC SPEEDS ONA THIN 45° SWEPTBACK HIGHLY TAPERED WING WITHSYSTEMATIC SPANWISE TWIST VARIATIONS.WING WITHQUADRATIC SPANWISE TWISTVARIATION,John P. Mugler, Jr., April 1959 MEMO 2-25-59A NUMERICAL SOLUTION OF THEFLOW OF A PERFECT GASOVER A CIRCULAR CYLINDER AT INFINITE MACH NUMBER , Frank M. Hamaker,March 1959 MEMO 2-25-59L SEVERAL METHODS FORREDUCING THEDRAG OF TRANSPORT CONFIGURATIONS AT HIGHSUBSONIC SPEEDS, Richard T. Whitcomband Atwood R. Heath, Jr., March 1959 MEMO 2-26-59A SOME FINITE DIFFERENCE SOLUTIONS OF THELAMINAR COMPRESSIBLE BOUNDARY LAYER SHOWING THEEFFECTS OF UPSTREAM TRANSPIRATION COOLING, John T. Howe, February 1959 MEMO 2-27-59A LOW-SPEED TESTS OF SEMISPAN-WING MODELS AT ANGLES OFATTACK FROM 0° TO 180° , David G. Koenig, April 1959 MEMO 2-27-59E DETAILS OF EXACT LOW PRANDTL NUMBER BOUNDARY-LAYER SOLUTIONS FORFORCED ANDFORFREECONVECTION, E. M. Sparrow and J. L.

Gregg, February 1959 MEMO 2-27-59L LOCAL HEATTRANSFER ANDRECOVERY TEMPERATURES ONA YAWED CYLINDER AT A MACH NIIMBER OF 4.15 ANDHIGHREYNOLDS NUMBERS, Ivan E. Beckwi_h and JamesJ. Gallagher, April 1959 MEMO 3-I-59H FLIGHTSTUDIES OF PROBLEMS PERTINENT TO LOW-SPEED OPERATION OF JET TRANSPORTS, Jack Fischel, Stanley P. Butchart, Glenn H. Robinson, and Robert A. Tremant, April 1959 MEMO 3-2-59H FLIGHTSTUDIES OF PROBLEMS PERTINENT TO HIGH-SPEED OPERATION OF JET TRANSPORTS, Stanley P. Butchart, Jack Fischel, Robert A. Tremant, and Glenn H. Robinson, April 1959 MEMO 3-3-59A SUBSONIC AERODYNAMIC CHARACTERISTICS OFAIRPLANE CONFIGURATION WITH63° SWEPTBACK WING ANDTWIN-BOOM TAILS (WITHLIST OF REFERENCES), HowardF. Savage and GeorgeG. Edwards, March MEMO 3-3-59H A SUMMARY OF FLIGHT-DETERMINED TRANSONIC LIFT ANDDRAG CHARA- CTERISTICS OF SEVERAL RESEARCH AIRPLANE CONFIGURATIONS, Donald R. Bellman, April 1959 MEMO 3-4-59L THESHOCK-WAVE NOISEPROBLEM OF SUPERSONIC AIRCRAFT IN STEADY FLIGHT, DomenicJ. Maglieri and Harry W. Carlson, April 1959 MEMO 3-5-59E STABILITYOF CERAMICS IN HYDROGEN BETWEEN 4000 ° AND4500°F, Charles E. May, Donald Koneval, and George C. Fryburg, March MEMO 3-5-59L NOISEPROBLEMS ASSOCIATED WITHGROUND OPERATIONS OF JET AIR- CRAFT,Harvey H. Hubbard, March 1959 MEMO 3-7-59L INFLUENCE OFLARGE POSITIVEDIHEDRAL ONHEAT TRANSFER TO LEADING EDGES OF HIGHLY SWEPT WINGS AT VERY HIGHMACH NUMBERS, Morton Cooper and P. Calvin Stainback, April 1959 MEMO 3-8-59L WIND-TUNNEL INVESTIGATION OFA SMALL-SCALE SWEPTBACK-WING JET- TRANSPORT MODEL EQUIPPED WITHAN EXTERNAL-FLOW JET-AUGMENTED DOUBLE SLOTTED FLAP, Joseph L. Johnson, Jr., April 1959 M_MO 3-12-59L THEEFFECT OF LIFT-DRAG RATIOANDSPEED ONTHEABILITY TO POSITION A GLIDINGAIRCRAFT FORA LANDING ONA 5,000-FOOT RUNWAY, John P. Reeder, April 1959 MEMO 3-17-59E ANALYSIS ANDEVALUATION OF SUPERSONIC UNDERWING HEAT ADDITION, Roger W. Luidens and Richard J. Flaherty. APPENDIX C: DERIVA- TIONOF EFFECT OF SUPERSONIC UNDERWING HEATADDITION FROM POTENTIAL- FLOW EQUATIONS, Stephen H. Maslen, April 1959 MEMO 3-17-59L THEFLUORESCENT-OIL FILM METHOD ANDOTHER TECHNIQUES FOR BOUNDARY-LAYER FLOW VISUALIZATION, Donald L. Loving and S.

Katzoff, March 1959 MEMO 3-17-59W SPACE-TIME CORRELATIONS ANDSPECTRA OF WALL PRESSURE IN A TURBULENT BOUNDARY LAYER,W. W. Willmarth, March 1959 MEMO 4-3-59L FORMULAS PERTINENT TO THECALCULATION OF FLOW-FIELD EFFECTS AT SUPERSONIC SPEEDS DUETOWING THICKNESS, Kenneth Margolis and Miriam H. Elliott, May 1959 MEMO 4-9-59L SOME BASICASPECTS OFMAGNETOHYDRODYNAMIC BOUNDARY-LAYER FLOWS, Robert V. Hess, April 1959 MEMO 4-9-59W SPECTRAL EMITTANCE OF UNCOATED ANDCERAMIC-COATED INCONEL ANDTYPE321 STAINLESS STEEL,Joseph C. Richmondand James E. Stewart, April 1959 MEMO 4-13-59L WIND-TUNNEL INVESTIGATION AT MACH NUMBERS FROM 0.40 TO 1.14 OFTHESTATIC AERODYNAMIC CHARACTERISTICS OF A NONLIFTING VEHICLE SUITABLE FORREENTRY, Albin O. Pearson, May 1959 MEMO 4-13-59W INTERACTIONS BETWEEN GROUND-STATE NITROGEN ATOMS ANDMOLECULES, Joseph T. Vanderslice, EdwardA. Mason, and Ellis R. Lippincott, April 1959 M]_MO 4-14-59E PRELIMINARY DEVELOPMENT OF ELECTRODES FORAN ELECTRIC-ARC WIND TUNNEL, Charles E. Shepard and Donald R. Boldman, March 1959 MEMO 4-15-59L CHARTS OF THEINDUCED VELOCITIES NEAR A LIFTINGROTOR, Joseph W. Jewel, Jr. and Harry H. Heyson, May 1959 MEMO 4-17-59L AIRPLANE MEASUREMENTS OFATMOSPHERIC TURBULENCE AT ALTITUDES BETWEEN 20,000 AND55,000 FEETFORFOUR GEOGRAPHIC AREAS, ThomasL. Colemanand May T. Meadows,June 1959 MEMO 4-18-59A PREDICTED STATICAEROELASTIC EFFECTS ONWINGS WITHSUPERSONIC LEADING EDGES ANDSTREAMWISE TIPS, Stuart C. Brown, April 1959 MEMO 4-19-59A SUPERSONIC ANDMOMENT-OF-AREA RULES COMBINED FORRAPIDZERO- LIFT WAVE-DRAG CALCULATIONS, Lionel L. Levy, Jr., June 1959 MEMO 4-20-59L TRANSONIC AERODYNAMIC CHARACTERISTICS OFA 45 ° SWEPT-WING- FUSELAGE MODEL WITH A FINNED AND UNFINNED BODY PYLON-MOUNTED BENEATH THE FUSELAGE OR WING, INCLUDING MEASUREMENTS OF BODY LOADS, Dewey E. Wornom, May 1959 MEMO 4-21-59L INVESTIGATION OF THE CHARACTERISTICS OF AN ACCELERATION-TYPE TAKE-OFF INDICATOR IN A LARGE JET AIRPLANE, Joseph J. Kolnick and Emmanuel Rind, May 1959 MEMO 4-22-59E PRELIMINARY ANALYSIS OF THEEFFECT OF FLOW SEPARATION DUETO ROCKET JET PLUMING ONAIRCRAFT DYNAMIC STABILITYDURING AT- MOSPHERIC EXIT, Murray Dryer and Warren J. North, June 1959 MEMO 4-22-59W HEATTRANSFER FROM A HORIZONTAL CYLINDER ROTATING IN OIL, R. A. Seban and H. A. Johnson, April 1959 MEMO 4-27-59A LIFT-DRAG RATIOS FORAN ARROW WING WITHBODIES AT MACH NUMBER 3, Leland H. Jorgensen, May 1959 MEMO 4-27-59E HEAT TRANSFER FROM CYLINDERS IN TRANSITION FROM SLIP FLOW TO FREE-MOLECULE FLOW, Ronald J. Cybulski and Lionel V. Baldwin, May 1959 MEMO 5-5-59W EFFECT OF CONTRACTION ONTURBULENCE ANDTEMPERATURE FLUCTUA- TIONSGENERATED BYA WARM GRID, Robert R. Mills, Jr., and Stanley Corrsin, May 1959 MEMO 5-8-59L FLUID-DYNAMIC PROPERTIES OF SOME SIMPLESHARP- ANDBLUNT- NOSED SHAPES AT MACH NUMBERS FROM 16 TO 24 IN HELIUM FLOW, Arthur Henderson, Jr. and Patrick J. Johnston, June 1959 MEMO 5-9-59L HYDRODYNAMIC CHARACTERISTICS OF TWO LOW-DRAG SUPERCAVITATING HYDROFOILS, John R. McGehee and Virgil E. Johnson, Jr., June MEMO 5-I0-59L REVIEW OFAIRCRAFT ALTITUDE ERRORS DUETO STATIC-PRESSURE SOURCE ANDDESCRIPTION OFNOSE-BOOM INSTALLATIONS FORAERO- DYNAMIC COMPENSATION OF ERROR, William Gracey and Virgil S.

Ritchie, June 1959 MEMO 5-12-59L BASICPRESSURE MEASUREMENTS AT TRANSONIC SPEEDS ONA THIN 45° SWEPTBACK HIGHLY TAPERED WING WITHSYSTEMATIC SPANWISE TWIST VARIATIONS. WING WITHCUBICSPANWISE TWISTVARIATION,John P.

Mugler, Jr., June 1959 MEMO 5-13-59L MEASUREMENTS OF TOTAL HEMISPHERICAL EMISSIVITYOF SEVERAL STABLY OXIDIZED NICKEL-TITANIUM CARBIDE CEMENTED HARD METALS FROM 600°F TO 1,600°F, William R. Wadeand F. W. Casey, Jr., June 1959 MEMO 5-18-59A THEEFFECTS OF STREAMWISE-DEFLECTED WINGTIPS ONTHEAERODYNAMIC CHARACTERISTICS OFAN ASPECT-RATIO-2 TRIANGULAR WING,BODY,AND TAIL COMBINATION, Victor L. Peterson, May 1959 MEMO _-19-59E HUMAN TOLERANCE TORAPIDLY APPLIED ACCELERATIONS: _ SUMMARY OF THELITERATURE, A. Martin Eiband, June 1959 MEMO 5-20-59A AN EXPERIMENTAL INVESTIGATION OF THEEFFECT OF A CANARD CONTROL ONTHELIFT, DRAG,ANDPITCHING MOMENT OFAN ASPECT-RATIO-2.0 TRIANGULAR WING INCORPORATING A FORM OF CONICAL CAMBER, GeneP.

Meneesand John W. Boyd, May 1959 MEMO 5-23-59L WATER-LANDING CHARACTERISTICS OF A REENTRY CAPSULE, John R.

McGehee,Melvin E. Hathaway, and Victor L. Vaughan, Jr., June 1959 MEMO 5-24-59L A SIMPLE METHOD FORDETERMINING HEATTRANSFER, SKINFRICTION, ANDBOUNDARY-LAYER THICKNESS FORHYPERSONIC LAMINAR BOUNDARY- LAYER FLOWS IN A PRESSURE GRADIENT, Mitchel H. Bertram and William V. Feller, June 1959 MEMO 5-25-59W 1958 NASA/USAF SPACE PROBES (ABLE-I) FINAL REPORT.VOL. I - SUMMARY; VOL. 2 - PAYLOAD ANDEXPERIMENTS; VOL. 3 - VEHICLES, TRAJECTORIES, ANDFLIGHTHISTORIES; VOL. 4 - CHARACTERISTICS OF THEABLE- i ENGINES, SpaceTechnology Laboratories, Inc., June 1959 MEMO 6-4-59L DISTRIBUTION OF HEATTRANSFER ONA i0 ° CONE AT ANGLES OF ATTACK FROM 0 ° TO 15 ° FOR MACH NUMBERS OF 2.49 TO 4.65 AND A SOLUTION TO THE HEAT-TRANSFER EQUATION THAT PERMITS COMPLETE MACHINE CALCULATIONS, Paige B. Burbank and B. Leon Hodge, June 1959 MEMO 6-4-59 AERODYNAMIC HEATING AND FATIGUE, Wilhelmina D. Kroll, June 1959 MEMO 6-8-59L AERODYNAMIC CHARACTERISTICS OF X-15/B-52 COMBINATION, William J. Alford Jr. and Robert T. Taylor, June 1959 MEMO 6-9-59A TRANSONIC AERODYNAMIC CHARACTERISTICS OF A LATERAL CONTROL EMPLOYING ROTATABLE AIRFOILS MOUNTED VERTICALLY AT THE WING TIPS OF A 45 ° SWEPTBACK WING, FUSELAGE, AND TAlL COMBINATION, John A. Axelson, June 1959 MEMO 6-I0-59L EXPERIMENTAL INVESTIGATION OF THE HEAT-TRANSFER RATE TO A SERIES OF 20 ° CONES OF VARIOUS SURFACE FINISHES AT A MACH NUMBER OF 4.95, Jim J. Jones, June 1959 MEMO 6-29-59L THREE-DIMENSIONAL LUNAR MISSION STUDIES, William H. Michael, Jr., and Robert H. Tolson, June 1959 ME_MO 7-9-59A EXTENDING THE LORENTZ TRANSFORMATION TO MOTION WITH VARIABLE VELOCITY, Robert T. Jones, June 1959 Applicable NASA Technics] Notes ANALYSIS OF COMPUTED FLOW PARAMETER FOR A SET OF SUDDEN STALLS IN TN D 85 LOW-SPEED TWO-DIMENSIONAL FLOW, William T. Evans and Kenneth W.

Mort, August 1959 This report presented an analysis from which it was inferred that there were two distinct mechanisms of nose stall in low-speed two-dimensional flow. These were presumed to be the two mecha- nisms already described in other literature as "bubble-bursting" and "reseparation". A basis for distinguishing between the two mechanisms was provided by a criterion for transitional reattach- ment of separated laminar boundary layer, proposed independently by Tani, and by Owen and Klanfer, and was indicated in this re- port to be essentially valid. This report considered a set of sudden airfoil stalls obtained under fixed test conditions.

Theoretical velocity distributions about the leading edges just prior to stall were computed. For those stalls ascribed to the reseparation mechanism, a correlation was demostrated between high velocity peaks and either steep initial adverse gradients or thin boundary layers in the region of these gradients.

It was found that: Both mechanisms of stall mentioned appeared in testing.

The Tani-Owen criterion for transitional reattachment of a separated laminar boundary layer appeared to be essentially valid, and afforded a means for distinguishing between the two mechanisms of nose stall.

For nose stalls by the reseparation mechanism, under a given set of test conditions, a correlation can be expected between high velocity peaks at stall and either steep initial adverse gradients or thin boundary layers in the region of these gradients.

THE BOUNDARY-LAYER TRANSITION CHARACTERISTICS OF TWO BODIES OF TN D 309 REVOLUTION, A FLAT PLATE, AND AN UNSWEPT WING IN A LOW-TURBULENCE WIND TUNNEL, Frederick W. Boltz, George C. Kenyon, and Clyde Q.

Allen, April 1960 An investigation was conducted to determine the boundary-layer transition characteristics of two bodies of revolution, a flat plate, and an unswept wing. The bodies of revolution had fine- ness ratios of 9.0 and 7.5 and were tested at Mach numbers from about 0.i to 0.98. The wing had an NACA 642-A015 section and, along with the flat plate, was tested at Mach numbers below about 0.5. The beginning of transition in the boundary layer was de- tected with hot-wire probes and/or microphones coupled to static- pressure orifices. As a necessary part of the transition investigation, a survey of the tunnel turbulence and sound levels was also undertaken using a hot-wire anemometerand a condenser microphone.

In all cases it was found that the pressure distribution on the model was a primary factor in determining the level of transition Reynolds number. Small increases in the favorable pressure grad- ients over the forward portion of the models resulted in signifi- cant increases in the transition Reynolds number.

Measurementsof the tunnel turbulence and sound pressure levels with a hot-wire microphone and a condenser microphone indicate that sound comprises practically the entire "turbulence" field at all Machnumbers.

In general, it was found that increasing tunnel airspeed had an adverse effect on the transition Reynolds numbers for all of the models in the low subsonic speed range. It is believed that the effect was a result of changes in the frequency and/or intensity of the sound waves present in the flow field.

TN D 339 EXPERIMENTAL ANDTHEORETICAL STUDY OF A RECTANGULAR WINGIN A VORTICAL WAKE AT LOW SPEED, Willard G. Smith and Frank A.

Lazzeroni, October 1960 A systematic study was made, experimentally and theoretically, of the effects of a vortical wake on the aerodynamic characteristics of a rectangular wing at subsonic speed. The vortex generator and wing were mounted on a reflection plane to avoid body-wing inter- ference. Vortex position, relative to the wing, was varied both in the spanwise direction and normal to the wing. Angle of attack of the wing was varied from -4 ° to +6°. Both chordwise and span- wise pressure distributions were obtained with the wing in uniform and vortical flow fields. Stream surveys were madeto determine the flow characteristics in the vortical wake. The vortex-lnduced lift was calculated by several theoretical methods including strip theory, reverse-flow theory, and reverse-flow theory including a finite vortex core. In addition, the Prandtl lifting-line theory and the Weissinger theory were used to calculate the spanwise distribution of vortex-induced loads.

Stream-survey results showedthat the wake of lifting surfaces of rectangular plan form starts to roll up quickly forming a vortex which trails back in a nearly streamwise direction from the wing tip rather than from the centroid of circulation predicted by the lifting-line theory. This result was believed to be restricted to essentially untapered plan forms.

Results of the investigation indicated that the vortex interference lift could be predicted over the range of test variables hy the reverse-flow theory if a vortical wakewith a finite-core diameter were considered.

The experimental induced loads on the wing at zero angle of attack when the vortex was not in the wing-chord plane were different for a positive and negative direction of circulation because of the asymmetry of the vortex sheet which was not fully rolled up. When the wing was at an angle of attack the direction of circulation, regardless of extent of roll-up, also affected the magnitude of the induced loads.

The spanwise distribution of vortex-induced loads was predicted by lifting-line theory with reasonable accuracy using either the mea- sured downwash angles or the values calculated for a potential vortex trailing back from the tip of the vortex generators.

Not Applicable NASA Technical Notes TND LAMINAR SKIN-FRICTION AND HEAT-TRANSFER PARAMETERS FOR A FLAT PLATE AT HYPERSONIC SPEEDS IN TERMS OF FREE-STREAM FLOW PROPERTIES, James F. Schmidt, September 1959 TN D EXPERIMENTAL INVESTIGATION OF AIR FILM COOLING APPLIED TO AN ADIABATIC WALL BY MEANS OF AN AXIALLY DISCHARGING SLOT, S. Stephen Papell and Arthur M. Trout, August 1959 TND i0 ON SERIES EXPANSIONS IN MAGNETIC REYNOLDS NUMBER, Vernon J. Rossow, August 1959 TND ii MEASURED AND PREDICTED SECTION WAVE DRAG COEFFICIENTS AT A MACH NUMBER OF 1.6 FOR A DELTA WING WITH TWO AIRFOIL SECTIONS, Frederick C. Grant, September 1959 TN D 12 SOLUTIONS OF THE LAMINAR COMPRESSIBLE BOUNDARY-LAYER EQUATIONS WITH TRANSPIRATION WHICH ARE APPLICABLE TO THE STAGNATION REGIONS OF AXISYMMETRIC BLUNT BODIES, John T. Howe and William A. Mersman, August 1959 TN D 13 EFFECTIVENESS OF AN ALL-MOVABLE HORIZONTAL TAIL ON AN UNSWEPT- WING AND BODY COMBINATION FOR MACH NUMBERS FROM 0.60 TO 1.40, Louis S. Stivers, Jr., August 1959 TN D 14 TRANSONIC AERODYNAMIC CHARACTERISTICS OF SEVERAL BODIES HAVING ELLIPTICAL CROSS SECTIONS AND VARIOUS PLAN FORMS, Robert A.

Taylor, August 1959 TN D 16 LOW-SPEED WIND-TUNNEL INVESTIGATION OF BLOWING BOUNDARY-LAYER CONTROL ON LEADING-AND TRAILING-EDGE FLAPS OF A FULL-SCALE, LOW- ASPECT-RATIO, 42 ° SWEPT-WING AIRPLANE CONFIGURATION, Ralph L.

Maki and Demo J. Giulianetti, August 1959 TN D 17 WIND-TUNNEL INVESTIGATION OF EFFECT OF RATIO OF WING CHORD TO TO PROPELLER DIAMETER WITH ADDITION OF SLATS ON THE AERODYNAMIC CHARACTERISTICS OF TILT-WING VTOL CONFIGURATIONS IN THE TRANSI- TION SPEED RANGE, Robert T. Taylor, September 1959 TN D 18 TWO TECHNIQUES FOR DETECTING BOUNDARY-LAYER TRANSITION IN FLIGHT AT SUPERSONIC SPEEDS AND AT ALTITUDES ABOVE 20,000 FEET, John G.

McTigue, John D. Overton, and Gilbert Petty, Jr., August 1959 TN D CONSIDERATION OF SOME AERODYNAMIC CHARACTERISTICS DURING TAKE- OFF AND LANDING OF JET AIRPLANES, John M. Riebe, September 1959 TN D 24 CALCULATION OF SUPERSONIC FLOW PAST BODIES SUPPORTING SHOCK WAVES SHAPED LIKE ELLIPTIC CONES, Benjamin R. Briggs, August 1959 LARGE-SCALE WIND-TUNNEL TESTS OF AN AIRPLANE MODEL WITHAN TN D 25 UNSWEPT, ASPECT-RATIO-IO WING,FOUR PROPELLERS, ANDBLOWING FLAPS,JamesA. Weiberg and V. Robert Page, September 1959 FLIGHTINVESTIGATION OF THELIFT ANDDRAG CHARACTERISTICS TND 30 OF A SWEPT-WING, MULTIJET,TRANSPORT-TYPE AIRPLANE, Ronald Tambor, November" 1959 FREE FALL ANDEVAPORATION OF JP-4 JET FUELDROPLETS IN A TND 33 QUIETATMOSPHERE, HermanH. Lowell, September 1959 TN D 37 EFFECTS OF BODY ANDFIN DEFLECTIONS ONTHEAERODYNAMIC CHARACTERISTICS IN PITCHOFA 0.065-SCALEMODEL OF A FOUR- STAGE ROCKET CONFIGURATION AT MACH NUMBERS OF 1.41 AND1.82, Ross B. Robinson, September1959 AN APPROXIMATE ANALYSIS OF UNSTEADY VAPORIZATION NEAR THE TND 41 STAGNATION POINTOF BLUNT BODIES,Leonard Roberts, September AN EVALUATION OF LINEARIZED VORTEX THEORY AS APPLIED TO SINGLE TND 43 ANDMULTIPLE ROTORS HOVERING IN ANDOUTOFGROUND EFFECT,Harry H. Heyson, September1959 TN D 46 PLASMA ACCELERATION BY USEOFGUIDED MICROWAVES, Robert V. Hess and Karlheinz Thom, December1959 SOME ASPECTS OFAIR-HELIUMSIMULATION ANDHYPERSONIC APPROXI- TN D 49 MATIONS, EugeneS. Love, Arthur Henderson, Jr., and Mitchel H.

Bertram, October 1959 WIND-TUNNEL INVESTIGATION OF THEAERODYNAMIC CHARACTERISTICS TN D 50 OF A MODEL REPRESENTATIVE OF A SUPERSONIC FIGHTER-CLASS AIR- PLANE WITHAN EXTERNAL-FLOW JET-AUGMENTED FLAPIN LOW-SPEED FLIGHT,William A. Newsom,Jr., September1959 THEHYDRODYNAMIC CHARACTERISTICS OF A SUBMERGED LIFTING SURFACE TN D 51 HAVING A SHAPE SUITABLE FORHYDRO-SKI APPLICATION, Victor L.

Vaughan, Jr., October 1959 EFFECT OFDISTRIBUTED THREE-DIMENSIONAL ROUGHNESS ANDSURFACE TND 53 COOLING ONBOUNDARY-LAYER TRANSITION ANDLATERAL SPREAD OF TURBULENCE AT SUPERSONIC SPEEDS, A!hert L. Braslow, EugeneC.

Knox, and Elmer A. Horton, October i_59 LOW-SPEED WIND-TUNNEL INVESTIGATION OF A WINGLESS JET VTOL TN D 57 TRANSPORT MODEL, M. OoMcKinney, Jr., October 1959 COMPARISON OF CALCULATED ANDMEASURED STALLBOUNDARIES OF A TND 73 HELICOPTER ROTOR AT ADVANCE RATIOS FROM 0.3 to 0.4, John L.

McCloud III and GeorgeB. McCullough, September1959 TND 77 UNSTEADY STAGNATION-POINT HEATTRANSFER, E(phraim) M. Sparrow, October 1959 TN D DEPARTURE TRAJECTORIES FORINTERPLANETARY VEHICLES, W. E.

Moeckel, November1959 TND 81 METHODS ANDVELOCITY REQUIREMENTS FORTHERENDEZVOUS OF SATELLITES IN CIRCUM-PLANETARY ORBITS,William E. Brunk and Richard J. Flaherty, October 1959 TN D MIXINGOFWAKES IN A TURBULENT SHEAR FLOW,SalamonEskinazi, September 1959 TN D 86 METHODS OF CALCULATING FUNDAMENTAL SOLUTIONS OF THEWAVE EQUATION, WITHTABLES,William A. Mersman, October 1959 TN D 87 EFFECTS OFCHEMICAL DISSOCIATION ANDMOELCULAR VIBRATIONS ON STEADY ONE-DIMENSIONAL FLOW,Steve P. Helms, August 1959 TN D WIND-TUNNEL TESTS OFA SEMISPAN WING WITHA FANROTATING IN THEPLANE OF THEWING,David H. Hickey and David R. Ellis, October 1959 TN D 92 MEASURED ANDTHEORETICAL FLOW FIELDSBEHIND A RECTANGULAR AND A TRIANGULAR WING UP TO HIGHANGLES OFATTACK AT A MACH NUMBER OF 2.46, Frank J. Centolanzi, September 1959 TN D 93 APPLICATION TO FLUIDDYNAMICS OFTHETHEORY OF REVERSIBLE HEAT ADDITION,Barrett, S. Baldwin, Jr., October 1959 TN D 95 THEORETICAL ANALYSIS OF THECREEP COLLAPSE OF COLUMNS, Floyd R.

Schlechte, September 1959 TN D 96 A METHOD FORCALCULATING AERODYNAMIC LOADINGS ONTHINWINGS AT A MACH NUMBER OF l,John L. Crigler, November1959 TN D 97 A NOTE ONTHECALCULATION OF HELICOPTER PERFORMANCE AT HIGHTIP- SPEED RATIOS,Alfred Gessow, September 1959 TN D 99 PRINCIPLES OF DESIGN OF DYNAMICALLY SIMILARMODELS FORLARGE PROPELLANT TANKS,Paul E. Sandorff, January 1960 TN D 103 INVESTIGATION OF DOUBLE SLOTTED FLAPSONA SWEPT-WING TRANSPORT MODEL, Rodger L. Naeseth and Edwin E. Davenport, October 1959 TN D 112 EXPERIMENTAL INVESTIGATION OF THEPRESSURE FLUCTUATIONS ONA FLATPLATEANDA CYLINDER IN THESLIPSTREAM OFA HOVERING ROTOR, John W. McKee, September1959 TN D 118 INVESTIGATION OF THEFLOW OVER A SPIKED-NOSE HEMISPHERE-CYLINDER AT A MACH NUMBER OF 6.8, Davis H. Crawford, December1959 TN D 119 INVESTIGATION OF A HIGH-SPEED HYDROFOIL WITHPARABOLIC THICKNESS DISTRIBUTION, Virgil E. Johnson, Jr. and ThomasA. Rasnick, November1959 TN D 120 IMPORTANCE OF THEVARIATION OFDRAG WITHLIFT IN MINIMIZATION OF SATELLITE ENTRY ACCELERATION, Frederick C. Grant, October 1959 TN D 122 WIND-TUNNEL CALIBRATIONS OFA COMBINED PITOT-STATIC TUBE,VANE- TYPEFLOW-DIRECTION TRANSMITTER, ANDSTAGNATION-TEMPERATURE ELEMENT AT MACH _BERS FROM 0.60 to 2.87, NormanR. Richardson and Albin O. Pearson, October 1959 TN D 124 STATICTESTS OFAN EXTERNAL-FLOW JET-AUGMENTED FLAPTESTBEDWITH TURBOJET ENGINE,Marvin P. Fink, December1959 TN D 127 EXPERIMENTAL INVESTIGATION OFMETAL TEMPERATURES OFAIR-COOLED AIRFOIL LEADING EDGES AT SUBSONIC FLOW ANDGASTEMPERATURES UP TO 2780°F., Francis S. Stepka and Hadley To Richards, November TN D 133 MEASUREMENTS OFHEATTRANSFER ANDFRICTION COEFFICIENTS FOR HELIUM FLOWING IN A TUBEAT SURFACE TEMPERATURES UP TO 5900°R, Maynard F. Taylor and ThomasA. Kirchgessner, October 1959 TN D 135 FULL-SCALE WIND-TUNNEL TESTS OFA LOW-ASPECT-RATIO, STRAIGHT- WING AIRPLANE WITHBLOWING BOUNDARY-LAYER CONTROL ONLEADING- ANDTRAILING-EDGE FLAPS,Mark W. Kelly, William H. Tolhurst, Jr., and Ralph L. Maki, September 1959 TN D 140 DISSOCIATIVE RELAXATION OF OXYGEN OVER AN ADIABATIC FLATPLATE AT HYPERSONIC MACH NUMBERS, Paul M. Chungand AemerD. Anderson, April 1960 TND 141 EFFECT OF LOCALIZED MASS TRANSFER NEAR THESTAGNATION REGION OF BLUNT BODIES IN HYPERSONIC FLIGHT, Paul M. Chung, May 1960 TND 144 DETERMINATION OF NONLINEAR PITCHING-MOMENT CHARACTERISTICS OF AXIALLYSYMMETRIC MODELS FROM FREE-FLIGHT DATA,Maurice L.

Rasmussen,February 1960 TN D 157 EXPERIMENTAL PRESSURE DISTRIBUTIONS OVER BLUNT TWO-ANDTHREE- DIMENSIONAL BODIES HAVING SIMILARCROSS SECTIONS AT A MACH NUM- BEROF 4.95, Jerome D. Julius, September 1959 TN D 159 HEAT-TRANSFER MEASUREMENTS AT A MACH NUMBER OF 2 IN THETURBULENT BOUNDARY LAYER ONA FLATPLATE HAVING A STEPWISE TEMPERATURE DISTRIBUTION, Raul J. Conti, November1959 TND 164 A RADAR TESTTARGET SYSTEM, JamesT. Rose and R. Donald Smith, January 1960 TND 166 A HYDRODYNAMIC INVESTIGATION OF THEEFFECT OFADDING UPPER- SURFACE CAMBER TO A SUBMERGED FLATPLATE, Victor L. Vaughan, Jr., November1959 TND 167 INVESTIGATION OFVARIATION IN BASE PRESSURE OVER THEREYNOLDS NUMBER RANGE IN WHICH WAKE TRANSITION OCCURS FORTWO-DIMENSIONAL BODIES AT MACH NUMBERS FROM 1.95 to 2.92, Vernon Van Hise, November1959 TN D 170 LIFT ANDDRAG CHARACTERISTICS AT SUBSONIC SPEEDS ANDAT A MACH NUMBER OF 1.9 OFA LIFTING CIRCULAR CYLINDER WITHA FINENESS RATIOOF i0, Vernard E. Lockwoodand Linwood W. McKinney, December1959 TN D 174 REFLECTION CHARACTERISTICS OF ARTIFICIAL SATELLITES CONSTRUCTED IN THEFORM OF INFLATED POLYHEDRONS, Archibald R. Sinclair, December1959 TN D 179 MEASUREMENTS OF PRESSURE ANDLOCAL HEATTRANSFER ONA 20° CONE AT ANGLES OF ATTACK UP TO 20° FORA MACH NUMBER OF 4.95, Jerome D. Julius, December1959 TN D 183 EFFECTS OFA LOWER SURFACE JET ONTHELIFT-DRAG RATIOOFA 45° SWEPTBACK WING AT A MACH NUMBER OF 2.01, Emn_a Jean Landrum, March 1960 TND 184 AN EXPERIMENTAL INVESTIGATION AT A MACH NUMBER OF 4.95 OF FLOW IN THEVICINITY OFA 90° INTERIOR CORNER ALINEDWITHTHEFREE- STREAM VELOCITY,P. Calvin Stainback, February 1960 TND 187 EXPERIMENTAL INVESTIGATION OFASPECT-RATIO-I SUPERCAVITATING HYDROFOILS AT SPEEDS UP TO 185 FEETPERSECOND, Kenneth W.

Christopher and Virgil E. Johnson, Jr._ January 1960 TND 194 CORRELATION FORMULAS ANDTABLES OFDENSITY ANDSOME TRANSPORT PROPERTIES OF EQUILIBRIUM DISSOCIATING AIR FORUSEIN SOLUTIONS OF THEBOUNDARY-LAYER EQUATIONS, Nathaniel B. Cohen, February TND 195 EVOLUTION OFAMPLIFIED WAVES LEADING TO TRANSITION IN A BOUNDARY LAYER WITHZERO PRESSURE GRADIENT, P. S. Klebanoff and K. D.

Tidstrom, September 1959 TN D 196 ANALYSIS OF TEMPERATURE DISTRIBUTION ANDRADIANT HEAT TRANSFER ALONG A RECTANGULAR FIN OF CONSTANT THICKNESS, SeymourLieblein, November1959 TN D 201 METHODS OF PREDICTING LAMINAR HEAT RATES ONHYPERSONIC VEHICLES, Richard J. Wisniews, December1959 TN D 205 FREE-FLIGHT INVESTIGATION AT MACH NUMBERS BETWEEN 0.5 AND1.7 OF THEZERO-LIFT ROLLING EFFECTIVENESS ANDDRAG OF VARIOUS SURFACE, SPOILER,ANDJET CONTROLS ONAN 80° DELTA-WING MISSILE, EugeneD. Schult, February 1960 TN D 209 THEROLLING MOMENT DUETO SIDESLIPOF SWEPT WINGS AT SUBSONIC ANDTRANSONIC SPEEDS, Edward C. Polhamusand William C. Sleeman, Jr., February 1960 TN D 216 AERODYNAMIC-HEATING DATAOBTAINED FROM FREE-FLIGHT TESTS BETWEEN MACH NUMBERS OF 1 AND5, Charles B. Rumsey,Robert O. Piland, and Russell N. Hopko, January 1960 TN D 220 A BRIEFINVESTIGATION OF A HYDRO-SKI STABILIZED HYDROFOIL SYSTEM ONA MODEL OFA TWIN-ENGINE AMPHIBIAN, SandyM. Stubbs and Edward L. Hoffman, February 1960 TND 223 EFFECTS OF NOSE CORNER RADII, AFTERBODY SECTION DEFLECTIONS, AND A DROGUE CHUTE ONSUBSONIC MOTIONS OF'MANNED-SATELLITE MODELS IN REENTRY CONFIGURATIONS, Willard S. B]anchard, Jr_ and Sherwood Hoffman, March 1960 TND 224 A TECHNIQUE FORFIRING DYNAMICALLY SCALED MISSILEMODELS IN WIND TUNNELS ANDFORMEASURING ROCKET-MOTOR SOUND ANDPRESSURE FLUCTUA- TIONS, William J. Alford, Jr. and Kenneth W. Goodson,March 1960 TND 225 SUBSONIC WIND-TUNNEL INVESTIGATION OF THEAERODYNAMIC EFFECTS OF PIVOTING A LOW-ASPECT-RATIO WING TO LARGE YAW ANGLES WITHRESPECT TOTHEFUSELAGE TO INCREASE LIFT-DRAG RATIO, ThomasG. Gainer, March 1960 TN D 226 EXPERIMENTAL INVESTIGATION AT A MACH NUMBER OF 3.11 OF THELIFT, DRAG, ANDPITCHING-MOMENT CHARACTERISTICS OF FIVE BLUNT LIFTING BODIES,William Letko, April 1960 TN D 230 THEVARIATION ANDCONTROL OF RANGE TRAVELED IN THEATMOSPHERE BY A HIGH-DRAG VARIABLE-LIFT ENTRY VEHICLE,Donald C. Cheatham, John W. Young, and John M. Eggleston, March 1960 TND 234 GROUND EFFECT FORLIFTING ROTORS IN FORWARD FLIGHT, Harry H.

Heyson, May 1960 GROUND MEASUREMENTS OF AIRPLANE SHOCK-WAVE NOISEAT MACH NUMBERS TND 235 TO 2.0 ANDAT ALTITUDES TO 60,000 FEET, Lindsay J. Lina and DomenicJ. Maglieri, March 1960 TN D 236 PRESSURE DISTRIBUTIONS ANDAERODYNAMIC CHARACTERISTICS OF SEVERAL SPOILER CONTROLS ONA 40° SWEPTBACK WING AT A MACH NUMBER OF 1.61, Emma Jean Landrumand K. R. Czarnecki, April 1960 TN D 237 EFFECT OF A VARIABLE-GEOMETRY DIFFUSER ONTHEOPERATING CHARAC- TERISTICS OFA HELIUM TUNNEL DESIGNED FORA MACH NUMBER IN EXCESS OF 20, Patrick J. Johnston and Robert D. Witcofski, February 1960 TN D 240 A NOTE ONTHEMEAN VALUE OF INDUCED VELOCITY FORA HELICOPTER ROTOR, Harry H. Heyson, May 1960 TN D 241 A FLIGHTINVESTIGATION OF AN ACCELERATION RESTRICTOR, Arthur Assadourian and Donald L. Mallick, April 1960 TN D 242 INVESTIGATION BY SCHLIEREN TECHNIQUE OFMETHODS OF FIXING FULLYTURBULENT FLOW ONMODELS AT SUPERSONIC SPEEDS, Mary W.

Jackson and K. R. Czarnecki, April 1960 TN D 243 TABLES ANDCHARTS FORESTIMATING STALLEFFECTS ONLIFTING-ROTOR CHARACTERISTICS, Alfred Gessowand Robert J. Tapscott, May 1960 TND 244 LIFT GENERATION ONA CIRCULAR CYLINDER BYTANGENTIAL BLOWING FROM SURFACE SLOTS, Vernard E. Lockwood, May 1960 TND 247 EXPERIMENTAL INVESTIGATION OFMIXINGOF MACH NUMBER 3.95 STREAM IN PRESENCE OFWALL,Marian Visich, Jr., and Paul A. Libby, February 1960 TN D 249 ANALYSIS OFLOW-ACCELERATION LIFTING ENTRY FROM ESCAPE SPEED, Frederick C. Grant, June 1960 TN D 250 MEASUREMENT OF AERODYNAMIC HEATTRANSFER TO A DEFLECTED TRAILING- EDGE FLAPONA DELTA FIN IN FREEFLIGHTAT MACH NUMBERS FROM 1.5 TO 2.6, Leo T. Chauvin and JamesJ. Buglia, June 1960 TN D 278 FREE-FLIGHT OBSERVATION OF A SEPARATED TURBULENT FLOW INCLUDING HEATTRANSFER UP TO MACH 8.5, Dudley GeorgeMcConnell, October TN D 279 OPERATIONAL METHOD OF DETERMINING INITIAL CONTOUR OF ANDPRESSURE FIELD ABOUT A SUPER SONIC JET, Gerald W. Engler, April 1960 TND 280 FLIGHTMEASUREMENT OF WALL-PRESSURE FLUCTUATIONS ANDBOUNDARY- LAYER TURBULENCE, Harold R. Mull and Joseph S. Algranti, October TND 291 LAMINAR BOUNDARY LAYER BEHIND A STRONG SHOCK MOVING INTOAIR, Harold Mirels, February 1961 TND 292 AN INTEGRAL METHOD FORNATURAL-CONVECTION FLOWS AT HIGHAND LOW PRANDTL NUMBERS, Willis H. Braun and John Eo Heighway, June 1960 TND 306 A SIMPLIFIEDSTUDY ONTHENONEQUILIBRIUM COUETTE ANDBOUNDARY- LAYER FLOWS WITHAIR INJECTIONS, Paul M. ChunE, February 1960 TND 310 TESTS OF ANAREASUCTION FLAPONAN NACA64A010AIRFOILAT HIGH SUBSONIC SPEEDS, Donald W. Smith and John Walker, May 1960 TN D 312 EFFECTS OF FIXING BOUNDARY-LAYER TRANSITION FORA SWEPT- ANDA TRIANGULAR-WING ANDBODY COMBINATION AT MACH NUMBERS FROM 0.60 TO 1.40, Louis S. Stivers, Jr., June 1960 TN D 313 EFFECT OF LEADING-EDGE THICKNESS ONTHEFLOW OVER A FLATPLATE AT A MACH NUMBER OF 5.7, Marcus O. Creager, May 1960 TND 316 STUDY OF THEAERODYNAMIC FORCES ANDMOMENTS ONBODIES OF REVOLUTION IN COMBINED PITCHING ANDYAWING MOTIONS, Murray Tobak and Henry C. Lessing, May 1960 TND 317 WIND-TUNNEL TESTS OF A CIRCULAR WING WITHAN ANNULAR NOZZLE IN PROXIMITY TOTHEGROUND, Richard K. Greif, Mark W. Kelly and William H. Tolhurst, Jr., May 1960 TND 319 ANAPPROXIMATE ANALYTICAL METHOD FORSTUDYING ATMOSPHERE ENTRY OF VEHICLES WITHMODULATED AERODYNAMIC FORCES, Lionel L. Levy, Jr., October 1960 TND 320 AN EXPERIMENTAL INVESTIGATION OF BOUNDARY-LAYER CONTROL FOR DRAG REDUCTION OFA SWEPT-WING SECTION AT LOWSPEED ANDHIGH REYNOLDS NUMBERS, Donald E. Gault, October 1960 FLIGHTINVESTIGATION OF THELOW SPEED CHARACTERISTICq OF A 45° TND 321 SWEPT-WING FIGHTER-TYPE AIRPLANE WITHBLOWTNG BOUNDARY-LAYER CONTROL APPLIED TO THELEADING-AND TRAILING-EDGE FLAPS,Hervey C. Quigley, Seth B. _+tderson, and Robert C. Innis, September TN D 326 LARGE-SCALE WIND-TUNNEL TESTS OF A WINGLESS VERTICAL TAKE-OFF ANDLANDING AIRCRAFT - PRELIMINARY RESULTS, David G. Hoenig and JamesA. Brady, October 1960 TN D 328 PHOTOGRAPHIC EVIDENCE OF STREAMWISE ARRAYS OFVORTICES IN BOUNDARY-LAYER FLOW,EdwardJ. Hopkins, Stephen J. Keating, Jr., and Angelo Bandettini, September 1960 TN D 329 RADIATION SHIELDING OF THESTAGNATION REGION BY TRANSPIRATION OFAN OPAQUE GAS, John ThomasHowe, September1960 TND 333 LARGE-SCALE WIND-TUNNEL TESTS ANDEVALUATION OF THELOW-SPEED PERFORMANCE OFA 35° SWEPTBACK WING JET TRANSPORT MODEL EQUIPPED WITHA BLOWING BOUNDARY-LAYER-CONTROL FLAPANDLEADING-EDGE SLAT, David H. Hickey and Kiyoshi Aoyagi, October 1960 TND 334 MOTION ANDHEATING DURING ATMOSPHERE REENTRY OF SPACE VEHICLES, ThomasJ. Wong, Glen Goodwin, and Robert E. Slye, September 1960 TN D 335 FULL-SCALE WIND-TUNNEL TESTS OF BLOWING BOUNDARY-LAYER CONTROL APPLIED TO A HELICOPTER ROTOR, John L. McCloud III, Leo P.

Hall, and JamesA. Brady, September 1960 TN D 338 EFFECTS OF SWEEP ANGLE ONTHEBOUNDARY-LAYER STABILITYCHARAC- TERISTICS OFAN UNTAPERED WING AT LOWSPEEDS, Frederick W. Boltz, George C. Kenyon, and Clyde Q. Allen, October 1960 TN D 340 THENUMERICAL CALCULATION OF FLOW PASTCONICAL BODIESSUPPORTING ELLIPTIC CONICAL SHOCK WAVES AT FINITE ANGLES OF INCIDENCE, Benjamin R. Briggs, November1960 TN D 341 EXPERIMENTAL INVESTIGATION OF A HYPERSONIC GLIDER CONFIGURATION AT A MACH NUMBER OF 6 ANDAT FULL-SCALE REYNOLDS NUMBERS, Alvin Seiff and Max E. Wilkins, January 1961 TN D 342 EXPLORATORY STUDY OF THEREDUCTION IN FRICTION DRAG DUETO STREAMWISE INJECTION OFHELIUM,Byron L. Swenson,January 1961 TN D 346 THESHOCK-WAVE PATTERNS ONA CRANKED-WING CONFIGURATION, Robert I. Sammonds, November1960 TN D 349 TRANSITION REYNOLDS NUMBERS OF SEPARATED FLOWS AT SUPERSONIC SPEEDS, HowardK. Larson and Stephen J. Keating, Jr., December TND 352 CONSTANT ENTROPY PORPERTIES FORANAPPROXIMATE MODEL OF EQUILB- RIUMAIR, C. Frederick Hansenand Marion E. Hodge, January 1961 TN D 353 EXPERIMENTAL DETERMINATION OF THERECOVERY FACTOR ANDANALYTICAL SOLUTION OF THECONICAL FLOW FIELDFORA 20° INCLUDED ANGLE CONE AT MACH NUMBERS OF 4.6 AND6.0 ANDSTAGNATION TEMPERATURES 2600°R., Frank A. Pfyl and Leroy L. Presley, June 1961 TN D 354 EFFECTS OF STING-SUPPORT DIAMETER ONTHEBASEPRESSURES OF AN ELLIPTICCONE AT MACH NUMBERS FROM 0.60 to 1.40, Louis S. Stivers, Jr. and Lionel L. Levy, Jr., February 1961 TND 356 INTERIMDEFINITIVEORBITFORTHESATELLITE 1958 - GAMMA, EXPLORER iII_ Theory and Analysis Staff, Goddard Space Flight Center, June THEVECTOR FIELDPROTON MAGNETOMETER FORIGY SATELLITE GROUND TND 358 STATIONS, I. R. Shapiro, J. D. Stolarik, and J. P. Heppner, October 1960 TN D 359 INTERIMDEFINITIVEORBITFORTHESATELLITE 1958-ALPHA,EXPLORER- I, Theory and Analysis Staff, Goddard SpaceFlight Center, September 1960 FREE-FLIGHT MEASUREMENTS OF THETRANSONIC DRAG CHARACTERISTICS TN D 361 OF LOW-FINENESS-RATIO CYLINDERS INCLUDING STABILIZING PLATES ANDFLARES ANDVARYING NOSE BLUNTNESS, Joseph H. Judd and Gerard E. Woodbury,May 1960 EFFECTS OF TRANSIENT HEATING ONTHEVIBRATION FREQUENCIES OF TN D 362 A PROTOTYPE OF THEX-15 WING,Robert R. McWithey and Louis F Vosteen, May 1960 INVESTIGATION OF THEAERODYNAMIC CHARACRERISTICS OF A COMBINA- TN D 363 TION JET-FLAPANDDEFLECTED-SLIPSTREAM CONFIGURATION AT ZERO ANDLOW FORWARD SPEEDS, Kenneth P. Spreemannand Edwin E.

Davenport, May 1960 TND 365 SHOCK-WAVE STRUCTURE BASED ONIKENBERRY-TRUESDELL APPROACH TO KINETICTHEORY OF GASES, Robert E. Street, February 1960 PRELIMINARY EXPERIMENTAL INVESTIGATION OF EFFECT OFFREE-STREAM TN D 368 TURBULENCE ONTURBULENT BOUNDARY-LAYER GROWTH, S. J. Kline, A. V. Lisin, and B. A. Waitman, March 1960 A FLIGHTSTUDY OFTHECONVERSION MANEUVER OF A TILT-DUCT VTOL TND 372 AIRCRAFT, Robert J. Tapscott and Henry L. Kelley, November AN INVESTIGATION OF INDUCED-PRESSURE PHENOMENA ONAXIALLY TN D 373 SYMMETRIC, FLOW-ALINED, CYLINDRICAL MODELS EQUIPPED WITH DIFFERENT NOSE SHAPES AT FREE-STREAM MACH NUMBERS FROM 15.6 TO 21 IN HELIUM,JamesN. Mueller, William H. Close, and Arthur Henderson, Jr., May 1960 HIGH-TIP-SPEED STATIC-THRUST TESTS OFA ROTOR HAVING NACA TND 376 63(215)A018 AIRFOIL SECTIONS WITHANDWITHOUT VORTEX GENERATORS INSTALLED, JamesP. Shivers, May 1960 FORCE INVESTIGATION OF THREE SURFACE-PIERCING SUPERCAVITATING TN D 378 HYDROFOILS WITH15° NEGATIVE DIHEDRAL, Irving Weinstein, June FREE-SPINNING-TUNNEL INVESTIGATION OFA 1/20-SCALE MODEL OF TND 381 AN UNSWEPT-WING JET-PROPELLED TRAINER AIRPLANE, JamesS.

Bowman, Jr. and Frederick M. Healy, June 1960 TN D 383 THEORETICAL CALCULATIONS OF THEPRESSURES, FORCES, ANDMOMENTS DUETOVARIOUS LATERAL MOTIONS ACTING ONTAPERED SWEPTBACK VERTICAL TAILS WITHSUPERSONIC LEADING ANDTRAILINGEDGES, Kenneth Margolis and Miriam H. Elliott, August 1960 TN D 385 A VISUALTECHNIQUE FORDETERMINING QUALITATIVE AERODYNAMIC HEATING RATES ONCOMPLEX CONFIGURATIONS, P. Calvin Stainback, October 1960 EFFECT OF STREAMLINE CONTOURING IN THEWING-FUSELAGE JUNCTURE TND 387 IN COMBINATION WITHTHESUPERSONIC AREA RULEONA SWEPTBACK- WING-FUSELAGE CONFIGURATION OF HIGHFINENESS RATIO, Charles D.

Trescot, Jr., May 1960 TN D 388 TRANSONIC PERFORMANCE CHARACTERISTICS OF SEVERAL JET NOISE SUPPRESSORS, JamesW. Schmeer, Leland B. Salters, Jr., and Marlowe D. Cassetti, July 1960 TND 389 THELONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A SWEPTBACK WING-BODY COMBINATION WITHANDWITHOUT ENDPLATES AT MACH NUMBERS FROM 0.40 TO 0.93, William P. Henderson, May 1960 TN D 390 AERODYNAMIC CHARACTERISTICS OF A I/4-SCALE MODEL OFA TILT- WING VTOLAIRCRAFT AT HIGHANGLES OF WINGINCIDENCE, Louis P.

Tosti, September 1960 TN D 391 THEINFLUENCE OF LOW WALL TEMPERATURE ONBOUNDARY-LAYER TRANSI- TIONANDLOCAL HEATTRANSFER ON2-1NCH-DIAMETER HEMISPHERES AT A MACH NUMBER OF 4.95 ANDA REYNOLDS NUMBER PERFOOT OF 73.2 x 106, Morton Cooper, Edward E. Mayo, and Jerome D. Julius, July TN D 394 EQUATIONS FORTHEINDUCED VELOCITIES NEAR A LIFTINGROTOR WITH NONUNIFORM AZIMUTH-WISE VORTICITY DISTRIBUTION, Harry H. Heyson, August 1960 TN D 395 FREE-FLIGHT MEASUREMENTS OF THEZERO-LIFT DRAG OF SEVERAL WINGS AT MACH NUMBERS FROM 1.4 TO 3.8, H. Herbert Jackson, June 1960 TND 399 VARIATION IN HEATTRANSFER DURING TRANSIENT HEATING OF A HEMI- SPHERE AT A MACH NUMBER OF 2, Roland D. English and Howard S.

Carter, June 1960 TND 403 LOW-SPEED AERODYNAMIC CHARACTERISTICS OF A MODEL OF A HYPERSONIC RESEARCH AIRPLANE AT ANGLES OFATTACK UP TO 90° FORRANGE OF REYNOLDS NUMBERS, JamesS. Bowman, Jr. and William D. Grantham, September1960 TN D 404 HOVERING ANDTRANSITION FLIGHTTESTS OF I/5-SCALE MODEL OF A JET-POWERED VERTICAL-ATTITUDE VTOLRESEARCH AIRPLANE,Charles C. Smith, Jr., May 1961 TN D 406 EFFECTS OFAIR CONTAMINATION IN A HELIUM TUNNEL, Arthur Henderson, Jr. and Frank E. Swalley, June 1960 TN D 407 AERODYNAMIC CHARACTERISTICS OFA LARGE-SCALE UNSWEPT WING-BODY-TAIL CONFIGURATION WITHBLOWING APPLIED OVER THEFLAPANDWING LEADING EDGE,H. Clyde McLemore and John B. Peterson, Jr., September1960 TN D 408 THEBLUNT PLATEIN HYPERSONIC FLOW,Donald L. Baradell and Mitchel H. Bertram, October 1960 TN D 409 WIND-TUNNEL INVESTIGATION OFA SMALL-SCALE MODEL OF ANAERIAL VEHICLE SUPPORTED BY TILTINGDUCTED FANS,Charles C. Smith, Jr., August 1960 TN D 410 INTERIMDEFINITIVEORBITFORTHESATELLITE 1958-EPSILON, EXPLORER- IV, Theory and Analysis Staff, Goddard SpaceFlight Center, September 1960 TN D 411 INTERIM DEFINITIVEORBITFORTHESATELLITE 1959-ALPHA VANGUARD-II, Theory and Analysis Staff, Goddard SpaceFlight Center, September TN D 412 THEFLUXANDENERGY SPECTRA OFTHEPROTONS IN THEINNERVANALLEN BELT, John E. Naugle and Donald A. Kniffen, August 1961 TND 413 ROCKET MEASUREMENT OFA DAYTIME ELECTRON DENSITY PROFILE UP TO 620 KILOMETERS, J. E. Jackson and S. J. Bauer, September 1961 TND 414 INSTRUMENTATION OFTHEIONOSPHERE DIRECT MEASUREMENTS SATELLITE (EXPLORER VIII), R. E. Bourdeau, J. L. Donley, and E. C. Whipple, Jr., April 1962 TND 415 AN EXPERIMENTAL INVESTIGATION OF THEEFFECT OF WINDTUNNEL WALLS ONTHEAERODYNAMIC PERFORMANCE OFA HELICOPTER ROTOR, Victor M.

Ganzer and William H. Rae, Jr., May 1960 TND 417 INVESTIGATION OF EFFECTS OF ROUGHNESS, SURFACE COOLING, ANDSHOCK IMPINGEMENT ONBOUNDARY-LAYER TRANSITION ONA TWO-DIMENSIONAL WING,K. R. Czarnecki and John R. Sevier, Jr., June 1960 TN D 419 EFFECT OF GROUND PROXIMITY ONAERODYNAMIC CHARACTERISTICS OF TWO HORIZONTAL-ATTITUDE JET VERTICAL-TAKE-OFF-AND-LANDING AIRPLANE MODELS, William A. Newsom, Jr., August 1960 TN D 422 A WIND-TUNNEL INVESTIGATION OFTHEDEVELOPMENT OF LIFT ONWINGS IN ACCELERATED LONGITUDINAL MOTION, ThomasR. Turner, August 1960 TN D 423 THESUPERSONIC TRANSPORT - A TECHNICAL SUMMARY, Langley Research Center Staff, June 1960 TN D 425 TRIM DRAG AT SUPERSONIC SPEEDS OF VARIOUS DELTA-PLANFORM CONFIGURATIONS_ M. E. Graham and B. M. Ryan_ June 1960 TN D 431 AN EXPERIMENTAL STUDY OF THE IONIZATION OF LOW-DENSITY GAS FLOWS BY INDUCED DISCHARGES_ R. L. Barger_ J. D. Brooks_ and W. D. Beasley_ September 1960 TN D 432 A SUMMARY OF OPERATING CONDITIONS EXPERIENCED BY THREE MILITARY HELICOPTERS AND A MOUNTAIN-BASED COMMERCIAL HELICOPTER_ Andrew B. Connor_ October 1960 TN D 434 LOW-SPEED INVESTIGATION OF A FULL-SPAN INTERNAL-FLOW JET- AUGMENTED FLAP ON A HIGH-WING MODEL WITH A 35 ° SWEPT WING OF ASPECT RATIO 7.0._ Thomas R. Turner_ August 1960 TN D 435 TRANSONIC AND SUPERSONIC WIND-TUNNEL TESTS OF WING-BODY COMBINATIONS DESIGNED FOR HIGH EFFICIENCY AT A MACH NUMBER OF 1.41_ Frederick C. Grant and John R. Sevier_ Jr._ October 1960 TN D 436 EXPERIMENTAL INVESTIGATION OF TWO LOW-DRAG SUPERCAVITATING HYDROFOILS AT SPEEDS UP TO 200 FEET PER SECOND_ Kenneth W.

Christopher and Virgil E. Johnson_ Jr._ August 1960 A TWO-IMPULSE PLAN FOR PERFORMING RENDEZVOUS ON A ONCE-A-DAY TN D 437 BASIS_ John D. Bird and David F. Thomas_ Jr._ November 1960 TN D 443 PRELIMINARY INVESTIGATION OF A PARAGLIDER_ Francis M. Rogallo_ John G. Lowry_ Delwin R. Croom_ and Robert T. Taylor_ August_ 1960 TN D 446 SOME EXAMPLES OF THE APPLICATIONS OF THE TRANSONIC AND SUPER- SONIC AREA RULES TO THE PREDICTION OF WAVE DRAG_ Robert L.

Nelson and Clement J. Welsh_ September 1960 TN D 448 SOME LANDING STUDIES PERTINENT TO GLIDER-REENTRY VEHICLES_ John C. Houbolt and Sidney A. Batterson_ August 1960 TN D 449 INVESTIGATION OF THE FLOW OVER SIMPLE BODIES AT MACH NUMBERS OF THE ORDER OF 20_ Arthur Henderson_ Jr._ August 1960 TN D 453 LANDING ENERGY DISSIPATION FOR MANNED REENTRY VEHICLES_ Lloyd J. Fisher_ Jr._ September 1960 TN D 455 EFFECT OF REYNOLDS NUMBER ON THE FORCE AND PRESSURE DISTRIBUTION CHARACTERISTICS OF A TWO-DIMENSIONAL LIFTING CIRCULAR CYLINDER_ Vernard E. Lockwood and Linwood W. McKinney_ September 1960 TN D 456 DIFFUSION OF SOUND WAVES IN A TURBULENT ATMOSPHERE_ Richard H.

Lyon_ September 1960 TN D 458 EXPERIMENTAL SMOKE ANDELECTROMAGNETIC ANALOG STUDY OF INDUCED FLOW FIELD ABOUT A MODEL ROTOR IN STEADY FLIGHTWITHINGROUND EFFECT_ Robin B. Gray_ August 1960 TN D 461 SOME DIVERGENCE CHARACTERISTICS OF LOW-ASPECT-RATIO WINGS AT TRANSONIC ANDSUPERSONIC SPEEDS_ Donald S, Woolston_ Frederick W. Gibson_ and Herbert J. Cunningham_ September1960 TND 462 REAL-GAS CORRECTION FACTORS FORHYPERSONIC FLOW PARAMETERS IN HELIUM_ WayneD. Erickson_ September 1960 TN D 468 DISTRIBUTION OF TIME-AVERAGED PRESSURE FLUCTUATIONS ALONG THE BOUNDARY OFA ROUND SUBSONIC JET_ Walton L. Howes_October 1960 TN D 470 ANALYSIS OF TRAJECTORY PARAMETERS FORPROBE ANDROUND-TRIP MISSI- ONSTO VENUS_ JamesF. Dugan_Jr._ and Carl R. Simsic_ November TN D 471 AN EXPLORATORY STATISTICAL ANALYSIS OF A PLANET APPROACH-PHASE CUIDANCE SCHEME USING ANGULAR MEASUREMENTS WITHSIGNIFICANT ERROR_ Alan L. Friedlander and David P. Harry III_ September 1960 TN D 481 COLLISION INTEGRALS FORA MODIFIED STOCKMAYER POTENTIAL_ EugeneC.

Itean_ Alan R. Glueck_ and Roger A. Svehla_ .January 1961 TN D 483 EMPIRICAL EQUATION FORTURBULENT FORCED CONVECTION HEAT TRANSFER FORPRANDTL NUMBERS FROM 0.001 to I000_ UweH. von Glahn_ December TN D 486 PROJECT VANGUARD MAGNETIC-FIELD INSTRUMENTATION ANDMEASUREMENTS_ J. P. Heppmer_ J. D. Stolarik_ I. R. Shapiro_ and J. C. Cain_ September 1960 TN D 487 THESOLAR WIND_ J. R. Herring and A. L. Licht_ September 1960 TN m 488 RECENT DIRECT MEASUREMENTS BY SATELLITES OF COSMIC DUST IN THE VICINITY OF THEEARTH_ H. E. LaCowand W. M. Alexander_ September TN D 489 DETERMINATION OF SATELLITE ORBITS FROM RADAR DATA_ W. F. Cahill and I. Harris_ September1960 TN D 490 THEORIGINOF TEKTITES_ J. A. O'Keefe_ November1960 TN D 491 IONOSPHERIC MEASUREMENTS USINGEVNIRONMENTAL SAMPLING TECHNIQUES_ R. E. Bourdeau_J. E. Jackson_ !. A. Kane_ and G. P. Serbu_ September 1960 TN D 492 A MODIFIED HANSEN'S THEORY AS APPLIED TO THEMOTION OF ARTIFICIAL SATELLITES_ Peter Musen_November1960 TN D 493 A METHOD OF ESTIMATING RESIDUALS IN ORBITAL THEORY_ Myron Lecar_ January 1961 TN D 494 DEVELOPMENT OF THE LUNAR AND SOLAR PERTURBATION IN THE MOTION OF AN ARTIFICIAL SATELLITEj P. Musen_ A. Bailie_ and E. Upton_ January TN D 501 VERY RESTRICTED FOUR-BODY PROBLEM_ Su-Shu Huang_ September 1960 TN D 502 SOME DYNAMICAL PROPERTIES OF THE NATURAL AND ARTIFICIAL SATELLITES_ Su-Shu Huang_ September 1960 TN D 503 REEVALUATION OF IONOSPHERIC ELECTRON DENSITIES AND COLLISION FREQUENCIES DERIVED FROM ROCKET MEASUREMENTS OF REFRACTIVE INDEX AND ATTENUATION_ J. A. Kane_ November 1960 TN D 504 A THERMISTOR PRESSURE GAUGE_ A. P. Flanick and J. Ainsworth_ November 1960 RADIO TRANSMISSION THROUGH THE PLASMA SHEATH AROUND A LIFTING TN D 507 REENTRY VEHICLE_ Macon C. Ellis_ Jr._ and Paul W. Huber_ January TN D 509 SUPERSONIC AERODYNAMIC CHARACTERISTICS OF A LOW-DRAG AIRCRAFT CONFIGURATION HAVING AN ARROW WING OF ASPECT RATIO 1.86 AND A BODY OF FINENESS RATIO 20_ Warren Gillespie_ Jr._ October 1960 TN D 512 SHOCK-WAVE LAMINAR-BOUNDARY-LAYER INTERACTION ON A CONVEX WALL_ Isaac Greber_ October 1960 TN D 523 INVESTIGATION OF THE FLOW IN A RECTANGULAR CAVITY IN A FLAT PLATE AT A MACH NUMBER OF 3.55_ Russell W. McDearmon_ September TN D 528 BASIC PRESSURE MEASUREMENTS AT A MACH NUMBER OF 1.43 ON A THIN 45 ° SWEPTBACK HIGHLY TAPERED WING WITH SYSTEMATIC SPANWISE TWIST VARIATIONS_ John P. Mugler_ Jr._ Elizabeth R. Woodall_ October TN D 529 AERODYNAMIC AND HYDRODYNAMIC CHARACTERISTICS OF A MODEL OF A 500_000-POUND HIGHSUPERSONICMULTIJET LOGISTICS TRANSPORT SEA- PLANE_ Walter J. Kapryan_ Kenneth W. Goodson_ and Irving Weinstein_ March 1961 TN D 5B0 A RADIANT HEATER TO SIMULATE AERODYNAMIC HEATING IN A WIND TUNNEL_ Donald N. Trussell and Deene J. Weidman_ November 1960 HOVERING MEASUREMENTS FOR TWIN-ROTOR CONFIGURATIONS WIT_ AND TN D 534 WITHOUT OVERLAP_ George E. Sweet_ November 1960 A STUDY OF THE FEASIBILITY OF INFLATABLE REENTRY GLIDERS_ Walter TN D 538 B. Olstad_ October 1960 TN D 540 EFFECTS OF FINENESS RATIO AND REYNOLDS NUMBER ON THE LOW-SPEED CROSSWIND DRAG CHARACTERISTICS OF CIRCULAR AND MODIFIED SQUARE CYLINDERS_ Linwood W. McKinney_ October 1960 _ D 545 A NOTE ON THE DRAG DUE TO LIFT OF DELTA WINGS AT MACH NUMBERS UP TO 2.0_ Robert S. Osborne and Thomas C. Kelly_ November 1960 ATMOSPHERIC TURBULENCE MEASUREMENTS OBTAINED FROM AIRPLANE TN D 548 OPERATIONS AT ALTITUDES BETWEEN 20_000 AND 75_000 FEET FOR SEVERAL AREAS IN THE NORTHERN HEMISPHERE_ Thomas L. Coleman and Roy Steiner_ October 1960 HEAT-TRANSFER MEASUREMENTS AT A MACH NUMBER OF 4.95 ON TWO 60 ° TN D 549 SWEPT DELTA WINGS WITH BLUNT LEADING EDGES AND DIHEDRAL ANGLES OF 0 ° AND 45°_ P. Calvin Stainback_ January 1961 HEAT-TRANSFER MEASUREMENTS ON THE APEXES OF TWO 60 ° SWEPTBACK TN D 550 DELTA WINGS (PANEL SEMIAPEX ANGLE OF 30 ° ) HAVING 0 ° AND 45 ° DIHEDRAL AT A MACH NUMBER OF 4.95_ Charles R. Gunn_ January 1961 COMPARISON OF THEORETICAL AND EXPERIMENTAL VALUES FOR THE EFFECTIVE TN D 553 HEAT _ABLATION OF AMMONIUM CHLORIDE_ Jean E. Welker_ November 1960 THEORY OF THE FLUID OSCILLATIONS IN A CIRCULAR CYLINDRICAL RING TN D 557 TANK PARTIALLY FILLED WITH LIQUID_ Helmut F. Bauer_ December 1960 CHARACTERISTIC ORBITAL VARIABLES AND THEIR TIME RATES IN UN- TN D 558 PERTURBED ELLIPTIC ORBITS_ Helmut G. L. Krause_ December 1960 TN D 559 ORBITAL STORAGE OF LIQUID HYDROGEN_ ,I. R. Olivier and W. E.

Dempster; August 1961 IDEALIZED WIND PROFILES APPLICABLE FOR THE STUDY OF VEHICLE TN D 560 PERFORMANCE BETWEEN 60KM AND 80KM ALTITUDE_ CAPE CANAVERAL_ William W° Vaughan_ December 1960 INTERLEVEL AND INTRALEVEL CORRELATIONS OF WIND COMPONENTS FOR TN D 561 SIX GEOGRAPHICAL LOCATIONS_ William W. Vaughan_ December 1960 TEMPORAL CHANGES OF TEMPERATURE AS A FUNCTION OF ALTITUDE FOR TN D 562 PATRICK AIR FORCE BASE FLORIDA_ J. W. Smith_ January 1961 THEORETICAL INVESTIGATIONS OF THE ABLATION OF A GLASS-TYPE TN D 564 IIEAT PROTECTION SHIELD OF VARIED _TERIAL PROPERTIES AT THE STAGNATION POINT OF A RE-ENTERING IREM_ Ernst W. Adams_ January 1961 TN D 565 THE JAVELIN SPIKE ANTENNA RADIATION PATTERNS AND VOLTAGE STANDING- WAVE RATIO_ Roland R. Ford_ January 1961 TN D 567 DIRECT MEASUREMENTS OF ION DENSITY AND CONDUCTIVITY IN THE D- REGION_ E. C. Whipple_ Jr._ October 1960 TN D 568 OSCULATING ELEMENTS DERIVED FROM THE MODIFIED HANSEN'S THEORY FOR THE MOTION OF AN ARTIFICIAL SATELLITE_ A° Bailie and R.

Bryant_ January 1961 TN D 569 ON THE MOTION OF A SATELLITE IN AN ASYMMETRICAL GRAVITATIONAL FIELD_ P. Musen_ January 1961 TN D 570 RESULTS FROM A ROCKET-BORNE LAN(IMUIR PROBE EXPERIMENT_ Gideon P. Serbu_ July 1961 TN D 571 ANGULAR MOTION OF THE SPIN AXIS OF THE TIROS I METEOROLOGICAL SATELLITE DUE TO MAGNETIC AND GRAVITATIONAL TORQUES_ W. R.

Bandeen and W. P. Manger_ April 1961 TN D 572 ANALYSIS OF GRAVITATIONAL AND GEOMETRIC ASPECTS OF GEODETIC UTILIZATION OF SATELLITES_ William M. Kaula_ March 1961 TN D 573 ON THE ACCURACY OF AN ELLIPTICAL ORBIT DETERMINATION_ Robert F.

Weirauch_ January 1961 TN D 576 AN EXPERIMENTAL DETERMINATION OF THE DYNAMIC RESPONSE OF A LONG HYDRAULIC LINE_ John D. Regetz_ Jr.j December 1960 TN D 578 EFFECT OF SHIELD POSITION AND ABSORPTIVITY ON TEMPERATURE DISTRIBUTION OF A BODY SHIELDED FROM SOLAR RADIATION IN SPACE_ Lester D. Nichols_ January 1961 TN D 580 SURFACE PRESSURE DISTRIBUTIONS WITH A SONIC JET NORMAL TO ADJACENT FLAT SURFACES AT MACH 2.92 TO 6.41_ Robert W. Cubbison_ Bernhard H. Anderson_ and James J. Ward_ February 1961 TN D 583 ANALYTICAL PERFORMANCE CHARACTERISTICS AND OUTLET FLOW CONDITIONS OF CONSTANT AND VARIABLE LEAD HELICAL INDUCERS FOR CRYOGENIC PUMPS_ John C. Montgomery_ March 1961 TN D 584 SURFACE-TEMPERATURE DISTRIBUTION ON THIN-WALLED BODIES SUBJECTED TO SOLAR RADIATION IN INTERPLANETARY SPACE_ Lester D. Nichols_ October 1961 TN D 588 PROCEEDINGS OF CONFERENCE ON RADIATION PROBLEMS IN MANNED SPACE FLIGHT_ JUNE 21_ 1960_ WASHINGTON_ D. C._ George J. Jacobs# Editor_ APPENDIX A: PRIMARY COSMIC RAYS_ J. R. Winckler_ December 1960 TN D 590 APPROXIMATE ANALYSIS OFATMOSPHERIC ENTRY CORRIDORS ANDANGLES_ Roger W. Luidens_ January 1961 TN D 593 BASE-FLOW AERODYNAMICS OFA SATURN-TYPE BOOSTER STAGE AT MACH NUMBERS 0.I TO 2.0_ John L. Allen_ March 1962 TN D 594 AN ANALYTICAL ANDEXPERIMENTAL STUDY OF THETHERMAL BOUNDARY LAYER ANDEBULLITION CYCLE IN NUCLEATE BOILING_Y_h-Yun Hsu and Robert W. Graham_ May 1961 TN D 595 A REFERENCE ATMOSPHERE FORPATRICK AFB_FLORIDA_ (ANNUAL)_ Orvel E. Smith_ March 1961 GYROSCOPIC MOTION OFAN UNSYMMETRICAL SATELLITE UNDER NOEXTERNAL TN D 596 FORCESj Manfred E. Kuebler_ December1960 TN D 597 LONG RANGE PLANNING FORSPACE TRANSPORTATION SYSTEMS_ H. H.

Koelle_ January 1961 TN D 599 NUMERICALLY STABLE INTERPOLATION FORMULAS WITHFAVORABLE ERROR PROPAGATION FORFIRST- ANDSECOND-ORDER DIFFERENTIAL EQUATIONS_ Erwin Fehlberg_ March 1961 TN D 600 SURVEY OF CHARACTERISTIC VELOCITY REQUIREMENTS FORTWO-IMPULSE TRANSFERS BETWEEN CIRCULAR ANDCOPLANAR EXTERIOR ELLIPTICALORBIT WITHEXPOSITION OFLOCAL ANDOVERALL OPTIMUM SOLUTIONS_ Robert Silber_ March 1961 TN D 601 ARTIFICIAL EARTH SATELLITES ANDSUCCESSFUL SOLAR PROBES 1957- 1960_Walter H. Stafford and Robert M. Croft_ March 1961 TN D 603 TRANSMISSION DEVICE FORREVERSIBILITY OFROTATION WITHEXTREMELY FASTACTION_ J. Boehm_ A. L. Herrmann_and J. F. Blanche_ May 1961 TN D 604 THEEFFECT OF RADIATION FORCE ONSATELLITES OF CONVEX SHAPE_ Herbert B° Holl_ May 1961 TN D 605 ANALYSIS OF ERROR PROGRESSION IN TERMINAL GUIDANCE FORLUNAR LANDING_ P. J. deFries_ July 1961 TN D 606 EMPIRICAL THREE-SI(_MA WINDCOMPONENT PROFILES 45-DEGREE MISSILE FLIGHTAZIMUTH ATLANTIC MISSILE RANGE PATRICK AFB (CAPECANAVERAL)_ FLORIDA_ William W. Vaughan_July 1961 TN D 607 AUTOMATIC FIXED-CAMERA ORIENTATION PROCEDURES_ C. L. Bannister_ August 1961 TN D 608 JUNOII SUMMARY PROJECT REPORT.VOLUME I. EXPLORER VII SATELLITE_ Marshall SpaceFlight Center_ July 1961 TND 609 HORIZON SENSOR PERFORMANCE IN MEASURING ALTITUDE ABOVE THEMOON, P. J. de Fries, July 1961 TN D 610 MONTHLY ANDANNUAL WINDDISTRIBUTION AS A FUNCTION OFALTITUDE FORPATRICK AIR FORCE BASE,CAPE CANAVERAL, FLORIDA,J. W.

Smith and W. W. Vaughn, July 1961 TN D 612 RANGE OF DENSITY VARIABILITYFROM SURFACE TO 120 KMALTITUDE, Orvel E. Smith and Halsey B. Chenoweth, July 1961 TN D 614 THETIROSLOW RESOLUTION RADIOMETER, Frank Bartko, Virgil Kunde, Clarence Catoe, and MusaHaler, September 1964 TN D 615 MEASUREMENT OF THEMAXIMUM SPEED ATTAINED BYTHEX-15 AIRPLANE POWERED WITHINTERIMROCKET ENGINES, Wendell H. Stillwell and Terry J. Larson, September 1960 TN D 617 AN INVESTIGATION OFA PHOTOGRAPHIC TECHNIQUE OFMEASURING HIGH SURFACE TEMPERATURES, JamesH. Siviter, Jr. and H. Kurt Strass, November1960 TN D 618 EXTENSION OF BOUNDARY-LAYER-SEPARATION CRITERIA TO A MACH NUMBER OF 6.5 BYUTILIZING FLATPLATES WITHFORWARD-FACING STEPS,James R. Sterrett and JamesC. Emery, December1960 TN D 619 DETERMINATION OF THEREQUIRED NUMBER OFRANDOMLY SPACED COMMUNI- CATION SATELLITES, Floyd V. Bennett, ThomasL. Coleman, and John C. Houbolt, January 1961 TN D 621 EXPERIMENTAL ANDCALCULATED FLOW FIELDSPRODUCED BYAIRPLANES FLYINGAT SUPERSONIC SPEEDS, Harriet J. Smith, November1960 TN D 622 AERODYNAMIC CHARACTERISTICS AT LOWSPEED OFA REENTRY CONFIGURA- TIONHAVING RIGID RETRACTABLE CONICAL LIFTING SURFACES, Paul G.

Fournier, November1960 TN D 623 MEASUREMENT OF THEMAXIMUM ALTITUDE ATTAINED BYTHEX-15 AIRPLANE POWERED WITHINTERIMROCKET ENGINES, Wendell H. Stillwell and Terry J. Larson, October 1960 TN D 624 A PRELIMINARY STUDY OFV/STOLTRANSPORT AIRCRAFT ANDBIBLIOGRAPHY OF NASA RESEARCH IN THEVTOL-STOL FIELD, Staff of Langley Research Center, January 1961 TN D 625 APPLICATION OF SIMILARSOLUTIONS TO CALCULATION OF LAMINAR HEAT TRANSFER ONBODIES WITHYAW ANDLARGE PRESSURE GRADIENT IN HIGH- SPEED FLOW,Ivan E. Beckwith and Nathaniel B. Cohen, January 1961 TN D 626 SATELLITE ATTITUDE CONTROL USING A COMBINATION OF INERTIAWHEELS ANDA BARMAGNET, JamesJ. Adamsand Roy F. Brissenden, November TN D 627 EXPERIMENTS WITHPLASMAS PRODUCED BYPOTASSIUM-SEEDED CYANOGEN OXYGEN FLAMES FORSTUDY OF RADIOTRANSMISSION AT SIMULATED REENTRY VEHICLE PLASMA CONDITIONS, Paul W. Huber and Paul B.

Gooderum, APPENDIX A: PRELIMINARY ATTENUATION MEASUREMENTS OF 219.5-mc PROPAGATION THROUGH THEPLASMA, Theo E. Sims and Duncan E. Mclver, Jr., APPENDIX B: DIAGNOSTIC ANDTRANSMISSION STUDIES OF THEPLASMA USINGMICROWAVE TECHNIQUES, Joseph Burlock and William L. Grantham, January 1961 TND 628 LANDING CHARACTERISTICS OF A REENTRY CAPSULE WITHA TORUS- SHAPED AIR BAGFORLOAD ALLEVIATION, John R. McGehee and Melvin E. Hathaway, November1960 TND 629 AN EXPLORATORY STUDY OF A PARAWING AS A HIGH-LIFT DEVICE FOR AIRCRAFT, Rodger L. Naeseth, November1960 TND 631 CHARACTERISTICS AT MACH NUMBER OF 2.03 OF A SERIES OF WINGS HAVING VARIOUS SPANWISE DISTRIBUTIONS OF THICKNESS RATIOAND CHORD, A. Warner Robins, Roy V. Harris, Jr. and Charlie M.

Jackson, Jr., October 1960 TND 634 EFFECTS OF CONE ANGLE,MACH NUMBER, ANDNOSE BLUNTING ON TRANSITION AT SUPERSONIC SPEEDS, K. R. Czarneeki and Mary W.

Jackson, January 1961 TN D 636 A WIND-TUNNEL INVESTIGATION OFA TRANSONIC-TRANSPORT CONFIGURA- TION UTILIZING DRAG-REDUCING DEVICES AT MACH NUMBERS FROM 0.20 TO 1.03, Donald L. Loving, March 1961 TN D 637 WIND-TUNNEL INVESTIGATION OF THEEFFECTS OF WING BODIES,FENCES, FLAPS,ANDA FUSELAGE ADDITION ONTHEWINGBUFFET RESPONSE OFA TRANSONIC-TRANSPORT MODEL, Elden S. Cornette, April 1961 TN D 639 EXPERIMENTAL STUDY OF A SINGLE-COIL INDUCED-ELECTROMOTIVE-FORCE PLASMA ACCELERATOR, Clarence W. Matthews and William F. Cuddihy, January 1961 TN D 640 AERODYNAMIC CHARACTERISTICS OF A MODEL OFAN INFLATABLE-SPHERE LAUNCHING VEHICLE UNDER SIMULATED CONDITIONS OF MACH NUMBER AND ALTITUDE,Ross B. Robinson and Odell A. Morris, December1960 TN D 642 EFFECT OF SHOCK IMPINGEMENT ONTHEDISTRIBUTION OF HEAT-TRANSFER COEFFICIENTS ONA RIGHTCIRCULAR CYLINDER AT MACH NUMBERS OF 2.65, 3.51, AND 4.44, Robert A. New3ander, January 196] TN D 645 CALCULATION OF WIND COMPENSATION FOR LAUNCHING OF UNGUIDED ROCKETS, Robert L. James, Jr. and Ronald J. Harris, April,1961 TN D 648 EXTERNAL-DRAG ESTIMATION FOR SLENDER CONICAL DUCTED BODIES AT HIGH MACH NUMBERS AND ZERO ANGLE OF ATTACK, E. Floyd Valentine, March 1961 TND 650 SOME EFFECTS OFNOSE BLUNTNESS ANDFINENESS RATIOONTHESTATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF BODIES OF REVOLUTION AT SUBSONIC SPEEDS, William C. Hayes, Jr. and William P. Henderson, February 1961 TN D 652 THEORETICAL EVALUATION OF THEPRESSURES, FORCES, ANDMOMENTS AT HYPERSONIC SPEEDS ACTING ONARBITRARY BODIES OF REVOLUTION UNDERGOING SEPARATE ANDCOMBINED ANGLE-OF-ATTACK ANDPITCHING MOTIONS, Kenneth Margolis, June 1961 TND 653 LANDING CHARACTERISTICS ANDFLOTATION PROPERTIES OF A REENTRY CAPSULE, Victor L. Vaughan, Jr., February 1961 TN D 656 LOW-SPEED INVESTIGATION OF THEEFFECTS OFLARGE WING-SIDESLIP ANGLES ONTHEAERODYNAMIC CHARACTERISTICS OF TWO ARROW-WING- FUSELAGE ARRANGEMENTS, ThomasG. Gainer, February 1961 TN D 657 A THEORETICAL INVESTIGATION OF VORTEX-SHEET DEFORMATION BEHIND A HIGHLY LOADED WING ANDITS EFFECT ONLIFT, Clarence D. Cone, Jr., April 1961 TN D 658 GROUND INFLUENCE ONA MODEL AIRFOIL WITHA JET-AUGMENTED FLAP AS DETERMINED BYTWO TECHNIQUES, ThomasR. Turner, February 1961 TN D 660 EFFECTS OF VARIOUS ARRANGEMENTS OF SLOTTED ANDROUND JET EXITS ONTHELIFT ANDPTICHING-MOMENT CHARACTERISTICS OFA RECTANGULAR- BASE MODEL AT ZERO FORWARD SPEED, Raymond D. Vogler, February 1961 TN D 665 THEION-TRAP RESULTS IN "EXPLORATION OF THEUPPER ATMOSPHERE WITHTHEHELPOF THETHIRDSOVIET SPUTNIK",Elden C. Whipple, Jr., January 1961 TN D 666 EIGHT-LEVEL PULSE-HEIGHT ANALYZER FORSPACE PHYSICS APPLICATIONS, U. D. Desai, R. L. Van Allen, and G. Porreca, January 1961 TND 667 SUMMARY OFROCKET ANDSATELLITE OBSERVATIONS RELATED TO THE IONOSPHERE, J. Carl Seddon, January 1961 TND 669 A VERY LOW FREQUENCY (VLF) SYNCHRONIZING SYSTEM, Chesley H.

Looney, Jr., February 1961 TN D 670 MEASI_EMENT OFUPPER-ATMOSPHERE STRUCTURE BYMEANS OFTHEPITOT- STATICTUBE,J. E. Ainsworth, D. F. Fox, and H. E. LaGow, February 1961 TND 671 DISCUSSIONS OF SOLAR PROTON EVENTS ANDMANNED SPACE FLIGHT, Kinsey A. Anderson and Carl E. Fichtel, March 1961 TN O 672 A DIGITALRECORDING SYSTEM FORSATELLITE tRACKING DATA,Thomas P. Sifferlen and William M. Hocking, May 1961 TN D 673 ULTRAVIOLET ASTRONOMICAL PHOTOMETRY FROM ROCKETS, Albert Boggess III, June 1962 TN D 674 AN INSTRUMENT TOMEASURE THESOLAR CONSTANT FROM A SATELLITE, Rudolf A. Hanel, April 1961 TN D 679 TWO-DIMENSIONAL ION BEAMS WITHSMALL LAIERALSPREADING, Harold Mirels, March 1961 TN D 680 A ONE-DIMENSIONAL ANALYSIS OFA MAGNETO-HYDRODYNAMIC ENERGY CONVERSION, Robert G. Deissler, March 1961 TND 681 RADIATION SHIELDING FOR MANNED SPACE FLIGHT,Lewis E. Wallner and Harold R. Kaufman, July 1961 TND 683 THERMOLUMINESCENCE OF SODIUM CHLORIDE IRRADIATED WITH40-MEV ALPHA PARTICLES, Charles C. Giamati, Michael Hacskaylo, and Gabriel Allen, March 1961 AN EXPLICITLINEARFILTERING SOLUTION FORTHEOPTIMIZATION OF TND 685 GUIDANCE SYSTEMS WITHSTATISTICAL INPUTS,Elwood C. Stewart, February 1961 TN D 687 EXPERIMENTAL ANDTHEORETICAL STUDY OF HEATCONDUCTION FORAIR UP TO 5000 ° K., Tzy-ChengPeng and Warrent F. Ahtye, February SURFACE PRESSURES ANDHEATTRANSFER ONUNSWEPT BLUNT PLATES IN TN D 688 HELIUM AT HIGHMACH NUMBERS, Joseph G. Marvin, March 1961 THEFLOW FIELDOVER BLUNTED FLATPLATES ANDITS EFFECT ON TND 689 TURBULENT BOUNDARY-LAYER GROWTH ANDHEAT TRANSFER AT A MACH NUMBER OF 4.7, Thorval Tendeland, Helmer L. Nielsen, and Melvin J. Fohrman, February 1961 TN D 692 A DESIGN STUDY OF THEINFLATED SPHERE LANDING VEHICLE,INCLUDING THELANDING PERFORMANCE ANDTHEEFFECTS OF DEVIATIONS FROM DESIGN CONDITIONS, E. Dale Martin, April 1961 TN D 695 THEIONOSPHERE BEACON SATELLITE,S-45, M. J. Aucremanne, Compiler, January 1961 TND 696 SATELLITE MAGNETIC FIELDMAPPING, JamesP. Heppner, Joseph C.

Cain, Ivan R. Shapiro and John D. Stolarik, May 1961 TN D 697 BROAD-BAND ULTRAVIOLET FILTERS, Charles B. Childs, April 1961 AN ABSOLUTE DEFINITIONOFPHASE SHIFTIN THEELASTICSCATTERING TN D 698 OFA PARTICLE FROM COMPOUND SYSTEMS, Aaron Temkin, April 1961 TN D 699 A SPECTROPHOTOMETRIC ATTACHMENT FORTHEVACUUM ULTRAVIOLET, NormanN. Axelrod, December1961 TND 700 PRELIMINARY STUDY OF PREDICTION ASPECTS OF SOLAR COSMIC RAY EVENTS, Kinsey A. Anderson, April 1961 TND 701 PHYSICAL SIGNIFICANCE OF THETIROSII RADIATION EXPERIMENT, R. A. Hanel, GSFC,and D. Q. Wark, U. S. Weather Bureau, December1961 TN D 702 A GEOID ANDWORLD GEODETIC SYSTEM BASED ONA COMBINATION OF GRAVIMETRIC, ASTRO-GEODETIC, ANDSATELLITE DATA,William M.

Kaula, May 1961 TN D 703 SEASONAL, LATITUDINAL ANDDIURNAL VARIATIONS IN THEUPPER ATMOSPHERE, W. G. Stroud and William Nordberg, April 1961 TN D 704 INTERACTION OF A CHARGED SATELLITE WITHTHEIONOSPHERE, A. H.

Davis and I. Harris, September 1961 TND 705 CONTRIBUTIONS OF ROCKETS ANDSATELLITES TO THEWORLD MAGNETIC SURVEY, J. P. Heppner, T. L. Skillman and J. C. Cain, September1961 TN D 709 CHOOSING A SUITABLE SWEEP RATEFORSINUSOIDAL VIBRATION TESTING, Neal Granick, October 1961 TN D 710 POWER INPUTTOA SMALL FLATPLATEFROM A DIFFUSELY RADIATING SPHERE, WITHAPPLICATION TO EARTH SATELLITES, F. G. Cunningham, July 1961 TN D 716 AN EXPERIMENTAL STUDY OF CONTINUOUS PLASMA FLOWS DRIVEN BYA CONFINED ARCIN A TRANSVERSE MAGNETIC FIELD, R. L. Barger, J. D.

Brooks, and W. D. Beasley, March 1961 TND 717 EFFECT ONNOSE BLUNTNESS ONTRANSITION FORA CONE ANDA HOLLOW CYLINDER AT MACH NUMBERS 1.41 AND2.01, William J. Monta, Paul W. Howard, and K. R. Czarnecki, April 1961 TN D 718 IRRADIATION EFFECTS OF 22 AND240 MEVPROTONS ONSEVERAL TRANSISTORS ANDSOLAR CELLS,W. C. Hulten, W. C. Honaker, and John L. Patterson, April 1961 TN D 721 EXPLORATORY INVESTIGATION OF TRANSPIRATION COOLING OF A 40° DOUBLE WEDGE USINGNITROGEN ANDHELIUM AS COOLANTS AT STAGNA- TIONTEMPERATURES FROM 1,295 ° F TO 2,910°F., Bernard Rashis, May 1961 TND 723 LAUNCH CHARACTERISTICS OF THE X-15 RESEARCH AIRPLANE AS DETERMINED IN FLIGHT, Gene J. Matranga, February 1961 TN D 724 A TECHNIQUE FOR OBTAINING HYPERVELOCITY IMPACT DATA BY USING THE RELATIVE VELOCITIES OF TWO PROJECTILES, William H. Kinard and Rufus D. Collins, Jr., February 1961 TN D 727 GROUND INTERFERENCE EFFECTS, Robert O. Schade, April 1961 TN D 728 EXPERIMENTAL INVESTIGATION OF A HIGH-SPEED HYDROFOIL WITH PARABOLIC THICKNESS DISTRIBUTION AND AN ASPECT RATIO OF 3, Kenneth W. Christopher, March 1961 TN D 730 AERODYNAMIC CHARACTERISTICS OF PROPELLER-DRIVEN VTOL AIRCRAFT, Robert H. Kirby, March 1961 TN D 731 INDUCED INTERFERENCE EFFECTS ON JET AND BURIED-FAN VTOL CONFIGU- RATIONS IN TRANSITION, Kenneth P. Spreemann, March 1961 TN D 732 INVESTIGATION OF WATER-POND ARRESTING OF A DYNAMIC MODEL OF A JET TRANSPORT, William C. Thompson, May 1961 TN D 733 REVIEW OF BASIC PRINCIPLES OF V/STOL AERODYNAMICS, Richard E.

Kuhn, March 1961 TN D 734 CONSIDERATIONS OF METHODS OF IMPROVING HELICOPTER EFFICIENCY, Richard C. Dingeldein, April 1961 TN D 738 SURVEY OF ALTITUDE-MEASURING METHODS FOR THE VERTICAL SEPARA- TION OF AIRCRAFT, William Gracey, March 1961 TN D 739 AN INVESTIGATION OF A DEVICE TO OSCILLATE A WIND-TUNNEL AIR- STREAM, Charles F. Reid, Jr. and Clifton G. Wrestler, Jr., April 1961 TN D 740 IONIZATION AND DEIONIZATION PROCESSES IN LOW-DENSITY PLASMA FLOWS, Raymond L. Barger, April 1961 TN D 741 A THEORETICAL ANALYSIS OF EFFECTS OF ABLATION ON HEAT TRANSFER TO AN ARBITRARY AXISYMMETRIC BODY, Robert T. Swann and Jerry South, April 1961 TN D 742 HOVERING CHARACTERISTICS OF A ROTOR HAVING AN AIRFOIL SECTION DESIGNED FOR FLYING-CRANE TYPE OF HELICOPTER, James P. Shivers, April 1961 TN D 743 AERODYNAMIC INTERACTION EFFECTS AHEAD OF A SONIC JET EXHAUSTING PERPENDICULARLY FROM A FLAT PLATE INTO A MACH NUMBER 6 FREE STREAM, David J. Romeo and James R. Sterrett, April 1961 TN D 744 AIRSPEED OPERATING PRACTICES OF TURBINE-POWERED COMMERCIAL TRANS- PORT AIRPLANES, Thomas L. Coleman, Martin R. Copp, and Walter G. Walker, April 1961 TN D 745 MEASUREMENTS OF AERODYNAMIC HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONA i0 ° CONE IN FREEFLIGHTAT SUPERSONIC MACH NUMBERS UP TO 5.9, Charles B. Rumseyand Dorothy B. Lee, May TN D 748 ANALYSIS OFA FOUR-STATION DOPPLER TRACKING METHOD USINGA SIMPLE CWBEACON, Clifford L. Fricke and Carl W. L. Watkins, April 1961 TN D 752 AERODYNAMIC CHARACTERISTICS OF PARACHUTES AT MACH NUMBERS FROM 1.6 to 3, Julian D. Maynard, May 1961 PRESSURE MEASUREMENTS ONSHARP ANDBLUNT 5°-AND15°-HALF-ANGLE TN D 753 CONES AT MACH NUMBER 3.86 ANDANGLES OF ATTACK TO i00 °, James L. Amick, February 1961 TN D 756 EFFECTS OFGEOMETRIC VARIATIONS ONLIFT AUGMENTATION OF SIMPLE- PLENUM-CHAMBER GROUND EFFECT MODELS, Edwin E. Davenport, April TN D 758 HEAT-TRANSFER TESTS OF 20-MILLIMETER PROJECTILES AT A MACH NUMBER OF 5 WITHAN ANALYSIS BYUNSTEADY SCALING LAWS TO PRE- DICT COMPONENT TEMPERATURE RISESAFTERFIRINGFORVARIOUS FREE- FLIGHTCONDITIONS, Robert L. Trimpi, James G. Gallagher, and Robert A. Jones, May 1961 TN D 772 TRAJECTORY CONTROL IN RENDEZVOUS PROBLEMS USINGPROPORTIONAL NAVIGATION, Luigi S. Cicolam, April 1961 TND 773 HOT-WIRE HEAT-LOSS CHARACTERISTICS ANDANEMOMETRY IN SUBSONIC CONTINUUM ANDSLIP FLOW,Frederick W. Boltz, February 1961 TN D 774 OPERATIONAL TECHNIQUE FORTRANSITION OF SEVERAL TYPES OF V/STOL AIRCRAFT, Fred J. Drinkwater III, March 1961 TN D 775 AERODYNAMIC CHARACTERISTICS OFA LARGE SCALE MODEL WITHA HIGH DISK-LOADING LIFTING FANMOUNTED IN THEFUSELAGE, Kiyoshi Aoyagi, David H. Hickey, and Richard A. deSavigny, October 1961 TN D 777 BALLISTICRANGE MEASUREMENTS OF STAGNATION POINTHEATTRANSFER IN AIR ANDIN CARBON DIOXIDEAT VELOCITIES UP TO 18,000 FEETPER SECOND, Layton Yee, Harry E. Bailey, and Henry T. Woodward, March 1961 TN D 781 FIRSTPLANNING CONFERENCE ONBIOMEDICAL EXPERIMENTS IN EXTRA- TERRESTRIAL ENVIRONMENTS, February 1961 TN D 783 A PRELIMINARY STUDY OF THESOLAR-PROBE MISSION,DuaneW. Dugan, April 1961 TN D 785 AERODYNAMICS OFA TILTINGDUCTED FANCONFIGURATION, Paul F.

Yaggy and Kenneth W. Goodson,March 1961 TN D 787 PILOTED SIMULATOR TESTS OFA GUIDANCE SYSTEM WHICH CANCON- TINUOUSLY PREDICT LANDING POINTOF A LOW L/D VEHICLE DURING ATMOSPHERE RE-ENTRY, RodneyC. Wingrove and Robert E. Coate, March 1961 TN D 788 SUBSONIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF DISKS WITHELLIPTICCROSS SECTIONS ANDTHICKNESS-DIAMETER RATIOS FROM 0.225 TO 0.425, Fred A. Demele and Jack J. Brownson, April 1961 TN D 790 FILM CONDENSATION WITHANDWITHOUT BODY FORCE IN BOUNDARY- LAYER FLOW OFVAPOR OVER A FLATPLATE,Paul M. Chung, April TN D 791 NUMERICAL SOLUTIONS FORSUPERSONIC FLOW OFAN IDEALGAS AROUND BLUNT TWO-DIMENSIONAL BODIES,Franklyn B. Fuller, July 1961 TN D 793 AERODYNAMIC CHARACTERISTICS IN PITCHANDSIDESLIPOFA 1/15- SCALE MODEL OF THESCOUT VEHICLE AT A MACH NUMBER OF 2.01, Ross B. Robinson, May 1961 TND 794 TRANSONIC WIND-TUNNEL INVESTIGATION OFTHESTATICLONGITUDINAL AERODYNAMIC CHARACTERISTICS OF SEVERAL CONFIGURATIONS OFTHE SCOUT VEHICLE ANDOF A NUMBER OFRELATED MODELS, ThomasC.

Kelly, May 1961 TND 795 A SEMIGRAPHICAL METHOD OF APPLYING IMPACT THEORY TO AN ARBITRARY BODY TOOBTAIN THEHYPERSONIC AERODYNAMIC CHARAC- TERISTICS AT ANGLE OFATTACK ANDSIDESLIP, Charlie M.

Jackson, Jr., May 1961 STATICLONGITUDINAL AERODYNAMIC CHARACTERISTICS AT TRANSONIC TN D 797 SPEEDS OF A BLUNTED RIGHTTRIANGULAR PYRAMIDAL LIFTING REENTRY CONFIGURATION FORANGLES OFATTACK UP TO ii0 °, John P. Mugler, Jr. and Walter B. Olstad, June 1961 SOME SIMPLESOLUTIONS TO THEPROBLEM OF PREDICTING BOUNDARY- TN D 798 LAYER SELF-INDUCED PRESSURES, Mitchel H. Bertram and ThomasA.

Blackstock, April 1961 TN D 800 A SENSOR FOROBTAINING ABLATION RATES,Clyde W. Winters and EmedioM. Bracalente, April 1961 A METHOD OF DETERMINING AERODYNAMIC-INFLUENCE COEFFICIENTS FROM TN D 801 WIND-TUNNEL DATA FORWINGS AT SUPERSONIC SPEEDS, Patrick A.

Gainer, April 1961 TN D 807 FREE-FLIGHT SKIN-TEMPERATURE ANDSURFACE-PRESSURE MEASUREMENTS ONA HIGHLY POLISHED NOSE HAVING A i00 ° TOTAL-ANGLE CONE AND A i0 ° HALF-ANGLE CONICAL FLARE SECTION UP TO A MACH NUMBER OF 4.08, Bernard Rashis and Aleck C. Bond, April 1961 TN D 809 TABLES AND CHARTS OF THE NORMAL COMPONENT OF INDUCED VELOCITY IN THE LATERAL PLANE OF A ROTOR WITH HARMONIC AZIMUTH-WISE VORTICITY DISTRIBUTION, Harry H. Heyson, April 1961 TN D 814 NOMOGRAPHIC SOLUTION OF THE MOMENTUM EQUATION FOR VTOL-STOL AIRCRAFT, Harry H. Heyson, April 1961 TN D 815 LOW-SPEED WIND-TUNNEL INVESTIGATION OF A REFLECTION PLANE WING MODEL EQUIPPED WITH PARTIAL-SPAN JET-AUGMENTED FLAPS, James H. Otis, Jr., May 1961 TN D 817 TRANSONIC AERODYNAMIC CHARACTERISTICS OF A WING-BODY COMBINATION HAVING A 52.5 ° SWEPTBACK WING OF ASPECT RATIO 3 WITH CONICAL CAMBER AND DESIGNED FOR A MACH NUMBER OF_ William B.

Igoe, Richard J. Re, and Marlowe D. Cassetti, May 1961 TN D 819 CHARTS FOR CONICAL AND TWO-DIMENSIONAL OBLIQUE-SHOCK FLOW PARAMETERS IN HELIUM AT MACH NUMBERS FROM ABOUT 1 to I00, Arthur Henderson, Jr., and Dorothy O. Braswell, June 1961 TN D 820 RANDOM DEVIATIONS FROM CRUISE ALTITUDES OF A TURBOJET TRANSPORT AT ALTITUDES BETWEEN 20,000 AND 41,000 FEET, William Gracey and Jo Ann Shipp, April 1961 TN D 821 INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF TWO PRE- LIMINARY DESIGNS OF SCOUT RESEARCH VEHICLE AT MACH NUMBERS FROM 1.77 TO 4.65, Robert J. Keynton and Ann B. Fichter, April 1961 TND 822 TABLES OF AIRSPEED, ALTITUDES, AND MACH NUMBER BASED ON LATEST INTERNATIONAL VALUES FOR ATMOSPHERIC PROPERTIES AND PHYSICAL CONSTANTS, Sadie P. Livingston and William Gracey, August 1961 TN D 824 MEASUREMENTS OF AERODYNAMIC HEAT TRANSFER ON A 15 ° CONE- CYLINDER-FLARE CONFIGURATION IN FREE FLIGHT AT MACH NUMBERS UP TO 4.7, Charles B. Rumsey and Dorothy B. Lee, May 1961 TND 834 TRANSONIC INVESTIGATION OF AERODYNAMIC CHARACTERISTICS OF A SWEPT-WING FIGHTER-AIRPLANE MODEL WITH LEADING-EDGE DROOP IN COMBINATION WITH OUTBOARD CHORD-EXTENSIONS AND NOTCHES, Charles F. Whitcomb and Harry T. Norton, Jr., May 1961 TND 835 PRESSURE DISTRIBUTIONS AND WAVE DRAG DUE TO TWO-DIMENSIONAL FABRICATION-TYPE SURFACE ROUGHNESS ON AN OGIVE CYLINDER AT MACH NUMBERS OF 1.61 AND 2.01, K. R. Czarnecki and William J. Monta, June 1961 AERODYNAMIC CHARACTERISTICS OVER A MACH NUMBER RANGE OF 1.40 TO TND 836 2.78 OFA ROCKET-PROPELLED AIRPLANE CONFIGURATION HAVING A LOW 52.5° DELTA WING ANDAN UNSWEPT HORIZONTAL TAIL, Alan B. Kehlet, May 1961 TN D 839 AERODYNAMIC CHARACTERISTICS IN PITCHOFA SERIESOFCRUCIFORM- WING MISSILESWITHCANARD CONTROLS AT A MACH NUMBER OF 2.01, M. Leroy Spearman,May 1961 AERODYNAMIC FORCE CHARACTERISTICS OFA SERIES OF LIFTING CONE TN D 840 ANDCONE-CYLINDER CONFIGURATIONS AT A MACH NUMBER OF 6.83 ANDANGLES OFATTACK UP TO 130° , Jim A. Penland, June 1961 HOVERING FLIGHTINVESTIGATION OF TWO METHODS OF CONTROLLING TND 841 A MAN-CARRYING DUCTED-FAN VEHICLE OF THEFLYING-PLATFORM TYPE, Lysle P. Parlett, June 1961 TND 842 NORMAL-FORCE ANDHINGE-MOMENT CHARACTERISTICS AT TRANSONIC SPEEDS OF FLAP-TYPE AILERONS AT THREE SPANWISE LOCATIONS ON A 4-PERCENT-THICK SWEPTBACK-WING-BODY MODEL ANDPRESSURE- DISTRIBUTION MEASUREMENTS ONAN INBOARD AILERON,Jack F.

Runckel and Gerald Hieser, May 1961 TRANSFER OF CRYOGENIC FLUIDSBY AN EXPULSION-BAG TECHNIQUE, TN D 849 Paul J. Sirocky, April 1961 MONTE CARLO STUDIES OF GAMMA-RAY ANDNEUTRON TRANSPORT IN TN D 850 INFINITE HOMOGENEOUS MEDIA, Theodore E. Fessler and Millard L. Wohl, November1961 AN INVESTIGATION OF TRANSONIC FLOW FIELDSSURROUNDING HOTAND TN D 853 COLD SONICJETS, George Lee, April 1961 A STUDY OF LAMINAR COMPRESSIBLE VISCOUS PIPE FLOW ACCELERATED TN D 855 BY AN AXIAL BODY FORCE, WITHAPPLICATION TOMAGNETOGAS- DYNAMICS, E. Dale Martin, April 1961 CONSTANT DENSITY APPROXIMATIONS FORTHEFLOW BEHIND AXI- TND 857 SYMMETRIC SHOCK WAVES, Albert G. Munson, May 1961 UNSTEADY AERODYNAMIC FORCES ONA SLENDER BODY OF REVOLUTION TND 859 IN SUPERSONIC FLOW, ReubenBond and Barbara B. Packard, May PREDICTED SHOCK ENVELOPES ABOUT TWO TYPES OFVEHICLES AT LARGE TND 860 ANGLES OF ATTACK, George E. Kaattari, April 1961 ANAPPROXIMATE ANALYSIS OF FILM COOLING ONBLUNT BODIES BY TN D 861 GASINJECTION NEAR THESTAGNATION POINT, Byron L. Swenson, September1961 TND 862 A FLIGHTEXAMINATION OF OPERATING PROBLEMS OF V/STOLAIRCRAFT IN STOL-TYPE LANDING ANDAPPROACH, Robert C. Innis and Hervey C. Quigley, June 1961 TN D 863 A TECHNIQUE FORCRYOPUMPING HYDROGEN, Jack Grobman,June 1961 TN D 865 REGIME OF FROZEN BOUNDARY LAYERS IN STAGNATION REGION OF BLUNT REENTRY BODIES,NormanT. Grier and NormanSands, May 1961 TND 866 LUNAR TRAJECTORIES, Richard J. Weber, Werner M. Pauson, and Richard R. Burley, August 1961 TN D 868 EXPERIMENTAL INVESTIGATION OF STAGE SEPARATION AERODYNAMICS, Robert A. Wasko, May 1961 TURBULENT SKIN-FRICTION ANDHEAT-TRANSFER COEFFICIENTS FORAN TN D 869 INCLINED FLATPLATEAT HIGHHYPERSONIC SPEEDS IN TERMS OF FREE- STREAM FLOW PROPERTIES, JamesF. Schmidt, May 1961 TN D 870 A COOLED-TUBE PYROMETER WITHEXPERIMENTAL RESULTS OBTAINED IN A HIGH-TEMPERATURE GASSTREAM, George E. Glawe, Robert C.

Johnson, and Lloyd N. Krause, August 1961 TN D 873 RADIALFLUXORFIELD OF AN ISOTROPIC, CYLINDRICAL SOURCE OF FINITE EXTENT, Edmund E. Callaghan and Lawrence Flax, July 1961 TND 875 HEATTRANSFER TO AN ELECTRICALLY CONDUCTING FLUIDFLOWING IN A CHANNEL WITHA TRANSVERSE MAGNETIC FIELD, Morris Perlmutter and Robert Siegel, August 1961 TN D 877 AN EXPERIMENTAL INVESTIGATION OF A FLOW MODULATOR USING A PIEZOELECTRIC CRYSTAL AS THEDRIVINGELEMENT, Leon M. Wenzel, July 1961 TN D 880 GROUND MEASUREMENTS OFTHESHOCK-WAVE NOISEFROM SUPERSONIC BOMBER AIRPLANES IN THEALTITUDE RANGE FROM 30,000 TO 50,000 FEET, DomenicJ. Maglieri and Harvey H. Hubbard, July 1961 TN D 881 AN INVESTIGATION OFTHEINFLUENCE OFLIFT ONSONIC-BOOM INTEN- SITY BYMEANS OFWIND-TUNNEL MEASUREMENTS OF THEPRESSURE FIELDSOF SEVERAL WING-BODY COMBINATIONS AT A MACH NUMBER OF 2.01, Harry W. Carlson, July 1961 TN D 883 ANALYTICAL EVALUATION OF A METHOD OF MIDCOURSE GUIDANCE FOR RENDEZVOUS WITHEARTH SATELLITES, John M. Eggleston and Robert S. Dunning, June 1961 TND 884 ANALOG-COMPUTER INVESTIGATION OF EFFECTS OF FRICTION ANDPRE- LOAD ONTHEDYNAMIC LONGITUDINAL CHARACTERISTICS OF A PILOT- AIRPLANE COMBINATION, Harold L. Crane, May 1961 TN D 885 STUDY OFA SOLAR SENSOR FORUSEIN SPACE-VEHICLE ORIENTATION CONTROL SYSTEMS, Paul R. Spencer, June 1961 TND 886 THEORY OFAN ELECTROMAGNETIC MASS ACCELERATOR FORACHIEVEING HYPERVELOCITIES, Karlheinz Thomand Joseph Norwood, Jr., June 1961 TND 888 MEASUREMENTS OFAERODYNAMIC HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONA 15° CONE IN FREEFLIGHTAT SUPERSONIC MACH NUMBERS UP TO 5.2, Charles B. Rumseyand Dorothy B. Lee, August 1961 FREE-FLIGHT AERODYNAMIC-HEATING DATATOMACH NUMBER 10.4 TND 889 FORA MODIFIED VONKARMAN NOSE SHAPE, William M. Bland, Jr.

and Katherine A. Collie, May 1961 TND 890 SIMPLE FORMULAS FORSTAGNATION-POINT CONVECTIVE HEATLOADS IN LUNAR RETURN, Frederick C. Grant, July 1961 TND 891 LAMINAR HEAT-TRANSFER ANDPRESSURE-DISTRIBUTION STUDIES ONA SERIES OF REENTRY NOSE SHAPES AT A MACH NUMBER OF 19.4 IN HELIUM,Richard D. Wagner, Jr., W. Clint Pine, and Arthur Henderson, Jr., June 1961 TND 894 INVESTIGATION OF LOW-SUBSONIC FLIGHTCHARACTERISTICS OFA MODEL OF A HYPERSONIC BOOST-GLIDE CONFIGURATION HAVING A 78° DELTA WING,John W. Paulson and Robert E. Shanks, May 1961 APPROXIMATE TEMPERATURE DISTRIBUTIONS ANDSTREAMWISE HEAT TN D 895 CONDUCTION EFFECTS IN THETRANSIENT AERODYNAMICS HEATING OF THIN-SKINNED BODIES,Raul J. Conti, September 1961 TN D 897 EXPLORATORY ENVIRONMENTAL TESTS OF SEVERAL HEATSHIELDS, George P. Goodman and John Betts, Jr., September 1961 TND 901 AERODYNAMIC CHARACTERISTICS OF A FOUR-PROPELLER TILT-WING VTOLMODEL WITHTWINVERTICAL TAILS, INCLUDING EFFECTS OF GROUND PROXIMITY, Kalman J. Grunwald, June 1961 LOCAL AERODYNAMIC HEAT TRANSFER ANDBOUNDARY-LA_'ER TRANSI- TND 907 TION ONROUGHENED SPHERE-ELLIPSOID BODIES AT MACH NUMBER 3.0, William D. Deveikis and Robert W. Walker, August 1961 TN D 908 THEDEVELOPMENT OFAN 8-INCH BY 8-INCH SLOTTED TUNNEL FOR MACH NUMBERS UP TO 1.28, B. H. Little, Jr. and JamesM.

Cubbage, Jr., August 1961 TN D 910 MAGNETIC IGNITIONOF PULSED GASDISCHARGES IN AIR OFLOW PRESSURE IN A COAXIAL PLASMA GUN,Karlheinz Thomand JoseDh Norwood, Jr., June 1961 TN D 911 DECLINATION, RADIALDISTANCE D ANDPHASES OF THEMOON FORTHE YEARS 1961 TO 1971 FORUSEIN TRAJECTORY CONSIDERATIONS, Donald S. Woolston, August 1961 TN D 915 INVESTIGATION OF INTERFERENCE OF A DEFLECTED JET WITHFREESTREAM ANDGROUND ONAERODYNAMIC CHARACTERISTICS OFA SEMISPAN DELTA- WING VTOLMODEL, Kenneth P. Spreemann,August 1961 TN D 916 AERODYNAMIC CHARACTERISTICS AT A MACH NUMBER OF 3.10 OF SEVERAL FOURTH-STAGE SHAPES OF THESCOUT RESEARCH VEHICLE,Byron M.

Jaquet, June 1961 TN D 917 A FIXED-BASE-SIMULATOR STUDY OF THEABILITY OF A PILOTTO ESTABLISH CLOSE ORBITS AROUND THEMOON, M. J. Queijo and Donald R. Riley, June 1961 TN D 919 WIND-TUNNEL INVESTIGATION OF A BALLON ASA TOWED DECELERATOR AT MACH NUMBERS FROM 1.47 TO 2.50, John T. McSheraand J. Wayne Keyes, August 1961 TN D 922 REPEATABILITY, DRIFT, ANDAFTEREFFECT OFTHREE TYPES OF AIRCRAFT ALTIMETERS, William Gracey and Richard E. Stell, July 1961 TND 923 AN AUTOMATIC TERMINAL GUIDANCE SYSTEM FORRENDEZVOUS WITHA SATELLITE,Terrance M. Carney, August 1961 TN D 925 MEASUREMENTS ANDCALCULATIONS OF THEEFFECTS OFDISTORTIONS IN THECOLLECTOR SURFACE ONEFFICIENCIES OFUMBRELLA-TYPE SOLAR COLLECTORS, Victor R. Bond, August 1961 TN D 926 AERODYNAMIC CHARACTERISTICS OFLOW-ASPECT-RATIO WINGS IN CLOSE PROXIMITY TO THEGROUND, Marvin P. Fink and JamesL. Lastinger, July 1961 TN D 927 FREE-FLIGHT INVESTIGATION OF RADIO-CONTROLLED MODELS WITHPARA- WINGS,Donald E. Hewes, September 1961 TN D 929 EFFECTS AT MACH NUMBERS OF 1.61 AND2.01 OF CAMBER ANDTWIST ONTHEAERODYNAMIC CHARACTERISTICS OF THREE SWEPT WINGS HAVING THESAME PLANFORM, Emma Jean Landrum and K. R. Czarnecki, August 1961 TND 930 A LINEARTHEORY FORINFLATABLE PLATES OF ARBITRARY SHAPE, Harvey G. McComb, Jr., October 1961 TN D 932 BOUNDARY-LAYER TRANSITION ONA GROUP OF BLUNT NOSE SHAPES AT A MACH NUMBER OF 2.20, Mary W. Jackson and K. R. Czarnecki, July 1961 TN D 933 TABLES OF INTERFERENCE FACTORS FORUSEIN WIND-TUNNEL AND GROUND-EFFECT CALCULATIONS FORVTOL-STOL AIRCRAFT. PARTI - WINDTUNNELS HAVING WIDTH-HEIGHT RATIOOF 2.0, Harry H.

Heyson, January 1962 TN D 934 TABLES OF INTERFERENCE FACTORS FORUSEIN WIND-TUNNEL AND GROUND-EFFECT CALCULATIONS FORVTOL-STOL AIRCRAFT. PARTII - WINDTUNNELS HAVING WIDTH-HEIGHT RATIOOF 1.5, Harry H.

Heyson, January 1962 TN D 935 TABLES OF INTERFERENCE FACTORS FORUSEIN WIND-TUNNEL AND GROUND-EFFECT CALCULATIONS FORVTOL-STOL AIRCRAFT. PARTIII - WINDTUNNELS HAVING WIDTH-HEIGHT RATIOOF 1.0, Harry H.

Heyson, January 1962 TND 936 TABLES OF INTERFERENCE FACTORS FORUSEIN WIND-TUNNEL AND GROUND-EFFECT CALCULATIONS FORVTOL-STOL AIRCRAFT. PARTIV - WINDTUNNELS HAVING WIDTH-HEIGHT RATIOOF 0.5, Harry H.

Heyson, January 1962 TND 938 EFFECTS OF SOME TYPICAL GEOMETRICAL CONSTRAINTS ONLUNAR TRAJECTORIES, Robert H. Tolson, August 1961 TND 939 DESCRIPTION OFA 2-FOOT HYPERSONIC FACILITYAT THELANGLEY RESEARCH CENTER, GeorgeM. Stokes, September1961 TN D 940 LANDING CHARACTERISTICS OF A LENTICULAR-SHAPED REENTRY VEHICLE, Ulysse J. Blanchard, September 1961 TND 941 A TRANSONIC INVESTIGATION OF CHANGING INDENTATION DESIGN MACH NUMBER ONTHEAERODYNAMIC CHARACTERISTICS OFA 45° SWEPTBACK- WING-BODY COMBINATION DESIGNED FORHIGHPERFORMANCE, Donald L. Loving, October 1961 TN D 943 AERODYNAMIC CHARACTERISTICS, TEMPERATURE, ANDNOISEMEASURE- MENTS OFA LARGE-SCALE EXTERNAL-FLOW JET-AUGMENTED-FLAP MODEL WITHTURBOJET ENGINES OPERATING, Marvin P. Fink, September 1961 TN D 946 RAPID-TRANSITION TESTS OFA 1/4-SCALEMODEL OF THEVZ-2 TILT- WING AIRCRAFT, Louis P. Tosti, October 1961 TN D 947 WIND-TUNNEL TESTS OF SEVEN STATIC-PRESSURE PROBES AT TRANSONIC SPEEDS, Francis J. Capone, November1961 TND 948 A SIMULATOR STUDY OF THEEFFECTIVEN.ESS OF A PILOT'S INDICATOR WHICH COMBINED ANGLF OFATTACK ANDRATEOF CHANGE OF TOTAL PRESSURE AS APPLIED TO THETAKE-0FF ROTATION ANDCLIMBOUT OF A SUPERSONIC TRANSPORT, Albert W. Hall and Jack E. Harris, September1961 TN D 951 SUPERSONIC FREE-FLIGHT MEASUREMENT OF HEATTRANSFER ANDTRANSITION ONA I0 ° CONE HAVING A LOW TEMPERATURE RATIO, Charles F. Merlet and Charles B. Rumsey,August 1961 TN D 954 A METHOD FORLONGITUDINAL ANDLATERAL RANGE CONTROL FORA HIGH- DRAG LOW-LIFT VEHICLE ENTERING THEATMOSPHERE OFA ROTATING EARTH, John W. Young, September 1961 TN D 955 HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONA HIGHLY POLISHED HEMISPHERE-CONE IN FREEFLIGHTAT MACH NUMBERS UP TO 3.14 AND REYNOLDS NUMBERS UP TO 24 x 106, JamesJ. Buglia, September 1961 TN D 957 A STUDY OF THEEFFECT OFERRORS IN MEASUREMENT OFVELOCITY AND FLIGHT-PATH ANGLE ONTHEGUIDANCE OF A SPACE VEHICLE APPROACHING THEEARTH,Jack A. White, October 1961 TN D 958 EFFECTS OF CANARD PLANFORM ANDWING-LEADING-EDGE MODIFICATION ON LOW-SPEED LONGITUDINAL AERODYNAMIC CHARACTERISTICS OFA CANARD AIRPLANE CONFIGURATION, Bernard Spencer, Jr., August 1961 TN D 959 MEASUREMENT OF FLOW ANGULARITY AT SUPERSONIC ANDHYPERSONIC SPEEDS WITHTHEUSEOF A CONICAL PROBE, Frank E. Swalley, September 1961 TND 961 TRANSONIC WIND-TUNNEL TESTS OF AN ERROR-COMPENSATED STATIC-PRESSURE PROBE, Francis J. Capone, August 1961 TND 962 LAMINAR HEAT-TRANSFER ANDPRESSURE MEASUREMENTS AT A MACH NUMBER OF 6 ONSHARP ANDBLUNT 15° HALF-ANGLE CONES AT ANGLES OF ATTACK UP TO 90° , Raul J. Conti, October 1961 TN D 967 MEASUREMENT ANDEMPIRICAL CORRELATION OF TRANSPIRATION-COOLING PARAMETERS ONA 25° CONE IN A TURBULENT BOUNDARY LAYERIN BOTH FREE FLIGHTANDA HOT-GAS JET, ThomasE. Walton, Jr. and Bernard Rashis, October 1961 TN D 968 CHARTS DEPICTING KINEMATIC ANDHEATING PARAMETERS FORA BALLISTIC REENTRY AT SPEEDS OF 26,000 TO 45,000 FEETPERSECOND, Uriel M.

Lovelace, October 1961 TN D 969 EFFECT OFGROUNDBOARD HEIGHT ONTHEAERODYNAMIC CHARACTERISTICS OF A LIFTING CIRCULAR CYLINDER USINGTANGENTIAL BLOWING FROM SURFACE SLOTS FORLIFT GENERATION, Vernard E. Lockwood, October 1961 TN D 970 EFFECT OFGROUND PROXIMITY ONTHEAERODYNAMIC CHARACTERISTICS OF ASPECT-RATIO-I AIRFOILSWITHANDWITHOUT ENDPLATES,Arthur W.

Carter, October 1961 TN D 972 EXPERIMENTAL ANDTHEORETICAL STUDIES OF THEEFFECTS OF CAMBER AND TWISTONTHEAERODYNAMIC CHARACTERISTICS OF PARAWINGS HAVING NOMINAL ASPECT RATIOS OF 3 AND6, Edward C. Polhamusand Rodger L. Naeseth, January 1963 TN D 977 AN INVESTIGATION OFTHEEFFECT OFDOWN-WASH FROM A VTOLAIRCRAFT ANDA HELICOPTER IN THEGROUND ENVIRONMENT, ThomasC. O'Bryan, October 1961 TN D 978 INVESTIGATION OFNET-THRUST ANDBASE-PRESSURE CHARACTERISTICS OF CYLINDRICAL AFTERBODIES WITHCLUSTERED SUPERSONIC NOZZLES AT TRANSONIC MACH NUMBERS, Earl H. Andrews, Jr., November1961 TND 981 AERODYNAMIC CHARACTERISTICS OF A POWERED SEMISPAN TILTING- SHROUDED-PROPELLER VTOLMODEL IN HOVERING ANDTRANSITION FLIGHT, Kenneth W. Goodsonand Kalman J. Grunwald, January 1962 TND 982 TAKE-OFF DISTANCES OFA SUPERSONIC TRANSPORT CONFIGURATION AS AFFECTED BYAIRPLANE ROTATION DURING THETAKE-OFF RUN,Albert W. Hall, October 1961 TND 983 LOW SUBSONIC PRESSURE DISTRIBUTIONS ONTHREE RIGID WINGS SIMULATING PARAGLIDERS WITHVARIED CANOPY CURVATURE AND LEADING-EDGE SWEEP, Paul G. Fournier and B. Ann Bell, November TN D 984 AERODYNAMIC EFFECTS OF SOME CONFIGURATION VARIABLES ONTHE AEROELASTIC CHARACTERISTICS OF LIFTING SURFACES AT MACH NUMBERS FROM 0.7 TO 6.86, Perry W. Hanson, November1961 TN D 985 WIND-TUNNEL INVESTIGATION OF PARAGLIDER MODELS AT SUPERSONIC SPEEDS, Robert T. Taylor, November1961 TN D 988 FREE-FLIGHT INVESTIGATION OF HEATTRANSFER TO ANUNSWEPT CYLINDER SUBJECTED TO AN INCIDENT SHOCK ANDFLOW INTERFERENCE FROM AN UPSTREAM BODY AT MACH NUMBERS UP TO 5.50, HowardS.

Carter and Robert E. Carr, October 1961 TN D 989 SUMMARY OF FLIGHT-TEST RESULTS OF THEVZ-2 TILT-WINGAIRCRAFT, Robert J. Pegg, February 1962 TN D 992 STUDY OF FLOW OVER OSCILLATING AIRFOILMODELS AT A MACH NUMBER OF 7.0 IN HELIUM,Ali Arman, December1961 TN D 994 AERODYNAMIC CHARACTERISTICS OF TOWED CONES USED AS DECELERATORS AT MACH NUMBERS FROM 1.57 TO 4.65, Nickolai Charczenko and John T. McShera, December1961 EXPLORATORY TESTS OF THEEFFECTS OF JET PLUMES ONTHEFLOW OVER TND i000 CONE-CYLINDER FLARE BODIES,Ralph A. Falanga, William F. Hinson, and Davis H. Crawford, February 1962 TN D 1002 AERODYNAMIC CHARACTERISTICS OF A CANARD ANDAN OUTBOARD-TAlL AIRPLANE MODEL ATHIGH SUBSONIC SPEEDS, Paul G. Fournier, November1961 TN D 1004 THEDESIGN ANDOPERATION OFA CONTINUOUS-FLOW ELECTRODELESS PLASMA ACCELERATOR, R. L. Barger, J. D. Brooks, and W. D.

Beasley, February 1962 TN D 1005 STUDY OFA PROPOSED INFRARED HORIZON SCANNER FORUSEIN SPACE- ORIENTATION CONTROL SYSTEMS, NormanM. Hatcher and Ernst F.

Germann,Jr., January 1962 TN D 1007 INVESTIGATION OFTHELOW-SUBSONIC FLIGHTCHARACTERISTICS OF A MODEL OFA REENTRY VEHICLE WITHA THICKFLAT 75° SWEPT DELTA WING ANDA HALF-CONE FUSELAGE, Peter C. Boisseau, February TN D 1009 TRANSONIC PRESSURE DISTRIBUTIONS ONTHREE RIGID WINGS SIMULATING PARAGLIDERS WITHVARIED CANOPY CURVATURE AND LEADING-EDGE SWEEP, Paul G. Fournier and B. Ann Bell, January TN D i010 STATISTICS OF SOLAR COSMIC RAYS AS INFERRED FROM CORRELATION WITHINTENSE GEOMAGNETIC STORMS, David Adamsonand Robert E.

Davidson, February 1962 TN D i011 AN INVESTIGATION OF PERIODIC FORCES ANDMOMENTS TRANSMITTED TO THEHUBOF FOUR LIFTINGROTOR CONFIGURATIONS, Milton A. Silveira, March 1962 TN D 1013 THEMAGNETIC FIELD ONTHEAXIS OF CIRCULAR CYLINDRICAL COILS, David E. Morris and Robert A. Kilgore, April 1962 TND 1014 EXPERIMENTAL SEPARATION STUDIES FORTWO-DIMENSIONAL WEDGES AND CURVED SURFACES AT MACH NUMBERS OF 4.8 TO 6.2, JamesR. Sterrett and JamesC. Emery, February 1962 TN D 1015 THEORETICAL EVALUATION OF HYPERSONIC FORCES, MOMENTS, ANDSTABILITY DERIVATIVES FORCOMBINATIONS OF FLATPLATES,INCLUDING EFFECTS OF BLUNT LEADING EDGES, BYNEWTONIAN IMPACT THEORY, Walter B. Olstad, March 1962 TN D 1016 JET EFFECTS ONCYLINDRICAL AFTERBODIES HOUSING SONIC ANDSUPERSONIC NOZZLES WHICH EXHAUST AGAINST A SUPERSONIC STREAM AT ANGLES OF ATTACK FROM 90 ° TO 180 ° , Lovic O. Hayman, Jr. and Russel W.

McDearmon, March 1962 TN D 1017 AN EXPLORATORY INVESTIGATION OF JET-BLAST EFFECTS ON A DUST- COVERED SURFACE AT LOW AMBIENT PRESSURE, Amos A. Spady, Jr., February 1962 TN D 1019 GEOMAGNETIC-AND INTERPLANETARY-MAGNETIC-FIELD ENVIRONMENT OF AN EARTH SATELLITE, Edward W. Leyhe, July 1962 TN D 1020 FURTHER DEVELOPMENTS ON THE REQUIRED NUMBER OF RANDOMLY SPACED COMMUNICATION AND NAVIGATION SATELLITES, Floyd V. Bennett, February 1962 TN D 1022 A STUDY OF THE AERODYNAMIC CHARACTERISTICS OF A FIXED GEOMETRY PARAGLIDER CONFIGURATION AND THREE CANOPIES WITH SIMULATED VARIABLE CANOPY INFLATION AT A MACH NUMBER OF 6.6, Jim A.

Penland, March 1962 TN D i024 MEASURED SURFACE DEFECTS ON TYPICAL TRANSONIC AIRPLANES AND ANALYSIS OF THEIR DRAG CONTRIBUTION, Elmer A° Horton and Neal Tetervin, October 1962 TN D 1025 RECEIVING SYSTEM DESIGN FOR THE ARRAYING OF INDEPENDENTLY STEERABLE ANTENNAS FOR DEEP SPACE COMMUNICATIONS, James H.

Schrader, April 1962 TN D 1026 WIND-TUNNEL TESTS OF AI/20-SCALE AIRSHIP MODEL WITH STERN PROPELLERS, H. Clyde McLemore, January 1962 TN D 1028 CHARACTERISTICS OF THREE PRECISION CIRCUMLUNAR TRAJECTORIES FOR THE YEAR 1968, John P. Gapcynski and Donald S. Woolston, March 1962 TN D 1029 A STUDY OF THE OPTIMUM VELOCITY CHANGE TO INTERCEPT AND RENDEZVOUS, John M. Eggleston, February 1962 TN D 1031 RADIATION EMISSION EFFECTS OF THE EQUILIBRIUM BOUNDARY LAYER IN THE STAGNATION REGION, John Thomas Howe, September 1961 TN D 1032 STOL CHARACTERISTICS OF A PROPELLER-DRIVEN, ASPECT-RATIO-10, STRAIGHT-WING AIRPLANE WITH BOUNDARY-LAYER CONTROL FLAPS, AS ESTIMATED FROM LARGE-SCALE WIND-TUNNEL TESTS, James A. Weiberg and Curt A. Holzhauser, June 1961 TN D 1034 LARGE-SCALE WIND-TUNNEL TESTS OF AN AIRPLANE MODEL WITH AN UNSWEPT, TILT WING OF ASPECT RATIO 5.5, AND WITH FOUR PROPEL- LERS AND BLOWING FLAPS, James A. Weiberg and Curt A. Holzhauser, June 1961 TWO INSTRUMENTS FOR MEASURED DISTRIBUTIONS OF LOW-ENERGY TN D 1035 CHARGED PARTICLES IN SPACE, Michel Bader, Thomas B. Fryer, and Fred Witteborn, July 1961 TN D 1037 THE USE OF DRAG MODULATION TO LIMIT THE RATE AT WHICH DECELERA- TION INCREASES DURING NONLIFTING ENTRY, Lionel L. Levy, Jr., September 1961 TN D 1038 VELOCITY REQUIREMENTS FOR ABORT FROM THE BOOST TRAJECTORY OF A MANNED LUNAR MISSION, Robert E. Slye, July 1961 TN D 1041 ONTHELONG PERIOD LUNI-SOLAR EFFECT IN THEMOTION OF AN ARTIFICIAL SATELLITE,Peter Musen, July 1961 TND 1042 DENSITY IN A PLANETARY EXOSPHERE, Jackson Herring and Herbert L. Kyle, July 1961 TND 1043 SPORADIC-E AS OBSERVED WITHROCKETS, J. Carl Seddon, July 1961 TN D 1044 THEDEVELOPMENT OFTHEELECTRIC FIELDMETER FORTHEEXPLORER VIII SATELLITE(1960_), ThomasW. Flatley and Harold E. Evans, April 1962 TN D 1045 EARTH OBLATENESS ANDRELATIVE SUNMOTION CONSIDERATIONS IN THE DETERMINATION OFAN IDEALORBITFORTHENIMBUS METEOROLOGICAL SATELLITE,William R. Bandeen, July 1961 TN D 1047 RECOVERY TEMPERATURE, TRANSITION, ANDHEAT-TRANSFER MEASURE- MENTS AT MACH 5, Paul F. Brinich, August 1961 TN D 1050 ESTIMATE OF SHOCK STANDOFF DISTANCE AHEAD OFA GENERAL STAGNA- TION POINT, Eli Reshotko, August 1961 TN D 1051 APPLICABILITY OF MIXINGLENGTH THEORY TOA TURBULENT VORTEX SYSTEM, Robert G. Ragsdale, August 1961 TN D 1054 A TECHNIQUE FORINCREASING THESENSITIVITYOFA SOLID-STATE FISSIONPROBE, Robert Steinberg, August 1961 TN D 1055 THENEUTRALIZATION OF ION-ROCKET BEAMS, Harold R. Kaufman, August 1961 TN D 1056 PRELIMINARY BASEPRESSURES OBTAINED FROM THEX-15 AIRPLANE AT MACH NUMBERS FROM i.i TO 3.2, Edwin J. Saltzman, August 1961 TND 1057 ANALYSIS OF X-15 LANDING APPROACH ANDFLARE CHARACTERISTICS DETERMINED FROM THEFIRST 30 FLIGHTS,GeneJ. Matranga, July TND 1060 AERODYNAMIC-DERIVATIVE CHARACTERISTICS OF THEX-15 RESEARCH AIRPLANE AS TETERMINED FROM FLIGHTTESTS FORMACH NUMBERS FROM 0.6 TO 3.4, RoxanahB. Yancey, HermanA. Rediess, and Glen H. Robinson, APPENDIX A. APPROXIMATE EQUATIONS FOR DETERMINING CnB ' CtB ' AND (Cnr - CnB), Chester H. Wolow±cz, January 1962 TND 1061 GODDARD SPACE FLIGHT CENTER CONTRIBUTION TO THE 1961 KYOTO CONFERENCE ON COSMIC RAYS AND THE EARTH STORM, June 1962 TN D 1062 A DIGITAL SOLAR ASPECT SENSOR, James S. Albus, September 1961 THEEFFECT OF SOLAR RADIATION PRESSURE ONTHEMOTION OFAN TND 1063 ARTIFICIAL SATELLITE,Robert W. Bryant, September 1961 MEASUREMENTS OF SHEATH CURRENTS ANDEQUILIBRIUM POTENTIAL ON TND 1064 THEEXPLORER VIII SATELLITE (1960 ._), R. E. Bourdeau, J. L.

Donley, G. P. Serbu, and E. C. Whipple, Jr., July 1961 ONTHEELECTRON DENSITY DISTRIBUTION ABOVE THEF2 PEAK,S. J.

TND 1065 Bauer, July 1961 TRANSITION OF THELAMINAR BOUNDARY LAYER ONA DELTA WING WITH TN D 1066 74° SWEEP IN FREEFLIGHTAT MACH NUMBERS FROM 2.8 TO 5.3, Gary T. Chapman,August 1961 EFFECTS OF FLIGHTCONDITIONS AT BOOSTER SEPARATION ONPAYLOAD TND 1069 WEIGHT IN ORBIT,Richard D. Nelson, November1961 TN D 1071 EFFECTS OFMACH NUMBER, LEADING-EDGE BLUNTNESS, ANDSWEEP ON BOUNDARY-LAYER TRANSITION ONA FLATPLATE,Don W. Jillie and Edward J. Hopkins, September 1961 HEAT IRANSFER AT THEREATTACHMENT ZONE OF SEPARATED LAMINAR TN D 1072 BOUNDARY LAYERS, Paul M. Chungand John R. Viegas, September RADIATIVE HEATTRANSFER DURING ATMOSPHERE ENTRY AT PARABOLIC TN D 1074 VELOCITY, Kenneth K. Yoshikawa and Bradford H. Wick, November SOME EFFECTS OF LEADING-EDGE SWEEP ONBOUNDARY-LAYER TRANSITION TN D 1075 AT SUPERSONIC SPEEDS, Gary T. Chapman,September1961 INVESTIGATION OF MONOPOLE ANTENNA SYSTEMS FORUSEONTHENASA TN D 1077 ATMOSPHERIC STRUCTURE SATELLITE,Roland R. Ford and Louis F.

Schmadebeck,February 1962 FOURIER SERIES OPERATING PACKAGE, Milton L. Charnow, December TN D 1078 IONOSPHERIC RESULTS WITHSOUNDING ROCKETS ANDTHEEXPLORER VIII TND 1079 SATELLITE(1960 _), R. E. Bourdeau, August 1961 SIGNAL CONDITIONING FORSATELLITE BORNE ENERGETIC-CHARGED- TN D 1080 PARTICLE EXPERIMENTS, George H. Ludwig, August 1961 PRELIMINARY SURVEY OF RETROGRADE VELOCITIES REQUIRED FORINSER- TN D 1081 TION INTOLOW-ALTITUDE LUNAR ORBITS,Morris V. Jenkins and Robert E. Munford, September 1961 PHYSIOLOGICAL SENSORS FORUSEIN PROJECT MERCURY, Charles D.

TN D 1082 Wheelwright, August 1962 TN D 1083 DEVELOPMENT OF INFLATABLE COMPONENTS OF PERSONAL EQUIPMENT FOR ASTRONAUT BODY INSTRUMENTATION ANDSURVIVAL AT SEA, Matthew I. Radnofsky and Joseph J. Kosmo, January 1963 TND 1085 EQUATIONS FORTHENEWTONIAN STATICANDDYNAMIC AERODYNAMIC COEFFICIENTS FORA BODY OF REVOLUTION WITHAN OFFSET CENTER- OF-GRAVITY LOCATION, Robert C. Ried, Jr. and Edward E. Mayo, June 1963 TN D 1089 THEELECTROCHEMICAL FLUORINATION OF ORGANOSILICON COMPOUNDS, Robert E. Seaver, September1961 TN D 1090 EFFECT OF SURFACE PREPARATION ANDGASFLOW ONNITROGEN ATOM SURFACE RECOMBINATION, GeorgeM. Prok, September1961 TN D 1091 FLIGHT-PATH CHARACTERISTICS FORDECELERATING FROM SUPER- CIRCULAR SPEED, Roger W. Luidens, December1961 TN D 1092 AN INPUTROUTINE USINGARITHMETIC STATEMENTS FORTHEIBM 704 DIGITALCOMPUTER, Don N. Turner and Vearl N. Huff, September TN D 1093 BASEFLOW CHARACTERISTICS FORSEVERAL FOUR-CLUSTERED ROCKET CONFIGURATIONS AT MACH NUMBERS FROM 2.0 TO 3.5, NormanT.

Musial and JamesJ. Ward, December1961 TN D 1095 INTERACTION OF HIGHLY UNDEREXPANDED JETSWITHSIMULATED LUNAR SURFACES, Leonard E. Stitt, December1961 TN D 1096 INFRARED ANDREFLECTED SOLAR RADIATION MEASUREMENTS FROM THE TIROSII METEOROLOGICAL SATELLITE,W. R. Bandeen, R. A.

Hanel, John Licht, R. A. Stampfl, and W. G. Stroud, November TN D 1097 SCANNING MECHANISM FORA SATELLITE BORNE X-RAYSPECTROMETER, Gerald L. Hempfling, November1962 TN D 1098 THESIMULTANEOUS MEASUREMENT OF IONOSPHERIC ELECTRON DENSI- TIES BY CW PROPAGATION ANDRF IMPEDANCE PROBE TECHNIQUES, J. A. Kane, J. E. Jackson, and H. A. Whale, January 1962 TN D 1099 EARTH REFLECTED SOLAR RADIATION INPUTTO SPHERICAL SATELEITES, F. G. Cunningham,October 1961 TN D iiii A MATHEMATICAL TREATMENT OF THEPROBLEM OFDETERMINING THE EIGENVALUES ASSOCIATED WITHA PARTITION FUNCTION OF AN ATOM IN THEINTERIOR OFA PLASMA, E. Baylis Shanks, October 1963 TND 1112 A RECURSION RELATION ASSOCIATED WITHA CERTAIN SPECIAL TYPE DETERMINANT, E. Baylis Shanks, April 1963 TN D 1113 SPUTTERING OF A VEHICLE'S SURFACE IN A SPACE ENVIRONMENT, Jerome R. Redus, June 1962 DETERMINING INERTIAS BY USING THE AMPLITUDE DECAY RATE OF A TN D 1114 MECHANICAL OSCILLATING SYSTEM, Gene T. Carpenter and Dan T.

Meredith, May 1962 NUCLEAR RADIATION TRANSFER AND HEAT DEPOSITION RATES IN LIQUID TN D 1115 HYDROGEN, M. O. Burrell, August 1962 TN D 1116 THE RESULTS OF EMITTANCE MEASUREMENTS MADE IN RELATION TO THE THERMAL DESIGN OF EXPLORER SPACECRAFT, Ronald Merrill, William Snoddy, and Klaus Schocken, May 1962 SATURN VEHICLE ATTITUDE RESOLVER COMPUTER ERROR ANALYSIS, TN D 1119 Herman E. Thomason, September 1962 SUN TRACKING BY THE MINITRACK NETWORK STATIONS, E. J. Habib, TN D 1121 J. H. Berbert, and D. W. Harris, March 1962 TRACKING OF CYGNUS A AND CASSIOPEIA A BY THE NASA 108-MC TN D 1122 MINITRACK SYSTEM, E. J. Habib, J. H. Berbert, and D. W.

Harris, March 1962 TN D 1123 ROCKET M_ASUREMENTS OF THE UPPER IONOSPHERE BY A RADIO PRO- PAGATION TECHNIQUE, S. J. Bauer and J. E. Jackson, July 1961 A COMPARISON OF THEORY AND OBSERVATION OF THE ECHO I SATELLITE, TN D 1124 R. W. Bryant, December 1961 THE PROBLEM OF NITROGEN PEROXIDE IN THE ATMOSPHERES OF PLANETS, TN D 1125 Su-Shu Huang, January 1962 A DEVELOPMENT OF THE LUNAR AND SOLAR DISTURBING FUNCTIONS FOR TN D 1126 A CLOSE SATELLITE, William M. Kaula, January 1962 PARTICIPATION OF BELL TELEPHONE LABORATORIES IN PROJECT ECHO TN D 1127 AND EXPERIMENTAL RESULTS, William C. Jakes, Jr., December 1961 TN D 1128 PROJECT ECHO - SYSTEM CALCULATIONS, Clyde L. Ruthroff and William C. Jakes, Jr., November 1961 TN D 1129 PROJECT ECHO - 960-MEGACYCLE, IO-KILOWATT TRANSMITTER, J. P.

Schafer and R. H. Brandt, October 1961 TN D 1130 PROJECT ECHO - RECEIVING SYSTEM, E. A. Ohm, December 1961 PROJECT ECHO - HORN-REFLECTOR ANTENNA FOR SPACE COMMUNICATION, TN D 1131 A. B. Crawford, D. C. Hogg, and L. E. Hunt, December 1961 PROJECT ECHO - THEDUALCHANNEL 2390-MCTRAVELING - WAVE MASER, TN D 1132 R. W. DeGrasse, J. J. Kostelnick, and H. E. C. Scovil, December PROJECT ECHO - STANDBY RECEIVER SYSTEM, L. U. Kibler, December TND 1133 PROJECT ECHO - FMDEMODULATORS WITHNEGATIVE FEEDBACK, Clyde L.

TND 1134 Ruthroff, October 1961 PROJECT ECHO - SATELLITE-TRACKING RADAR,E. De Lange, November TN D 1135 PROJECT ECHO - 961-Mc LOWER-SIDEBAND UP-CONVERTER FORSATELLITE- TN D 1136 TRACKING RADAR, M. Uenohara and H. Seidel, December1961 PROJECT ECHO - BORESIGHT CAMERAS FORRECORDING ANTENNA POINTING TN D 1138 ACCURACY, K. L. Warthman, September 1961 TN D 1139 SOLAR PROTONS, Keith W. Ogilvie, July 1962 VELOCITY MODIFICATION FOREARTH CAPTURE OFAN ASTRONOMICAL BODY TN D 1140 IN THESOLAR SYSTEM, Su-Shu Huang, December1961 POINTRETURN FROM A LUNAR MISSIONFORA VEHICLE THATMANEUVERS TN D 1142 WITHINTHEEARTH'S ATMOSPHERE, SimonC. Sommer and Barbara J.

Short, November1961 TN D 1144 AN ACCELERATED RESERVOIR LIGHT-GAS GUN,John S. Curtis, February 1962 TN D 1145 ATMOSHERE ENTRIES WITHVEHICLE LIFT-DRAG RATIOMODULATED TO LIMIT DECELERATION ANDRATEOF DECELERATION - VEHICLES WITH MAXIMUM LIFT-DRAG RATIOOF 0.5, Elliott D. Katzen and Lionel L. Levy, Jr., December1961 TN D 1146 EFFECTS OF SURFACE RECOMBINATION ONHEATTRANSFER TO BODIES IN A HIGHENTHALPY STREAM OF PARTIALLY DISSOCIATED NITROGEN, Ernest L. Winkler and Roy N. Griffin, Jr., December1961 TN D 1147 CALCULATION OF FLOW FIELDSFROM BOW-WAVE PROFILES FORTHE DOWNSTREAM REGION OF BLUNT-NOSED CIRCULAR CYLINDERS IN AXIAL HYPERSONIC FLIGHT,Alvin Seiff and Ellis E. Whiting, November1961 A CORRELATION STUDY OF THEBOW-WAVE PROFILES OF BLUNT BODIES, TN D 1148 Alvin Seiff and Ellis E.Whiting, February 1962 NEW INVESTIGATIONS OF THEALLEGED METEORITE FROM IGAST, TN D 1151 ESTONIA,John A. O'Keefe and Paul D. Lowman,Jr., December TND 1152 THETIROSII RADIATION EXPERIMENT, R. A. Hanel and W. G. Stroud, October 1961 TND 1153 STAR CATALOGS ONPUNCHED CARDS ANDMAGNETIC TAPE, J. H. Berbert, December1961 TN D 1154 INTERPLANETARY DUST PARTICLES OF MICRON SIZE PROBABLY ASSOCIATED WITHTHELEONID METEOR STREAM, W. M. Alexander, C. W. McCracken, and H. E. LaGow,December1961 TN D 1155 CELESTIAL GEODESY, W. M. Kaula, March 1962 TN D 1159 MISSION PLANNING ANDOPERATIONAL PROCEDURES FORTHEX-15 AIR- PLANE,Robert G. Hoey and Richard E. Day, March 1962 TN D 1164 POTENTIAL FLOW ANALYSIS OFUNSTEADY OUT-FLOW FROM A TANKAND ITS EFFECT ONTHEDYNAMICS OF A FLUIDSYSTEM, William H.

Roudebushand I. Irving Pinkel, June 1962 TN D 1165 ANALYSIS OF HEATTRANSFER ANDPRESSURE DROP FORA GASFLOWING THROUGH A SETOFMULTIPLE PARALLEL FLATPLATES AT HIGHTEMPERA- TURES, ThomasH. Einstein, December1961 TN D 1169 CALIBRATION TECHNIQUES IN AN ARC-HEATED, HYPERSONIC, LOW- DENSITY WINDTUNNEL, Ruth N. Weltmann, August 1962 TN D ii/0 INVESTIGATION OF THEPERFORMANCE OF A 78° FLAT-PLATE HELICAL INDUCER, Richard F. Soltis, Douglas A. Anderson, and Donald M. Sandercock, March 1962 TN D 1171 ONTHEELECTRON DENSITY DISTRIBUTION ABOVE THEF2 PEAK(REVISED), S. J. Bauer, January 1962 TN D 1172 A TIME SHARING SWITCH FORSPACECRAFT TELEMETRY SYSTEMS, William A. Leavy, March 1962 TN D 1173 THENASA PROGRAM FORPARTICLES ANDFIELDSRESEARCH IN SPACE, George H. Ludwig, April 1962 TN D 1174 DIRECT MEASUREMENTS OF INTERPLANETARY DUST PARTICLES IN THE VICINITY OF EARTH, C. W. McCracken, W. M. Alexander, and M.

Dubin, December1961 TN D 1176 THETHERMOELECTRIC POWER OF SEMICONDUCTORS, F. E. Geiger, Jr., May 1962 TN D 1177 COMPUTATIONAL PROCEDURE FORVINTI'S THEORY OFAN ACCURATE INTERMEDIARY ORBIT, N. L. Bonavito, March 1962 ANALYSIS OF THE"RANGE ANDRANGE RATE"TRACKING SYSTEM, F. O.

TND 1178 Vonbun, February 1962 LONG PERIOD EFFECTS OF THEELLIPTICITY OFTHEEARTH'S EQUATOR TN D 1179 ONTHEMOTION OFARTIFICIAL SATELLITES, Peter Musen, May 1962 TN D 1180 CERAMIC VACUUM ULTRAVIOLET CHAMBERS, Alfred K. Stober, March TN D 1183 A STUDY OF GUIDANCE SENSITIVITYFORVARIOUS LOW-THRUST TRANSFERS FROM EARTH TOMARS,Alan L. Friedlander, February A MONTE CARLO STUDY OF RESONANCE ESCAPE PROBABILITY IN TN D 1184 HETEROGENEOUS SLABLATTICES CONTAINING RESONANT ABSORBERS AND SCATTERERS, Harold Schneider, Leo Levitt, and Kevin J. Sroub, April 1962 SOME THEORETICAL BASES FORSELECTION OFMOLECULARION PROPELLANTS TN D 1185 ANDA SURVEY OFMOLECULAR PLASMA COLLISION PROCESSES, John V.

Dugan, Jr., February 1964 TN D 1186 INCOMPRESSIBLE NONVISCOUS BLADE-TO-BLADE FLOW THROUGH A PUMP ROTOR WITHSPLITTER VANES,JamesJ. Kramer, Norbert O. Stockman, and Ralph J. Bean, April 1962 TN D 1187 EVALUATION OFAHOLLOW, CYLINDRICAL, CONTACT-ION SOURCE, J.

ThomasKotnik, February 1962 GOVERNMENT-INDUSTRY CONFERENCE ONMERCURY CONDENSING, APRIL 18, TN D 1188 1961, PASADENA, CALIFORNIA, February 1962 TND 1189 AN EMPIRICAL RELATION FORPREDICTING VOID FRACTION WITHTWO- PHASE,STREAM-WATER FLOW,UweH. von Glahn, January 1962 A STUDY OF THEEFFECT OFMULTI-GACCELERATIONS ONNUCLEATE- TN D 1196 BOILINGEBULLITION,Robert W. Grahamand Robert C. Hendricks, May 1963 EXPERIMENTAL STUDY OF THEEFFECTS OF WEIGHTLESSNESS ONTHE TN D 1197 CONFIGURATION OF MERCURY ANDALCOHOL IN SPHERICAL TANKS, Donald A. Petrash, Robert F. Zappa, and EdwardW. Otto, April 1962 THREE-DIMENSIONAL SPHERE-OF-INFLUENCE ANALYSIS OF INTER- TN D 1.].99 PLANETARY TRAJECTORIES TO MARS,Gerald Knip, Jr. and Charles L. Zola, May 1962 TND 1203 FORCES ANDMOMENTS ONSPHERE-CONE BODIES IN NEWTONIAN FLOW, Robert R. Dickey, December1961 TND 1205 THEPERFORMANCE OF ABLATIVE MATERIALS IN A HIGH-ENERGY, PARTIALLY DISSOCIATED, FROZEN NITROGEN STREAM, Nick S.

Vojvodich, May 1962 TND 1206 A METHOD FORCALCULATING THEGENERALIZED AERODYNAMIC FORCES ONRECTANGULAR WINGS DEFORMING SYMMETRICALLY IN SUPERSONIC FLIGHTWITHINDICIAL ORSINUSOIDAL TIME DEPENDENCE, Reuben Bond, Barbara B. Packard, Robert W. Warner, and Audrey L.

Summers,March 1962 TN D 1207 ANANALYTICAL STUDY OFORBITAL RENDEZVOUS FORLEASTFUELAND LEASTENERGY, Harold Hornby, March 1962 TN D 1208 OPTIMAL FILTERING ANDLINEARPREDICTION APPLIED TO A MIDCOURSE NAVIGATION SYSTEM FORTHECIRCUMLUNAR MISSION,John D. McLean, Stanley F. Schmidt, and Leonard A. McGee,March 1962 TN D 1209 ANALYSIS OF SOLAR-RADIATION SHIELDS FORTEMPERATURE CONTROL OF SPACE VEHICLES SUBJECTED TO LARGE CHANGES IN SOLAR ENERGY, GeorgeJ. Nothwang, John C. Arvesen, and Frank M. Hamaker, March 1962 TND 1210 MEASUREMENTS OFMOMENTUM TRANSFER FROM PLASTICPROJECTILES TO MASSIVE ALUMINUM TARGETS AT SPEEDS UP TO 25,600 FEETPER SECOND, B. Pat Denardo, March 1962 TND 1216 STUDY OF SINUSOIDALLY PERTURBED FLOW IN A LINE INCLUDING A 90° ELBOW WITHFLEXIBLESUPPORTS, Robert J. Blade, William Lewis, and Jack H. Goodykoontz, July 1962 TN D 1218 MEASUREMENTS OF FLOW DURATION IN A LOW-PRESSURE SHOCK TUBE, Virgil A. Sandborn, May 1962 TND 1222 ELECTRODE CONFIGURATIONS FOR A WIND-TUNNEL HEATER INCORPORATING THEMAGNETICALLY SPUN ELECTRIC ARC, Donald R. Boldman, Charles E. Shepard, and John C. Fakan, April 1962 TND 1225 VELOCITY POTENTIAL ANDFORCES ONOSCILLATING SLENDER BODIES OF REVOLUTION IN SUPERSONIC FLOW EXPANDED TO THEFIFTHPOWER OF THEFREQUENCY, Donald L. Lansing, April 1962 TND 1226 FEASIBILITYSTUDY OF A CIRCUMLUNAR PHOTOGRAPHIC EXPERIMENT, William H. Michael, Jr., Robert H. Tolson, and John P. Gapcynski, May 1962 TND 1227 A BRIEFEVALUATION OF HELICOPTER WAKE ASA POTENTIAL OPERATIONAL HAZARD TOAIRCRAFT, Andrew B. Connor and ThomasC. O'Bryan, March 1962 TN D 1228 INVESTIGATION OFTHESTATICLONGITUDINAL AERODYNAMIC CHARAC- TERISTICS OFA 1/10-SCALEMODEL OF THEBLUESCOUT JR. AT MACH NUMBERS FROM 0.40 to 1.03, ThomasC. Kelly and Robert J.

Keynton, April 1962 TN D 1230 ANALYSIS OF TWO THRUSTING TECHNIQUES FORSOFTLUNAR LANDINGS STARTING FROM A 50-MILE ALTITUDE CIRCULAR ORBIT,M. J. Queijo and G. Kimball Miller, Jr., March 1962 TN D 1232 STATIC AERODYNAMIC CHARACTERISTICS OF A TWO-STAGE ANDA THREE- STAGE ROCKET VEHICLE AT MACH NUMBERS FROM 1.47 TO 4.63, Clarence A. Brown, Jr. and Ausley B. Carraway, April 1962 TN D 1234 FORCE-TEST INVESTIGATION OF A MODEL OF ANAERIALVEHICLE SUPPORTED BY FOUR UNSHROUDED PROPELLERS, Robert H. Kirby, April 1962 TN D 1235 FLIGHT-TEST INVESTIGATION OF A MODEL OF ANAERIALVEHICLE SUPPORTED BY FOUR UNSHROUDED PROPELLERS, Robert H. Kirby, April 1962 TN D 1236 EXPERIMENTAL INVESTIGATION OF OSCILLATORY AERODYNAMIC FORCES, MOMENTS, ANDPRESSURES ACTING ONA TAPERED WING OSCILLATING IN PITCHAT MACH NUMBERS FROM 0.40 TO 1.07, SumnerA. Leadbetter, Sherman A. Clevenson, and William B. Igoe, April 1962 TND 1237 EXPERIMENTAL OBSERVATIONS OFAERODYNAMIC ANDHEATING TESTS ON INSULATING HEATSHIELDS, Melvin S. Anderson and C. W. Stroud, March 1962 TND 1238 INVESTIGATION OF VORTEX MOVEMENTS ABOUT A WING IN INTERMEDIATE ANDHIGHSUBSONIC FLOW UNDERGOING A LARGE ANGLE-OF-ATTACK CHANGE IN A BLAST-INDUCED GUST,Donald R. McFarland, April 1962 TN D 1239 AN EXPERIMENTAL STUDY OFTHEEFFECT OF DOWNWASH FROM A TWIN- PROPELLER VTOLAIRCRAFT ONSEVERAL TYPES OF GROUND SURFACES, ThomasC. O'Bryan, May 1962 TN D 1240 NASA SCOUT ST-I FLIGHT-TEST RESULTS ANDANALYSES, LAUNCH OPERATIONS, ANDTESTVEHICLE DESCRIPTION, Robert J. Mayhue, compiler, June 1962 TND 1241 EFFECTS OF SUCTION BOUNDARY-LAYER CONTROL ONTHEPERFORMANCE OFA SHORT ANNULAR DIFFUSER WITHAN UPSTREAM TERMINAL NORMAL SHOCK, Charles J. Shoemakerand John R. Henry, April 1962 TN D 1242 THEORETICAL INVESTIGATION OF EFFECTS OF CHANGES IN COMMAND COMPUTATIONS ANDFILTERLOCATION ONRESPONSE OF AN AUTO- MATICALLY CONTROLLED INTERCEPTOR DURING THEATTACK PHASE, Windsor L. Sherman,May 1962 TN D 1244 A TABULATION OF SECTION AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS OF 1,61 AND2.01 FORFOUR SWEPT WINGS HAVING THESAME PLANFORM BUTDIFFERENT SURFACE SHAPES, Emma Jean Landrum, April 1962 TN D 1245 LOW-SPEED AERODYNAMIC CHARACTERISTICS OFA CANARD AIRPLANE CONFIGURATION HAVING SPLIT FLAPSLOCATED AHEAD OF THEWING TRAILINGEDGE ANDLEADING- ANDTRAILING-EDGE FLAPSONTHE CANARD CONTROL, Bernard Spencer, Jr., April 1962 TN D 1246 PRESSURE MEASUREMENTS ONTWO 60° SWEPT DELTA WINGS WITHBLUNT LEADING EDGES ANDDIHEDRAL ANGLES OF 0QAND45 ° AT A MACH NUMBER OF 4.95, P. Calvin Stainback, April 1962 TN D 1248 THE METEORITIC HAZARD OF THE ENVIRONMENT OF A SATELLITE, John E. Duberg, May 1962 TN D 1249 STATISTICAL WIND DISTRIBUTION DATA FOR USE AT NASA WALLOPS STATION, William L. Weaver, Andrew G. Swanson, and John F.

Spurling, July 1962 TND 1250 SUBSONIC WIND-TUNNEL INVESTIGATION OF ERRORS INDICATED BY TOTAL-PRESSURE TUBES IN THE FLOW FIELD OF A BODY SIMULATING THE NOSE OF THE X-15 RESEARCH AIRPLANE, William J. Alford, Jr., April 1962 TN D 1252 IDEAL-GAS TABLES FOR HELIUM FLOW IN THE MACH NUMBERS RANGE FROM 40 TO i00, James Mueller, May 1962 TN D 1254 PRELIMINARY STUDIES OF MANNED SATELLITE WINGLESS CONFIGURATION: NONLIFTING, Maxime A. Faget, Benjamine J. Garland, and James J.

Buglia, March 1962 TN D 1255 LOW-SPEED WIND-TUNNEL INVESTIGATION TO DETERMINE THE FLIGHT CHARACTERISTICS OF A MODEL OF A PARAWING UTILITY VEHICLE, Joseph L. Johnson, Jr., August 1962 TND 1256 HEAT TRANSFER TO 0 ° AND 75 ° SWEPT BLUNT LEADING EDGES IN FREE FLIGHT AT MACH NUMBERS FROM 1.90 TO 3.07, Robert L. O'Neal and Aleck C. Bond, April 1962 TND 1260 HEAT TRANSFER AND PRESSURE DISTRIBUTION AT A MACH NUMBER OF 6.8 ON BODIES WITH CONICAL FLARES AND EXTENSIVE FLOW SEPARATION, John V. Becker and Peter F. Korycinski, April 1962 TN D 1262 STATISTICAL STUDY OF EFFECTS OF INSERTION ERRORS ONASCENT TRAJECTORIES FORLUNAR MISSIONS,Harold A. Hamer, Carl R.

Huss, and John P. Mayer, May 1962 TN D 1264 PRESSURE DISTRIBUTIONS AT MACH NUMBER 2.05 ONA SERIES OF HIGHLYSWEPT ARROW WINGS EMPLOYING VARIOUS DEGREES OF TWIST ANDCAMBER, Harry W. Carlson, May 1962 TN D 1266 INDUCED PRESSURES ONCYLINDRICAL RODS WITHVARIOUS NOSE DRAGS ANDNOSE SHAPES AT MACH NUMBERS OF 17 AND21, Robert D. Witcofski and Arthur Henderson, Jr., May 1962 TN D 1267 CURRENT ESTIMATES OF RADIATION DOSES IN SPACE, Trutz Foelsche, July 1962 TN D 1270 THEGRAVITATIONAL FIELDENVIRONMENT OFAN EARTH SATELLITE, David Adamson,August 1962 TN D 1272 AERODYNAMIC CHARACTERISTICS IN PITCHOF SEVERAL RING-WING- BODY CONFIGURATIONS AT A MACH NUMBER OF 2.2, Odell Morris, April 1962 TN D 1273 CONCEPTUAL DESIGN STUDY OF A MULTIPURPOSE AEROSPACE TEST FACILITY, July 1962 TN D 1274 CAPE CANAVERAL WIND ANDSHEAR DATA(i THRU 80 KM) FORUSE IN VEHICLE DESIGN ANDPERFORMANCE STUDIES,JamesR. Scoggins and William W. Vaughan, July 1962 TN D 1276 GROUND FACILITYREQUIREMENTS FORSUB-COOLING LIQUID HYDROGEN, W. E. Dempsterand J. R. Olivier, July 1962 TN D 1278 REVIEW OF THEX-15 PROGRAM, Compiled by Joseph Well, June 1962 TN D 1285 AN EMPIRICAL CORRELATION OF CRITICALBOILINGHEATFLUXIN FORCED FLOW UPWARD THROUGH UNIFORMLY HEATED TUBES,UweH. yon Glahn, September1962 TN D 1287 EXPERIMENTAL INVESTIGATION OF WATER-ABSORBENT MATERIALS AS POSSIBLE HEATSINKSFORHYPERSONIC ANDREENTRY VEHICLES, Robert P. Dengler and Reeves P. Cochran, July 1962 TN D 1289 ABSORPTION ANDEMISSION CHARACTERISTICS OF DIFFUSE SPHERICAL ENCLOSURES, E. M. Sparrow and V. K. Jonsson, June 1962 TN D 1290 ANADDITIONTOTHEYALETABLES FORTHEDEVELOPMENT OF THE DISTURBING FUNCTION, Lloyd Carpenter, March 1962 TND 1291 SOLAR PROTON IMPACT ZONES, ThomasKelsall, June 1962 TN D 1292 A PULSED FREQUENCY MODULATION DECOMMUTATOR, H. H. Levy, A. M.

Demmerle, and J. L. Tinsley, June 1962 TN D 1293 TELEMETERING INFRARED DATAFROM THETIROSMETEOROLOGICAL SATELLITES, J. F. Davis, R. A. Hanel, R. A. Stampfl, M. G.

Strange, and M. R. Townsend,August 1962 RE-ENTRY GLIDEMANEUVERS FORRECOVERY OFA WINGED FIRST-STAGE TN D 1295 ROCKET BOOSTER, Alan D. Levin and Edward J. Hopkins, May 1962 TN D 1297 AN INVESTIGATION OF THENORMAL-FORCE ANDVORTEX-WAKE CHARAC- TERISTICS OF AN OGIVE-CYLINDER BODY AT SUBSONIC SPEEDS, Bruce E. Tinling and Clyde Q. Allen, April 1962 TN D 1298 THEORY OFHIGH-SPEED-IMPACT ATTENUATION BY GASBAGS,John ThomasHowe,April 1962 TN D 1300 EFFECTS OF SIMULATED RETROROCKETS ONTHEAERODYNAMIC CHARAC- TERISTICS OFA BODY OF REVOLUTION AT MACH NUMBERS FROM 0.25 TO 1.90, Victor L. Peterson and Robert L. McKenzie, May 1962 TN D 1301 AERODYNAMIC CHARACTERISTICS OFA 4-FOOT-DIAMETER DUCTED FAN MOUNTED ONTHETIP OF A SEMISPAN WING,Kenneth W. Mort and Paul F. Yaggy, April 1962 APPROXIMATIONS FORTHETHERMODYNAMIC ANDTRANSPORT PROPERTIES TND 1303 OF HIGH-TEMPERATURE NITROGEN WITHSHOCK-TUBE APPLICATIONS, Warren F. Ahtye and Tzy-Cheng Peng, August 1962 TN D 1304 SECONDARY FLOW FIELDSEMBEDDED IN HYPERSONIC SHOCK LAYERS, Alvin Seiff, May 1962 TND 1307 ESTIMATION OF CRITICALTEMPERATURE FORSURFACE ION CURRENTS FROM ELECTRON EMISSION DATA,Thaine W. Reynolds, May 1962 TN D 1312 ANALYSIS OF MELTING BOUNDARY LAYERS ONDECELERATING BODIES, Simon Ostrach, Arthur W. Goldstein, and Jesse Hamman, July TN D 1313 EFFLUX OF THERMAL RADIATION FROM A CYLINDRICAL CAVITYIRRADIATED FROM AN EXTERNAL SOURCE, E. M. Sparrow, June 1962 TN D 1314 BOILINGHEATTRANSFER TO LIQUID HYDROGEN ANDNITROGEN IN FORCED FLOW, JamesP. Lewis, Jack H. Goodykoontz, and John F. Kline, September1962 TND 1316 THREE-DIMENSIONAL TRAJECTORY ANALYSIS FORROUND-TRIP MISSIONS TO MARS,Gerald Knip, Jr. and Charles L. Zola, October 1962 TND 1319 THREE-DIMENSIONAL TRAJECTORY ANALYSIS FORROUND-TRIP MISSIONS TOVENUS,Charles L. Zola and Gerald Knip, Jr., August 1962 TND 1320 A CENTRAL FACILITYFORRECORDING ANDPROCESSING TRANSIENT- TYPEDATA,By Staff of the Lewis Research Center, January 1963 TN D 1323 NUMERICAL SOLUTION OF TWO-DIMENSIONAL POISSON EQUATION: THEORY ANDAPPLICATION TO ELECTROSTATIC-ION-ENGINE ANALYSIS,Vladimir Hamzaand EdwardA. Richley, October 1962 TND 1324 ELECTRON DIFFUSION IN A TURBULENT PLASMA, Harold R. Kaufman, June 1962 TN D ]326 MOTIONS OF A SHORT I0 ° BLUNTED CONE ENTERING A MARTIAN ATMOSPHERE AT ARBITRARY ANGLES OFATTACK ANDARBITRARY PITCHING RATES,Victor L. Peterson, May 1962 TN D 1327 STATICAERODYNAMIC CHARACTERISTICS OF SHORT BLUNT CONES WITH VARIOUS NOSE ANDBASECONE ANGLES AT MACH NUMBERS FROM 0.6 TO 5.5 ANDANGLES OF ATTACK TO 180° , Stuart L. Treon, May 1962 TN D 1330 THEDETERMINATION OFABLATIVEPROPERTIES OFMATERIALS IN FREE- FLIGHTRANGES, Raymond C. Savin, Hermilo R. Gloria, and Richard G. Dahms,June 1962 TN D 1331 THETHEORETICAL ENTHALPY DISTRIBUTION OF AIR IN STEADY FLOW ALONG THEAXIS OFA DIRECT-CURRENT ELECTRIC ARC, HowardA. Stine and Velvin R. Watson, August 1962 TN D 1332 MEASUREMENTS OF THEEFFECTIVE HEATS OFABLATION OFTEFLON AND POLYETHYLENE AT CONVECTIVE HEATING RATES FROM 25 TO 420 BTU/FT 2 SEC,Dale L. Compton, Warren Winovich and Roy M. Wakefield, August 1962 TN D 1334 WIND-TUNNEL TESTS OFA SERIESOF 18-FOOT-DIAMETER PARACHUTES WITHEXTENDABLE FLAPS,Berl Gamse and Paul F. Yaggy, August TN D 1335 A LARGE-SCALE WIND-TUNNEL INVESTIGATION OF A WINGLESS VERTICAL TAKE-OFF ANDLANDING AIRCRAFT, David G. Koenig and JamesA.

Brady, February 1963 TN D 1336 THEEARTH'S FREE OSCILLATIONS, Gordon J. F. MacDonald, June 1962 TN D 1337 A TUNNEL-DIODE COUNTER FORSATELLITE APPLICATIONS, Edgar G. Bush, June 1962 TN D 1338 PRELIMINARY RESULTS OF RADIATION MEASUREMENTS FROM THETIROSIII METEOROLOGICAL SATELLITE,W. Nordberg, W. R. Bandeen, B. J.

Conrath, V. Kunde, and I. Persano, May 1962 TN D 1340 SCIENTIFICSATELLITES ANDTHESPACE ENVIRONMENT, John C. New, June 1962 TN D 1341 EARTH SCAN ANALOG SIGNAL RELATIONSHIPS IN THETIROSRADIATION EXPERIMENT ANDTHEIRAPPLICATION TO THEPROBLEM OF HORIZON SENSING, Barney J_ Conrath, June 1.962 TND 1344 PRELIMINARY REPORT ONTHESINGLE STATION DOPPLER ROCKET TRACKING TECHNIQUE, J. Carl Seddon, January 1963 TN D 1345 A CORRELATION FUNCTION DEFINITIONOF SPECTRAL RESOLUTION, Sidney O. Kastner, William A. White, John K. Coulter, and William E. Behring, June 1962 TN D 1346 EXPERIMENTAL EVIDENCE FORTHEPRESENCE OFHELIUMIONSIN THE UPPER ATMOSPHERE BASED ONEXPLORER VIII SATELLITE DATA,R. E.

Bourdeau, E. C. Whipple, Jr., J. L. Donley, and S. J. Bauer, July 1962 TN D 1347 CALCULATION OF THEECLIPSE FACTOR FORELLIPTICALSATELLITE ORBITS,Fred G. Cunningham,June 1962 TN D 1348 SPACECRAFT INFORMATION SYSTEMS, George H. Ludwig, October 1962 TND 1349 THEDISTRIBUTION OF SMALL INTERPI_NETARY DUST PARTICLES IN THE VICINITY OFTHEEARTH,C. W. McCrackenand W. M. Alexander, July 1962 TN D 1350 COMPUTATION OF THEPERTURBATIONS OF NEARLY CIRCULAR ORBITS, USING A NON-SINGULAR SETOFVECTORIAL ELEMENTS, Peter Musen, August 1962 TND 1355 EXPERIMENTAL INVESTIGATION OF THEEFFECT OF CONVECTIVE AND RADIATIVE HEAT LOADS ONTHEPERFORMANCE OF SUBLIMING AND CHARRING ABLATORS, Roger W. Peters and R. Gale Wilson, July TN D 1357 PROCEEDINGS OF CONFERENCE ONSPACECRAFT STERILIZATION, FreemanH. Quimby, editor, December1962 TND 1358 HIGH-EFFICIENCY MODIFIED FRESNEL REFLECTORS FORSOLAR-ENERGY CONCENTRATION, AtwoodR. Heath, Jr., July 1962 A WIND-TUNNEL INVESTIGATION OF PRESSURE FLUCTUATIONS ONTHE TN D 1359 UPPER VERTICAL TAIL OFTHEX-15 WHEN MATED TOTHEB-52 CARRIER AIRPLANE,John W. McKeeand ThomasA. Byrdsong, June 1962 THEELECTROMAGNETIC-RADIATION ENVIRONMENT OFA SATELLITE.

TN D 1360 PARTI. RANGE OF THERMAL TO X-RADIATION, S. Katzoff, September TN D 1361 THEELECTROMAGNETIC-RADIATION ENVIRONMENT OFA SATELLITE.

PARTII. RADIOWAVES, Jerry L. Modisette, September 1962 TN D 1362 WIND-TUNNEL INVESTIGATION OF TAIL BUFFET AT SUBSONIC AND TRANSONIC SPEEDS EMPLOYING A DYNAMIC ELASTIC AIRCRAFT MODEL, Robert N. Rigby and Elden S. Cornette, September1962 TN D 1364 A WIND-TUNNEL INVESTIGATION OF THELONGITUDINAL AERODYNAMIC CHARACTERISTICS OFTWO FULL-SCALE HELICOPTER FUSELAGE MODELS WITHAPPENDAGES, Julian L. Jenkins, Jr., Matthew M. Winston, and George E. Sweet, July 1962 TN D 1366 THEORBITAL BEHAVIOR OF THEECHO I SATELLITE ANDITS ROCKET CASING DURING THEFIRST 500 DAYS,Gertrude C. Westrick and Katherine G. Johnson, June 1962 TN D 1369 TEMPERATURE CONTROL OF THEEXPLORER IX SATELLITE,Charles V.

Woerner and Gerald M. Keating, July 1962 TN D 1370 NUMERICAl ANALYSIS OF THETRANSIENT RESPONSE OFADVANCED THERMAL PROTECTION SYSTEMS FORATMOSPHERIC ENTRY.Robert T.

Swannand Claud M. Pittman, July 1962 TN D 1371 PRESSURE DISTRIBUTIONS ONTWO-DIMENSIONAL SHARP-LEADING-EDGE FLATPLATES WITHSWEEP ANGLES OF 0°, 30° , AND45° AT A MACH NUMBER OF 6 ANDANGLES OF ATTACK FROM 0° TO 90° , JamesG.

Hondros, September 1962 TN D 1372 HEAT-TRANSFER ANDPRESSURE MEASUREMENTS ONA FLAT-PLATE SUR- FACE ANDHEAT-TRANSFER MEASUREMENTS ONATTACHED PROTUBERANCES IN A SUPERSONIC TURBULENT BOUNDARY LAYER AT MACH NUMBERS OF 2.65, 3.51, AND4.44, Paige B. Burbank, Robert A. Newlander, an_ Ida K. Collins, December1962 TN D 1374 LOW-SPEED LONGITUDINAL AERODYNAMIC CHARACTERISTICS ASSOCIATED WITHA SERIES OF LOW-ASPECT-RATIO WINGS HAVING VARIATIONS IN LEADING-EDGE CONTOUR, Bernard Spencer, Jr. and Alexander D.

Hammond, September1962 TND 1377 DESCRIPTION ANDPRELIMINARY CALIBRATION TESTOF A SMALL ARC- HEATED HYPERSONIC WINDTUNNEL, William B. Boatright, Roger B. Stewart, and John E. Grimaud, December1962 TN D 1378 AERODYNAMIC HEATING ANDBOUNDARY-LAYER TRANSITION ONA 1/10- POWER NOSE SHAPE IN FREEFLIGHTAT MACH NUMBERS UP TO 6.7 AND FREE-FLIGHT REYNOLDS NUMBERS UP TO 16 x 106, Benjamine J.

Garland, Andrew G. Swanson, and Katherine C. Speegle, June TN D 1381 LOW-SPEED STATICLONGITUDINAL ANDLATERAL AERODYNAMIC CHARAC- TERISTICS OF A MODEL WITHA LOW-ASPECT-RATIO VARIABLE-INCIDENCE WING ANDWITHA FREE-FLOATING ANDA PROGRAMMED HIGH-LIFT CANARD CONTROL, William I. Scallion, October 1962 TN D 1382 SLIPSTREAM FLOW AROUND SEVERAL TILT-WINGVTOLAIRCRAFT MODELS OPERATING NEAR THEGROUND, William A. Newsom,Jr. and Louis P.

Tosti, September1962 TN D 1383 RADIATION EXPOSURE IN SUPERSONIC TRANSPORTS, Trutz Foelsche, August 1962 TN D 1384 A WIND-TUNNEL INVESTIGATION AT A MACH NUMBER OF 2.01 OF THE SONIC-BOOM CHARACTERISTICS OF THREE WING-BODY COMBINATIONS DIFFERING IN WING LONGITUDINAL LOCATION, Odell A. Morris, September1962 TN D 1387 THEATMOSPHERE AS A PARTOF THESPACE ENVIRONMENT, Richard A.

Hord, Wilber Bo Huston, and Harold B. Tolefson, January 1963 TN D 1388 DRAG CHARACTERISTICS ANDDYNAMIC STABILITYIN DESCENT OF A ROTARY PARACHUTE TESTED IN A VERTICAL TUNNEL, Sanger M. Burk, Jr., August 1962 TN D 1391 WIND-TUNNEL MEASUREMENTS OF AERODYNAMIC DAMPING DERIVATIVES OF A LAUNCH VEHICLE VIBRATING IN FREE-FREE BENDING MODES AT MACH NUMBERS FROM 0.70 TO 2.87 ANDCOMPARISONS WITHTHEORY, Perry W.

Hansonand Robert V. Doggett, Jr., October 1962 TN D 1393 A TABULATION OF WIND-TUNNEL PRESSURE DATAANDSECTION AERO- DYNAMIC CHARACTERISTICS AT M_CH NUMBERS OF 1.61 AND2.01 FOR A REFLEX CAMBERED WING ANDA CAMBERED ANDTWISTED WING HAVING THESAME SWEPT PLANFORM, Emma Jean Landrum, September1962 TND 1394 A TABULATION OF WIND-TUNNEL PRESSURE DATAANDSECTION AERO- DYNAMIC CHAraCTERISTICS AT MACH NUMBERS OF 1.61 AND2.01 FOR TWO TRAPEZOIDAL ANDTHREE DELTA WINGS HAVING DIFFERENT SURFACE SHAPES, Emma Jean Landr_m, September1962 AN ANALYSIS OF THECONING MOTIONS OF THEFINAL STAGES OF THREE TND 1396 NASA SCOUT DEVELOPMENT VEHICLES,GeorgeR. Young and JamesJ.

Buglia, December1962 TN D 1397 LOW-SPEED LONGITUDINAL CHARACTERISTICS OFAN AIRPLANE CONFIGU- RATION INCLUDING EFFECTS OF CANARD ANDWING TRAILING-EDGE FLAP CONTROLS IN COMBINATION, Bernard Spencer, Jr. and William C.

Sleeman, Jr., September1962 TND 1398 A STUDY OFTHRUST VECTOR STEERING FORRENDEZVOUS WITHA NEAR- EARTH SATELLITE UTILIZINGA THREE-STAGE VEHICLE LAUNCHED OUT OF THESATELLITE PLANE,Charles P. Llewellyn, October 1962 TND 1400 INDUCED INTERFERENCE EFFECTS ONA FOUR-JET VTOLCONFIGURATION WITHVARIOUS WING PLANFORMS IN THETRANSITION SPEED RANGE, JamesH. Otis, Jr., September 1962 TN D 1401 ERECTABLE YAGI DISKANTENNAS FORSPACE-VEHICLE APPLICATIONS, William F. Croswell and Melvin C. Gilreath, October 1962 EXPERIMENTAL DETERMINATION OF SPECTRA ANDTOTAL TRANSMISSIVI- TN D 1405 TIES OF CLOUDS OF SMALL PARTICLES, Chester D. Lanzo and Robert G. Ragsdale, September1962 TND 1406 CALCULATION OF TRANSPORT PROPERTIES OF HEAT-TRANSFER PARAMETERS OF DISSOCIATION HYDROGEN, NormanT. Grier, October 1962 TN D 1412 ANALYSIS OF FLUORINE GASBY REACTION WITHMERCURY, Robert E.

Seaver, August 1962 TN D 1413 A PRELIMINARY STUDY OF THEORBITS OFMERITFORMOON PROBES, Su- Shu Huang, July 1962 TN D 1415 CALCULATION OF EPHEMERIDES FROM INITIAL VALUES, Karl Stumpff, December1962 TN D 1416 THELONG-PERIOD MOTION OF THETROJANS, WITHSPECIAL ATTENTION TO THETHEORY OF THUERING, Karl Stumpff, June 1963 TN D 1417 ONLAGRANGE'S THEORY OF THETHREE-BODY PROBLEM, Karl Stumpff, January 1963 TN D 1418 MEASUREMENTS OF THEGEOMAGNETIC FIELD BY THEVANGUARD III SATELLITE, Joseph C. Cain, Ivan R. Shapiro, John D. Stolarik, and JamesP. Heppner, October 1962 TN D 1419 A PHASE-LOCKED PHASE FILTERFORTHEMINITRACK SYSTEM, Ronald F.

Woodman, September 1962 TN D 1421 PULSE FREQUENCY MODULATION, R. W. Rochelle, October 1962 TN D 1422 THENIMBUS SPACECRAFT ANDITS COMMUNICATION SYSTEM AS OF SEPTEMBER 1961, Rudolf A. Stampfl, January 1963 TN D 1423 PREDICTED GASPROPERTIES IN THESHOCK LAYER AHEAD OF CAPSULE- TYPEVEHICLES AT ANGLES OFATTACK,GeorgeE. Kaattari, October TN D 1424 RADIATIVE HEATTRANSFER ANDABSORPTION BEHIND A HYPERSONIC NORMAL SHOCK WAVE, Kenneth K. Yoshikawa and Dear R. Chapman, September 1962 TND 1425 FREE-FLIGHT TESTS OF FIFTH-STAGE SCOUT ENTRY VEHICLE AT MACH NUMBERS OF 5 AND17, Donn B. Kirk and Robert J. Miller, October TND 1426 COMPARISON OF EXPERIMENTAL ANDNUMERICAL RESULTS FORTHEFLOW OF A PERFECT GASABOUT BLUNT-NOSED BODIES,MamoruInouye and Harvard Lomax, september 1962 TN D 1427 ATMOSPHERE ENTRIES WITHSPACECRAFT LIFT-DRAG RATIOS MODULATED TOLIMIT DECELERATIONS, Lionel L. Levy, Jr., October 1962 TN D 1428 A I-FOOTHYPERVELOCITY SHOCK TUNNEL IN WHICH HIGH-ENTHALPY, REAL-GAS AIR FLOWS CANBEGENERATED WITHFLOW TIMESOFABOUT 180 MILLISECONDS, Bernard E. Cunninghamand SamuelKraus, October 1962 TN D 1430 LONGITUDINAL TRIMCHARACTERISTICS OFA DEFELCTED SLIPSTREAM V/STOLAIRCRAFT DURING LEVELFLIGHTAT TRANSITION FLIGHT SPEEDS, HowardL. Turner and Fred J. Drinkwater III, October TN D 1432 LARGE-SCALE WIND-TUNNEL TESTS OF A CIRCULAR PLAN-FORM AIRCRAFT WITHA FERIPHERAL JET FORLIFT, THRUST, ANDCONTROL, Richard K. Greif and William H. Tolhurst, Jr., February 1963 TN D 1433 ANALYSIS OFGUIDANCE PERTURBATIONS FORA LOW-THRUST MARS ORBITER MISSION USINGSNAP-8,Alan L. Friedlander, December MONTE CARLO CALCULATIONS OF NEUTRON NUMBER SPECTRA ANDBUILDUP TN D 1434 FACTORS IN INFINITE CONICAL CONFIGURATIONS, Millard L. Wohl, September 1962 TND 1435 HEAT-TRANSFER CHARACTERISTICS OF SEVERAL RADIATOR FINNED-TUBE CONFIGURATIONS, E. M. Sparrow and W. J. Minkowycz, November TN D 1436 HEATTRANSFER ANDPRESSURE DISTRIBUTION ONCONE-CYLINDER-FLARE CONFIGURATION WITHBOUNDARY-LAYER SEPARATION, Harold Ferguson and John W. Schaefer, October 1962 CAVITATION ANDNONCAVITATION PERFORMANCE OF AN 80.6 ° FLAT- TND 1439 PLATEHELICALINDUCER AT THREE ROTATIONAL SPEEDS, Donald M.

Sandercock, Richard F. Soltis, and Douglas A. Anderson, November1962 ONTHEEFFECT OF HEAT ADDITIONIN THEEMPIRICAL CORRELATION OF TN D 1440 VOIDFRACTIONS FORSTEAM-WATER FLOW,UweH. vonGlahn and Richard P. Polcyn, November1962 TN D 1441 COMBINED RADIATION ANDFORCED CONVECTION FORFLOW OFA TRANS- PARENT GASIN A TUBE WITHSINUSOIDAL AXIAL WALL HEATFLUX DISTRIBUTION, Robert Siegel, October 1962 TND 1443 TIME-DEPENDENT STRUCTURE OF THEUPPER ATMOSPHERE, Isadore Harris and Wolfgang Priester, July 1962 TND 1444 THEORETICAL MODELS FORTHESOLAR-CYCLE VARIATION OF THEUPPER ATMOSPHERE, Isadore Harris and Wolfgang Priester, August 1962 TN D 1445 DIFFERENTIAL CORRECTION FORVINTI'S ACCURATE INTERMEDIARY ORBIT, N. L. Bonavito, December1962 TN D 1447 THEMAGNETIC FIELD OFA MODEL RADIATION BELTNUMERICALLY COMPUTED, Syun-Ichi Akasofu, Joseph C. Cain, and SydneyChapman,November TN D 1448 CORRECTION FORATMOSPHERIC REFRACTION AT THENASA MINITRACK STATIONS, F. O. Vonbun, August 1962 TND 1449 ARTICMETEOROLOGY PHOTO PROBE POLARIZED LIGHTEXPERIMENT, Gerald L. Hempfling, Harold E. Evans. Robert C. Baumann,and Richard J.

Andryshak, August 1963 TN D 1450 THEORBITING GEOPHYSICAL OBSERVATORY, A NEW TOOL FORSPACE RESEARCH, GeorgeH. Ludwig and Wilfred E. Scull, August 1962 TN D 1451 APPLICATION OF THEMODULARIZATION CONCEPT TO SATELLITE TAPE RECORDERS, P. T. Cole, H. J. Peake, and C. F. Rice, November1962 TN D 1452 RELIABILITYANDREDUNDANCY CONSIDERATIONS IN SELECTING SPACE- CRAFT BATTERIES, Joseph M. Sherfey and Klaus Johannsen, October TN D 1453 A FORTRAN II PROGRAM FORANALYSIS OF RADIOACTIVE DECAY CURVES, John L. Need and Theordore E. Fessler, October 1962 TN D 1454 A GENERAL IBM 704 OR7090 COMPUTER PROGRAM FORCOMPUTATION OF CHEMICAL EQUILIBRIUM COMPOSITIONS, ROCKET PERFORMANCE, AND CHAPMAN-JOUGUET DETONATIONS, Frank J. Zeleznik and Sanford Gordon, October 1962 TND 1455 THEN-BODY CODE - A GENERAL FORTRAN CODE FORSOLUTION OF PROBLEMS IN SPACE MECHANICS BYNUMERICAL METHODS, William C.

Strack, Wilbur F. Dobson, and Vearl N. Huff, January 1963 TN D 1456 OPTIMUM LOW-ACCELERATION TRAJECTORIES FORINTERPLANETARY TRANSFERS, Arthur V. Zimmerman,John S. MacKay, and Leonard G.

Rossa, January 1963 TN D 1457 AN ELECTRON-BOMBARDMENT ION ROCKET OPERATED WITHALTERNATING- CURRENT SUPPLIES, Paul D. Reader and Robert C. Finke, December TN D 1459 EFFECTS OFAIR CONTENT ANDWATER PURITYONLIQUIDTENSION AT INCIPIENTCAVITATION IN VENTURI FLOW,Robert S. Ruggeri and ThomasF. Gelder, March 1963 EXPERIMENTAL NEUTRON FLUXDISTRIBUTIONS IN A GRAPHITE ASSEMBLY TN D 1460 WITHAN INTERNAL CAVITY,ThomasA. Fox, Donald F. Shook, Robert A. Mueller, and Daniel Fieno, October 1962 TN D 1462 MICROPOWER TRANSISTOR LOGICCIRCUITS,John C. Sturman, February TN D 1463 RADIOMETRIC MEASUREMENTS FROM SATELLITES, R. A. Hanel, October TN D 1464 A DOUBLE GAMMA-RAY SPECTROMETER TO SEARCH FORPOSITRONS IN SPAGE, ThomasL. Cline, Peter Serlemitsos, and EdwardW.

Hones, Jr., October 1962 TN D 1465 THEEARLY CHRONOLOGY OF THESOLAR SYSTEM, A. G. W. Cameron, August 1962 TND 1466 SOLAR OBSERVATIONS WITHA SOFT X-RAYSPECTROMETER, W. M.

Neupert and W. E. Behring, September1962 TN D 1467 ONSCALING LAWS FORMATERIAL DAMPING, Stephen H. Crandall, December1962 AN ANALYTIC REPRESENTATION OFMUSEN'S THEORY OFARTIFICIAL TN D 1468 SATELLITES IN TERMS OF THEORBITAL TRUE LONGITUDE, Ann E.

Bailie and David Fisher, January 1963 ROTATIONAL DECAY OF THESATELLITE 1960 ETA2 DUETO THEEARTH'S TN D 1469 MAGNETIC FIELD, Raymond H. Wilson, Jr., October 1962 SATELLITE MOTION IN THEVICINITY OF CRITICALINCLINATION, TN D 1470 David Fisher, October 1962 TND 1471 TRACKING SYSTEMS, THEIRMATHEMATICAL MODELS ANDTHEIRERRORS.

PARTI - THEORY, F. O. Vonbunand W. D. Kahn, October 1962 EARTH-REFLECTED SOLAR RADIATION INCIDENT UPON SPHERICAL SATELLITES TND 1472 IN GENERAL ELLIPTICALORBITS,F. G. Cunningham,February 1963 AIR-HELIUMSIMULATION OFTHEAERODYNAMIC FORCE COEFFICIENTN OF TN D 1473 CONES AT HYPERSONIC SPEEDS, Charles L. Ladson and ThomasA.

Blackstock. APPENDIX: DESIGN ANDCALIBRATION OFTHREE HELIUM NOZZLES IN THELANGLEY ±I-INCH HYPERSONIC TUNNEL, Donald L.

Baradell and ThomasA. Blackstock, October 1962 TN D 1474 ENVIRONMENTAL PROBLEMS OF SPACE FLIGHTSTRUCTURES. I. IONIZING RADIATION IN SPACE ANDITS INFLUENCE ONSPACECRAFT DESIGN, Prepared by Louis F. Vosteen in collaboration with the NASA Research Advisory Con_nittee on Missile and SpaceVehicle Structures, October 1962 TIME-DEPENDENT AIR FORCES ONWINGS WITHSUPERSONIC LEADING AND TN D 1475 TRAILINGEDGES ANDSUBSONIC SIDE EDGES WITHAPPLICATION TO A WING DEFORMING HARMONICALLY ACCORDING TOA GENERAL POLYNOMIAL EQUATION, Joseph A. Drischler, December1962 TN D 1476 ONE-DIMENSIONAL HEATCONDUCTION THROUGH THESKINOF A VEHICLE UPON ENTERING A PLANETARY ATMOSPHERE AT CONSTANT VELOCITY AND ENTRY ANGLE,William R. Wells and Charles H. McLellan, October TN D1477 A PRELIMINARY EXPERIMENTAL INVESTIGATION OFAN ENERGY-ABSORPTION PROCESS EMPLOYING FRANGIBLE METAL TUBING,John R. McGehee, October 1962 TN D 1478 AN INVESTIGATION TODETERMINE THEDISCHARGE ANDTHRUST CHARAC- TERISTICS OFAUXILIARY-AIROUTLETS FORA STREAM MACH NUMBER OF 3.25, Allen R- Vick, October 1962 TN D 1479 FIXED-BASE-SIMULATOR STUDY OF PILOTED ENTRIES INTOTHEEARTH'S ATMOSPHERE FORA CAPSULE-TYPE VEHICLE AT PARABOLIC VELOCITY, John W. Young and Walter R. Russell, October 1962 TND 1480 STABILITYLIMITS OF THEPREMIXED STOICHIOMETRIC CYANOGEN- OXYGEN FLAME,Irving Fruchtman, October 1962 TN D 1481 AERODYNAMIC CHARACTERISTICS OF FOUR-DUCTTANDEM VTOL-AIRCRAFT CONFIGURATIONSj William A. Newsom_ Jr., January 1963 TN D 1483 AN INVESTIGATION OF LANDING-CONTACT CONDITIONS FORSEVERAL TURBO- JET TRANSPORTS DURING ROUTINE DAYLIGHT OPERATIONS AT NEW YORK INTERNATIONAL AIRPORT,Joseph W. Stickle, October 1962 TND 1486 THELOCATION ANDSIMIILATED REPAIR OF ROUGH AREAS OFA GIVEN RUNWAY BYAN ANALYTICAL METHOD, Albert W. Hall and Sheldon Kopelson, October 1962 TN D 1488 VTOLHEIGHT-CONTROL REQUIREMENTS IN HOVERING AS DETERMINED FROM MOTION SIMULATOR STUDY,John F. Garren, Jr. and Arthur Assadourian October 1962 TND 1489 INVESTIGATIONiOFVTOL APPROACH METHODS BY USEOF GROUND-CONTROLLED- APPROACH PROCEDURES, JamesP. Trant, Jr. and Joseph S. Algranti, October 1962 TN D 1490 IRRADIATION EFFECTS OF 40 AND 440 MEV PROTONS ON TRANSISTORS, William C. Honaker and Floyd R. Bryant, January 1963 TN D 1491 TRANSITION AND HOVERING FLIGHT CHARACTERISTICS OF A TILT-DUCT VTOL RESEARCH AIRCRAFT, Henry L. Kelley, November 1962 TN D 1494 THE LOWER BOUND OF ATTAINABLE SONIC-BOOM OVERPRESSURE AND DESIGN METHODS OF APPROACHING THIS LIMIT, Harry W. Carlson, October 1962 TN D 1500 A FREE-FLIGHT INVESTIGATION OF ABLATION OF A BLUNT BODY TO A MACH NUMBER OF 13.1, Clyde W. Winters, William G. Witte, Bernard Rashis, and Russell N. Hopko, December 1962 TN D 1502 NOISE MEASUREMENTS DURING CAPTIVE AND LAUNCH FIRINGS OF A LARGE ROCKET-POWERED VEHICLE, William H. Mayes and Philip M.

Edge, Jr.,November 1962 TN D 1503 HEAT TRANSFER AND PRESSURE DISTRIBUTIONS ON A HEMISPHERE- CYLINDER AND A BLUFF-AFTERBODY MODEL IN METHANE-AIR COMBUSTION PRODUCTS AND IN AIR, Irving Weinstein, December 1962 TN D 1504 A REPORT ON THE RESEARCH AND TECHNOLOGICAL PROBLEMS OF MANNED ROTATING SPACECRAFT, Langley Research Center Staff, August TN D 1505 THE BENDING-MOMENT DISTRIBUTION OF CAMBERED-SPAN WING SYSTEMS HAVING MINIMUM INDUCED DRAG, Clarence D. Cone, Jr., March 1963 TN D 1509 PROPELLER SLIPSTREAM EFFECTS AS DETERMINED FROM WING PRESSURE DISTRIBUTION ON A LARGE-SCALE SIX-PROPELLER VTOL MODEL AT STATIC THRUST, Matthew M. Winston and Robert J. Fuston, December 1962 TN D 1512 THE INFLUENCE OF PRECESSION OF EARTH RENDEZVOUS ORBITS ON LUNAR MISSION REQUIREMENTS, William R. Wells, November 1962 TN D 1519 THE EFFECT OF VACUUM ON THE PENETRATION CHARACTERISTICS OF PROJECTILES INTO FINE PARTICLES, Leonard V. Clark and John Locke McCarty, January 1963 TN D 1524 THERMAL RADIATION INCIDNET ON AN L%RTH SATELLITE, Frank E.

Swalley, December 1962 TN D 1526 A CONSIDERATION OF LUNAR SURFACE BALLISTICS AND THE HAZARDS ASSOCIATED WITH SPACECRAFT LANDING OR LAUNCH OPERATIONS, D. C. Cramblit, March 1963 TN D 1527 HEAT TRANSFER IN LAMINAR FLOWS OF INCOMPRESSIBLE FLUIDS WITH Pr _ 0 AND Pr ÷ _, Ernst W. Adams, February 1963 TND 1530 ANALOG STUDY OFDESCENTS FROM LUNAR ORBIT, Joseph N. Sivo and Carl E. Campbell, December1962 TN D 1532 EXPERIMENTAL INVESTIGATION OF A 90° FLAT-PLATE MAGNETIC TRIODE FORDIRECT ENERGY CONVERSION, Richard R. Cullom, November1962 A NUMERICAL SOLUTION OFTHEPROBLEM OF MIXINGOF LAMINAR COAXIAL TND 1534 STREAMS OF GREATLY DIFFERNT DENSITIES - ISOTHERMAL CASE,Herbert Weinstein and Carroll A. Todd, February 1963 HEAT TRANSFER TOA SPHERE WITHA RETRO-ROCKET EXHAUSTING INTO A TND 1535 FREESTREAM; MACH 2.0 AND0.8, Robert A. Wasko, November1962 TN D 1536 AN INVESTIGATION OF THELIQUID LEVELAT THEWALL OF A SPINNING TANK,David M. Winch, August 1962 TN D 1537 PRELIMINARY INVESTIGATION OF CATASTROPHIC FRACTURE OF LIQUID- FILLED TANKS IMPACTED BYHIGH-VELOCITY PARTICLES, Francis S.

Stepka and C. Robert Morse, May 1963 TN D 1538 FIRST TOPSIDE SOUNDINGS OF THEIONOSPHERE, J. E. Jackson, R. W.

Knecht, and S. Russell, March 1963 A SATELLITE ORBITCOMPUTATION PROGRAM FORIZSAK'S SECOND-ORDER TN D 1539 SOLUTION OF VINTI'S DYNAMICAL PROBLEM, Raymond V. Borchers, February 1963 TN D 1540 REMARKS ONHILL'S LUNAR THEORY.PARTI, Karl Stumpff, March TN D 1541 REMARKS ONHILL'S LUNAR THEORY.PARTII, Karl Stumpff, March TN D 1542 A PRECISION ENDLESS-LOOP MAGNETIC TAPERECORDER FORSPACE APPLICATIONS, R. C. Falwell, K. W. Stark, and A. F. White, February 1963 TN D 1543 USEOF A SEALED SILVER-CADMIUM BATTERY ONEXPLORER XII, T. J. Hennigan and A. O. Apelt, January 1963 TN D 1544 DIRECT MEASUREMENTS OF COSMIC DUSTSHOWERS, M. Dubin, W. M.

Alexander, and O. E. Berg, January 1963 TN D 1545 POWER INPUTTO A SMALL FLATPLATEFROM A DIFFUSELY RADIATING SPHERE WITHAPPLICATION TO EARTH SATELLITES: THESPINNING PLATE,Fred G. Cunningham,February 1963 TND 1546 THEIMPEDANCE OF AN ELECTRICALLY SHORT ANTENNA IN THEIONO- SPHERE, H. A. Whale, January 1963 TND 1547 DELINEATION OFTRACKS OF HEAVY COSMIC RAYS ANDNUCLEAR PROCESSES WITHINLARGE SILVERCHLORIDE CRYSTALS, Charles B. Childs and LawrenceM. Slifkin, March 1963 TN D 1548 WIND-TUNNEL TESTS OF TWO FULL-SCALE HELICOPTER FUSELAGES, James C. Biggers, John L. McCloud III, and Pete Patterakis, October TN D 1549 ANALYTICAL STUDY OF THETUMBLING MOTIONS OF VEHICLES ENTERING PLANETARY ATMOSPHERES, Murray Tobak, October 1962 TND 1550 HELIUM FILM COOLING ONA HEMISPHERE AT A MACH NUNBER OF i0, Robert E. Dannenberg, November1962 TND 1551 THEMAGNETIC FIELD OF A LINE CURRENT IN A TRANSVERSE RAREFIED PLASMA STREAM, Albert G. Munson, February 1963 TN D 1553 THERMODYNAMIC PROPERTIES OF CARBON-DIOXIDE ANDNITROGEN MIXTURES BEHIND A NORMAL SHOCK WAVE, Henry T. Woodward,March 1963 TN D 1554 LOCAL PRESSURE DISTRIBUTION ONA BLUNT DELTA WING FORANGLES OF ATTACK UP TO 35° AT MACH NUMBERS OF 3.4 AND4.7, Marvin Kussoy, December1962 TND 1555 Z-FUNCTION SOLUTIONS FORTHEMOTION ANDHEATING DURING ATMOSPHERE ENTRY FROM EQUATORIAL ORBITS OFA ROTATING PLANET,Frederick W.

Boltz, February 1963 TN D 1556 THELUNAR ORIGINOF TEKTITES,Dean R. Chapman and HowardK.

Larson, February 1963 TN D 1557 AERODYNAMIC CHARACTERISTICS IN GROUND EFFECT OFA LARGE-SCALE MODEL WITHA HIGHDISK-LOADING LIFTING FANMOUNTED IN THE FUSELAGE, Richard A. deSavigny and David H. Hickey, January 1963 TN D 1558 A RELIABILITYMODEL ANDANALYSIS FORPROJECT MERCURY - 3-ORBIT MANNED ANDUNMANNED MISSION,William Wolmanand Fred Okano, December1962 TN D 1560 LOW-POWER TESTS OF THEPLU_PBROOK REACTOR, Harold W. Giesler, Harry J. Reilly, and William A. Poley, February 1963 TN D 1561 ASYMMETRIC "PENSHAPE" NOZZLES IN JET-CANARD CONFIGURATIONS FOR ATTITUDE CONTROL, Robert W. Cubbison, September 1963 TN D 1562 METHOD FORDESIGN OF PUM IMPELLERS USING A HIGH-SPEED DIGITAL COMPUTER, Norbert O. Stockmanand ,JohnL. Kramer, January 1963 TND 1563 FEASIBILITYOFAPPLYING FIELD-IONEMISSION TO ELECTROSTATIC ROCKET ENGINES, N. Stankiewicz, January 1963 TN D 1564 A VISUALSTUDY OFTWO-PHASE FLOW IN A VERTICAL TUBEWITHHEAT ADDITION,Yih Yun Hsu and Robert W. Graham, January 1963 TND 1566 BASE HEATTRANSFER, PRESSURE RATIOS,ANDCONFIGURATION EFFECTS OBTAINED ONA 1/27 SCALE SATURN (C-I) MODEL AT MACH NUMBERS FROM 0.i TO 2.0, John L. Allen and Robert A. Wasko, May 1963 NITROGEN ANDOXYGEN ATOM RECOMBINATION AT OXIDESURFACES AND TN D 1567 EFFECT OF A TESLA DISCHARGE ONRECOMBINATION HEATTRANSFER, GeorgeM. Prok, January 1963 TN D 1569 MONTHLY ANDANNUAL WINDDISTRIBUTIONS ASA FUNCTION OF ALTITUDE FORSANTA MONICA,CALIFORNIA(PACIFICMISSILERANGE), J° W° Smith, January 1963 TN D 1570 ORBIT-LAUNCHED NUCLEAR VEHICLE DESIGN ANDPERFORMANCE EVALUATION PROCEDURE FORESCAPE ANDPLANETARY MISSIONS,Ronald J. Harris and Robert E. Austin, June 1963 TN D 1571 PROPOSAL FORDETERMINING THEMASS OF LIQUID PROPELLANT WITHINA SPACE VEHICLE PROPELLANT TANKSUBJECTED TOA ZERO GRAVITY ENVIRONMENT, R. L. Evans and J. R. Olivier, March 1963 TN D 1572 AN EVALUATION OF DETAILWINDDATAAS MEASURED BY THEFPS-16 RADAR/SPHERICAL BALLOON TECHNIQUE, JamesR. Scoggins, May 1963 TN D 1573 WINDFLOW IN THE80-400 KMALTITUDE REGION OF THEATMOSPHERE, George C° Ragsdale and Peter E. Wasko, March 1963 TND 1575 TWO-DIMENSIONAL CRITICALITYCALCULATIONS OF GASEOUS-CORE CYLINDRICAL-CAVITY REACTORS, Robert E. Hyland, Robert G.

Ragsdale, and EugeneJ. Gunn, March 1963 TN D 1576 EXPERIMENTAL EFFECT OF GASFLOW TRANSIENTS ONTHEHEAT RELEASE OF BURNING LIQUIDDROPS IN A ROCKET COMBUSTOR, Marcus F. Heidmann, March 1963 TN D 1579 PERFORMANCE CAPABILITY OF SINGLE-CAVITY VORTEX GASEOUS NUCLEAR ROCKETS, Robert G. Ragsdale. APPENDIX B: COMPUTER PROGRAM, Muriel B. Eian, May 1963 TND 1580 BOUNDARY LUBRICATION CHARACTERISTICS OF A TYPICALBEARING STEEL IN LIQUIDOXYGEN, William F. Hady, GordonP. Allen, and Robert L. Johnson, February 1963 TND 1582 EFFECT OF SURFACE ENERGY ONTHELIQUID-VAPOR INTERFACE CONFIGU- RATION DURING WEIGHTLESSNESS, Donald A. Petrash, ThomasM.

Nelson, and Edward W. Otto, January 1963 TND 1583 SUBCOOLED BOILINGHEATTRANSFER UNDER FORCED CONVECTION IN A HEATED TUBE,S. Stephen Papell, March 1963 TN D 1584 EVALUATION OFTHEINFLUENCE OF LOAD RANDOMIZATION ANDOF GROUND- AIR-GROUND CYCLES ONFATIGUE LIFE, EugeneC. Naumann,October TND 1586 AERODYNAMIC DATAONLARGE SEMISPAN TILTINGWING WITH0.6- DIAMETER CHORD, SINGLE SLOTTED FLAP, ANDSINGLE PROPELLER ROTATING UPAT TIP, Marvin P. Fink, Robert G. Mitchell, and Lucy C. White, October 1964 TN D 1587 NEUTRON SELF-SHIELDING FACTORS FORMULTIPLE-BODY CONCENTRIC CYLINDRICAL CONFIGURATIONS, Thor T. Semler, September1964 TN D 1588 COMPARISON OFABSOLUTE-AND REFERENCE-SYSTEM METHODS OF MEASURING CONTAINMENT-VESSEL LEAKAGE RATES,Edward G. Keshock, October 1964 TN D 1590 MEASUREMENT OFTHESTATE VECTOR, C. A. Harvey, November1962 TN D 1591 INVESTIGATION OF THEVISUALBOUNDARY FORIMMEDIATE PERCEPTION OF VERTICAL RATE OF DESCENT, Lindsay J. Lina and Arthur Assadourian, February 1963 TN D 1595 DETERIORATION OF CALCIA-STABILIZED ZIRCONIA,John D. Buckley, December1962 TN D 1596 RESEARCH PROBLEMS PERTAINING TO AIRCRAFT OPERATIONS, William A. McGowan and William S. Aiken, Jr., editors, March 1963 TN D 1597 THEUSEOFAN IONIZATION GAGE ASA QUANTITATIVE ANALYZER FOR BI-GASEOUS MIXTURES, Leonard T. Melfi, Jr. and GeorgeM. Wood, Jr., December1962 TN D 1598 DESIGN,OPERATION, ANDTESTING CAPABILITIES OF THELANGLEY 11-INCH CERAMIC-HEATED TUNNEL, Otto F. Trout, Jr., February TND 1599 A METHOD FORCOMPUTING THEEFFECT OFAN ADDITIONAL OBSERVATION ONA PREVIOUS LEAST-SQUARES ESTIMATE, Patrick A. Gainer, January 1963 TND 1601 AERODYNAMIC DRAG ANDSTABILITYCHARACTERISTICS OF TOWED INFLAT- ABLEDECELERATORS AT SUPERSONIC SPEEDS, John T. McShera, Jr., March 1963 TN D 1603 EXPERIMENTAL INVESTIGATION OF BLASTLOADING ONAN AIRFOIL IN MACH NUMBER 0.7 AIRFLOW WITHINITIAL ANGLE-OF-ATTACK CHANGE OF 20° , Harold B. Pierce and JamesC. Manning, February 1963 TN D 1604 EQUATIONS FOR DETERMINING VEHICLE POSITION IN EARTH-MOON SPACE FROM SIMULTANEOUS ONBOARD OPTICAL MEASUREMENTS, Alton P. Mayo, Harold A. Hamer, and Margery E. Hannah, February 1963 TN D 1605 EXPLORATORY INVESTIGATION OF THE EFFECT OF A FORWARD-FACING JET ON THE BOW SHOCK OF A BLUNT BODY IN A MACH NUMBER 6 FREE STREAM, David J. Romeo and James R. Sterrett, February 1963 TN D 1606 AERODYNAMIC CHARACTERISTICS AT A MACH NUMBER OF 6.77 OF A 9 ° CONE CONFIGURATION, WITH AND WITHOUTSPHERICAL AFTERBODIES, AT ANGLES OF ATTACK UP TO 180 ° WITH VARIOUS DEGREES OF NOSE BLUNTING, Luther Neal, Jr., March 1963 TN D 1607 A STUDY OF THE EFFECT OF A DEADBAND ABOUT A DESIRED PERIGEE ON THE GUIDANCE OF A SPACE VEHICLE APPROACHING THE EARTH, Jack A.

White, February 1963 TN D 1610 SELF-ERECTING FLEXIBLE FOAM STRUCTURES FOR SPACE ANTENNAS, Victor L. Vaughan, Jr., and Edward L. Hoffman, March 1963 TN D 1612 PRESSURE DISTRIBUTIONS OVER THE FORWARD PORTION OF THE PROJECT FIRE SPACE-VEHICLE CONFIGURATION AT MACH NUMBERS FROM 0.25 TO 0.60, William P. Henderson, February 1963 TN D 1618 PRESSURE DISTRIBUTIONS ON THREE RIGID WINGS SIMULATING PARAWINGS WITH VARIED CANOPY CURVATURE AND LEADING-EDGE SWEEP AT MACH NUMBERS FROM 2.29 TO 4.65, Paul G. Fournier, April 1963 TN D 1619 EFFECTS OF DISPLAY NOISE ON PILOT CONTROL OF THE TERMINAL PHASE OF SPACE RENDEZVOUS, Jack E. Pennington, August 1963 TN D 1620 EFFECT OF CROSS-SECTION SHAPE ON THE AERODYNAMIC CHARACTERISTICS OF BODIES AT MACH NUMBERS FROM 2.50 TO 4.63, Dennis E. Fuller, David S. Shaw, and Donald L. Wassum, March 1963 TN D 1621 A 6-1NCH SUBSONIC HIGH-TEMPERATURE ARC TUNNEL FOR STRUCTURES AND MATERIAL TESTS, Ronald D. Brown and L. Ross Levin, April 1963 TN D 1622 REAL-GAS EFFECTS ON HYPERSONIC NOZZLE CONTOURS WITH A METHOD OF CALCULATION, Charles B. Johnson, Lillian R. Boney, James C.

Ellison, and Wayne D. Erickson, April 1963 TN D 1623 A PARAMETRIC INVESTIGATION OF THE LUNAR-ORBIT-RENDEZVOUS SCHEME, David F. Thomas and John D. Bird, April 1963 TN D 1624 INVESTIGATION OF THE SKID-ROCKER LANDING CHARACTERISTICS OF SPACECRAFT MODELS, Sandy M. Stubbs, April 1963 TN D 1625 THEORETICAL STABILITY ANALYSIS OF SKID-ROCKER LANDINGS OF SPACE VEHICLES, Robert W. Fralich and Edwin T. Kruszewski, April 1963 EXPERIMENTAL PRESSURES ANDTURBULENT HEAT-TRANSFER COEFFICIENTS TN D 1626 ASSOCIATED WITHSINUSOIDAL PROTURBERANCES ONA FLATPLATE AT A MACH NUMBER OF 3, Charles P. Shore, Sidney C. Dixon, and George E. Griffith, March 1963 TN D 1627 ANALYSIS OF THEEFFECT OF ALTIMETER-SYSTEM ACCURACY ONCOLLISION PROBABILITY, William Gracey, March 1963 TN D 1628 PRESSURE ANDHEAT-TRANSFER MEASUREMENTS ONTHEFLATFACEOFA BLUNTED i0 ° HALF-CONE BODY (SEMIDISK)AT A MACH NUMBER OF 6.15, P. Calvin Stainback, May 1963 TN D 1629 SURFACE PRESSURE DISTRIBUTIONS INDUCED ONA FLATPLATEBYA COLD AIR JET ISSUINGPERPENDICULARLY FROM THEPLATEANDNORMAL TOA LOW-SPEED FREE-STREAM FLOW, Raymond D. Vogler, March 1963 TN D 1630 OFF-DESIGN AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS 1.61 AND 2.20 OF A SERIES OF HIGHLY SWEPT ARROW WINGS DESIGNED FORMACH NUMBER 2.0 EMPLOYING VARIOUS DEGREES OF TWISTANDCAMBER, Wilbur D. Middleton and Russell B. Sorrells, March 1963 TN D 1631 SIMILITUDEIN THERMAL MODELS OF SPACECRAFT, S. Katzoff, April TN D 1632 AN EXTENSION OF ESTIMATED HYPERSONIC FLOW PARAMETERS FORHELIUM AS A REALGAS,WayneD. Erickson, April 1963 TN D 1635 AN EXPERIMENTAL STUDY OF THEBEHAVIOR OF SPHERES ABLATING UNDER CONSTANT AERODYNAMIC CONDITIONS, Robert R. Howell, April 1963 TND 1636 A THEORETICAL STUDY OF THEMOTION OF AN IDEALIZED PLASMA RING THROUGH VARIOUS TRAVELING-MAGNETIC-WAVE PLASMA ACCELERATORS, Clarence W. Matthews, May 1963 TND 1637 QUALITATIVE EVALUATION OF EFFECT OFHELICOPTER ROTOR-BLADE TIP VORTEX ONBLADE AIRLOADS, JamesScheimanand Leroy H. Lundi, May 1963 TND 1639 ORBITAL ERROR ANALYSIS OF THESCOUT RESEARCH VEHICLE,C. H.

Woodling, Jarrell R. Elliott, and Paul J. Stull, May 1963 TN D 1640 MEASUREMENTS OF FLOW ANGLES IN VICINITY OF TWO LIFTING FOREBODY CONFIGURATIONS AT A MACH NUMBER OF 2.01, Odell A. Morris and Francis E. McLean,May 1963 TN D 1641 CROSS SECTIONS OF TEMPERATURE, PRESSURE, ANDDENSITY NEAR THE 80THMERIDIAN WEST,Orvel E. Smith, William M. McMurray, and Harold L. Crutcher, May 1963 TN D 1642 ONA CONSISTENT SYSTEM OF ASTRODYNAMIC CONSTANTS, Helmut G. L.

Krause, July 1963 CALCULATED RESULTS FORTHETRANSIENT HEATING ANDMELTING PROCESS TN D 1643 OF GLASS SHIELDS WITHVARIOUS MATERIAL PROPERTIES AT THESTAG- NATION POINTOFA RE-ENTERING ICBM, John D. Warmbrod,May 1963 ASCENT FROM THELUNAR SURFACE, Rowland E. Burns and Larry G.

TND 1644 Singleton, June 1963 SIMULATOR STUDY OF PRECISE ATTITUDE STABILIZATION OF A MANNED TND 1645 SPACECRAFT BYTWINGYROS ANDPULSE-MODULATED REACTION JETS, ArmandoE. Lopez and Jack W. Ratcliff, September1964 STATIC AERODYNAMIC CHARACTERISTICS OF A SHORT BLUNT i0 ° SEMI- TN D 1648 VERTEX ANGLE CONE AT A MACH NUMBER OF 15 IN HELIUM,Melvin J. Fohrman, February 1963 A FLIGHTEVALUATION OF I T_AR LANDING TRAJECTORIES USING A JET TN D 1649 VTOL TEST VEHICLE, L. Stewart Rolls and Fred J. Drinkwater III, February 1963 AERODYNAMIC CHARACTERISTICS OF A LARGE-SCALE MODEL WITH TWO TND 1650 HIGH DISK-LOADING FANS MOUNTED IN THE WING, David H. Hickey and Leo P. Hall, February 1963 THEORETICAL INVESTIGATION OF UNSTEADY DIFFUSION WITH RECOMBINA- TN D 1651 TION IN A TERNARY MIXTURE OF DIATOMIC MOLECULES, DISSOCIATED ATOMS, AND AN INERT GAS, Walter A. Reinhardt, February 1963 TN D 1652 ORBITS RETURNING FROM THE MOON TO A SPECIFIED GEOGRAPHIC LANDING AREA, Luigi S. Cicolani, April 1963 TWO SIGHTING PROBLEMS ASSOCIATED WITH SEXTANT TYPE MEASUREMENTS TN D 1653 FOR SPACE NAVIGATION: THE EFFECT OF FIELD OF VIEW ON STAR FIELD IDENTIFICATION, Daniel M. Hegarty. PRELIMINARY MEASUREMENTS OF THE ACCURACY OF MANUAL OPTICAL SIGHTING AT THE CENTER OF A PLANETARY DISK, Marvin H. Thigpen, April 1963 VARIATIONAL APPROACH TO THE CALCULATION OF CHARGE EXCHANGE CROSS TN D 1654 SECTIONS FOR ADIABATIC COLLISIONS, Frederick E. Alzofon and Fred C. Witteborn, May 1963 TN D 1655 PREDICTION OF VELOCITY REQUIREMENTS FOR MINIMUM TIME ABORTS FROM THE MIDCOURSE REGION OF A LUNAR MISSION, Robert B. Merrick and George P. Callas, April 1963 TN D 1656 ON THE EMPIRICAL CORRELATION OF CRITICAL BOILING HEAT FLUX FOR CHANNELS OF VARIOUS CROSS SECTIONS AND ORIENTATION, Uwe H.

von Glahn, June 1963 TN D 1657 CHARGE-EXCHANGE EFFECTS ON THE ACCELERATOR IMPINGEMENT OF AN ELECTRON-BOMBARDMENT ION ROCKET, William R. Kerslake, May 1963 TN D 1659 EXPERIMENTAL EVALUATION OFDIRECT-CURRENT LOW-PRESSURE PLASMA SOURCE, Stanley Domitz, April 1963 TN D 1660 A VARIATIONAL METHOD FORTHEOPTIMIZATION OF INTERPLANETARY ROUND-TRIP TRAJECTORIES, John S. MacKayand Leonard G. Rossa, March 1963 TN D 1661 DESIGN ANDOPERATIONAL PERFORMANCE OFA 150-KILOWATT SODIUM FLASH-VAPORIZATION FACILITY, Landon R. Nichols, Charles H.

Winzig, Stanley M. Nosek, and Louis J. Goldman,May 1963 TND 1662 THERMOLUMINESCENT SPECTRA OF SODIUM CHLORIDE ANDHYDROXIDE- FREESODIUM CHLORIDE IRRADIATED WITH40-MEVALPHA PARTICLES, JamesA. Partridge, April 1963 TN D 1663 PERFORMANCE OF ELECTRICAL-RESISTANCE STRAINGAGES AT CRYOGENIC TEMPERATURES, Albert Kaufman, March 1963 TN D 1664 FORMULATION ANDDIGITAL CODING OF APPROXIMATE HYDROGEN PROPER- TIES FORAPPLICATION TO HEAT-TRANSFER ANDFLUID-FLOW COMPUTA- TIONS,David P. Harry III, May 1963 TN D 1665 NUMERICAL EVALUATION OF ION-THRUSTOR OPTICS,Vladimir Hamza and EdwardA. Richley, May 1963 TN D 1669 GODDARD SPACE FLIGHTCENTER CONTRIBUTIONS TO THECOSPAR MEETING MAY1962, Goddard Space Flight Center, May 1963 TN D 1670 A MODEL OF THEQUIETIONOSPHERE, J. Carl Seddon, February 1963 TN D 1671 THECHARACTERISTICS OF DISTANT COMETS, Bertram Donn, March 1963 TN D 1672 ONTHEDESIGN OF PFMTELEMETRY ENCODERS, H. D. White, Jr., June 1964 TN D 1673 A SURVEY OFLARGE SPACE CHAMBERS, R. T. Hollingsworth, April TN D 1674 THEMAGNETIC FIELD OF THEQUIET-TIME PROTON BELT, Syun-lchi Akasofu, Joseph C. Cain, and Sidney Chapman, March 1963 TND 1675 SEPTEMBER 26, 1960 SOLAR COSMIC RAYEVENT,C. E. Fiehtel, D. A. Kniffen, and K. W. Ogilvie, January 1963 TND 1676 ANALYTICAL THEORY OFTHESTRETCH YO-YO FORDE-SPINOF SATELLITES_ Joseph V. Fedor, April 1963 TN D 1677 A MAGNETIC CORE VOLTAGE-TO-FREQUENCY CONVERTER, Stephen Paull, February 1963 A LOGICAL NETMECHANIZATION FORTIME-OPTIMAL REGULATION, F. B.

TN D 1678 Smith, Jr., December1962 TND 1679 ONTHEANOMALOUS COMPONENT OF LOW-ENERGY GEOMAGNETICALLY TRAPPED PROTONS, A. M. Lenchek, February 1963 TN D 1680 DEMODULATION OFWIDE-BAND FREQUENCY MODULATION BY A PHASE-LOCK TECHNIQUE, Richard C. Booton, Jr., June 1964 TN D 1681 MECHANICAL IMPEDANCE STUDY OF THEX-259 ROCKET MOTOR, Raymond G. Hartenstein and William G. Elsen, June 1963 TND 1682 THECOLLAPSE PHASE OF EARLY SOLAR EVOLUTION, A. G. W. Cameron, January 1963 TN D 1684 THELOW FREQUENCY POWER SPECTRUM OF COSMIC-RAY VARIATIONS DURING IGY, David Stern, March 1963 THEORIGINOFATMOSPHERIC XENON, A. G. W. Cameron, February 1963 TN D 1685 NOTE ONTHETHICKNESS OFTHEHELIUMION LAYER,S. J. Bauer, TN D 1686 March 1963 TND 1687 THEARTIFICIAL RADIATION BELTMADE ONJULY9, 1962, Wilmot N.

Hess, April 1963 HYDROMAGNETIC WAVE PROPAGATION IN A CONSTANT DIPOLEMAGNETIC TN D 1689 FIELD, John Carstoiu, December1962 TN D 1693 A DETECTOR FORLOW ENERGY GAMMA-RAY ASTRONOMY EXPERIMENTS, K. J.

Frost and E. D. Rothe, March 1963 PRELIMINARY MEASUREMENTS OF TEMPERATURES ANDWINDS ABOVE 50 KM TN D 1694 OVER WALLOPS ISLAND,VIRGINIA, William Nordberg and Wendell Smith, March 1963 APPARATUS FORTHEMEASUREMENT OF TRANSPORT PROPERTIES OF POLAR TN D 1695 SEMICONDUCTORS, Martin M. Sokoloski and Felix E. Geiger, March TN D 1696 NEUTRONS IN SPACE, Wilmot N. Hess, February 1963 SATELLITE-TRACKING CHARACTERISTICS OF THEX-Y MOUNT FORDATA TND 1697 ACQUISITION ANTENNAS, Andrew J. Rolinski, Donald J. Carlson, and Robert J. Coates, June 1964 EXPLORER XII SATELLITE INSTRUMENTATION FORTHESTUDY OF THE TN D 1698 ENERGY SPECTRUM OF COSMIC RAYS,U. D. Desai, R. L. Van Allen, and G. Porreca, May 1963 TN D 1699 NIKE APACHE PERFORMANCE HANDBOOK, Reed B. Jenkins, March 1963 TN D 1700 PROTONS FROM 0.I TO 5 MEV AND ELECTRON OF 20 KEV AT 12 EARTH RADII DURING THE SUDDEN COMMENCEMENT ON SEPTEMBER 30, 1962, R. A. Hoffman, L. R. Davis, and J. M. Williams, March 1963 TN D 1701 PERIODIC ORBITS FOR MOON PROBES, Su-Shi Huang, February 1963 TN D 1702 NONADIABATIC THEORY OF ELECTRON-HYDRO SCATTERING, PART II, A.

Temkin and E. Sullivan, July 1963 TN D 1703 HYDROMAGNETIC STAGNATION-POINT BOUNDARY LAYER WITH ARBITRARY PRESSURE GRADIENTS AND MAGNETIC FIELD, Willis H. Braun, May 1963 TN D 1704 A STEADY-STATE, STAGNATION-POINT, HEAT-TRANSFER-RATE MEASURING DEVICE, George Glawe, Lloyd N. Krause, and Robert C. Johnson, May 1963 TN D 1705 PRELIMINARY INVESTIGATION OF PARTICLE-SUBSTRATE BON_ING OF PLASMA-SPRAYED MATERIALS, Salvatore J. Grisaffe and William Spitzig, September 1963 TN D 1709 PRELIMINARY EXPERIMENTAL INVESTIGATION OF FREQUENCIES AND FORCES RESULTING FROM LIQUID SLOSHING IN TOROIDAL TANKS, Irving E.

Sumner, June 1963 TN D 1711 NUMERICAL SOLUTION OF AXIALLY SY}_ETRIC POISSON EQUATION; THEORY AND APPLICATION TO ION-THRUSTOR ANALYSIS. Vladimir Hamza, APPENDIX C: IBM 7090 ION-THRUSTOR FORTRAN CODE AND BLOCK DIAGRAM, Carl D. Bogart, May 1963 TN D 1712 EXPERIMENTAL INVESTIGATION OF THE SLOSH-DAMPING EFFECTIVENESS OF POSITIVE-EXPULSION BAGS AND DIAPHRAGMS IN SPHERICAL TANKS, Andrew J. Stofan and Irving E. Sumner, June 1963 TN D 1713 A RADIATION VIEW OF HURRICANE ANNA FROM THE TIROS III METEORO- LOGICAL SATELLITE, W. R. Bandeen, B. J. Conrath, W. Nordberg, and H. P. Thompson, April 1963 TN D 1714 PORTABLE INTEGRATING SPHERE FOR MONITORING REFLECTANCE OF SPACE- CRAFT COATINGS, W. B. Fussell, J. J. Trio]o, and F. A. Jerozal, April 1963 TN D 1715 A VACUUM ULTRAVIOLET PHOTOIONIZATION DETECTOR, A. K. Stober, R. Scolnik, and J. P. Hennes, March 1963 TN D 1716 A DYNAMIC THERMAL VACUUM TECHNIQUE FOR MEASURING THE SOLAR ABSORP- TANCE AND THERMAL _{ITTANCE OF SPACECRAFT COATINGS, W.B. Fussell, J. J. Triolo, and J. H. Henninger, March 1963 ENERGY SPECTRUM OF ELECTRONS IN THEOUTER RADIATION BELT, Wilmot TND 1717 N. IIess and John A. Poirier, March 1963 ULTRAVIOLET PHOTODETECTORS, Lawrence Dunkelman,August 1963 TN D 1718 THESOUTHERN SKYSURVEY PAYLOAD, Richard M. Windsor, February TN D 1719 ELECTRON-HYDROGEN PHASE SHIFTSJUSTBELOW THEINELASTIC THRES- TN D 1720 HOLD,Aaron Temkin, May 1963 THEEFFECT OFREFRACTION ONTHESETTING SUNAS SEEN FROM SPACE TN D 1721 IN THEORY ANDOBSERVATION, Winifred Sawtell Cameron,Lt. Col.

John H. Glenn, Lt. Comdr. M. Scott Carpenter, and John A.

O'Keefe, May 1963 RESULTS OF MICROMETEORITE PENETRATION EXPERIMENT ON THE EXPLORER TND 1722 VII SATELLITE (1959 IOTA), H. E. LaGow and L. Secretan, ADril CALIBRATIONS AND COMPARISONS OF PREgSURE-TYPE AIRSPEED-ALTITUDE TND 1724 SYSTEMS OF THE X-15 AIRPLANE FROM SUBSONIC TO HIGH SUPERSONIC SPEEDS, Terry J. Larson and Lannie D. Webb, February 1963 TN D 1725 TECHNIQUES USED TO MEASURE THE HYDRAULIC CHARACTERISTICS OF THE NASA PLUM BROOK REACTOR, Joseph M. Savino and Chester D. Lanzo, August 1963 EXPERIMENTAL INVESTIGATION OF ROCKET-ENGINE ABLATIVE-MATERIAL TN D 1726 PERFORMANCE AFTER POSTRUN COOLING AT ALTITUDE PRESSURES, R.

James Rollbuhler, June 1963 TND 1727 EXPERIMENTAL EVALUATION OF LIQUID-FLUORINE SYSTEM COMPONENTS, Richard L. DeWitt and Harold W. Schmidt, June 1963 TN D 1728 RATE OF LIQUID JET BREAKUP BY A TRANSVERSE SHOCK WAVE, Gerald Morrell, May 1963 CALIBRATION OF A THERMAL-CONDUCTIVITY VACUUM GAGE IN THE RANGE TN D 1729 OF 10 -4 TO 1 TORR BY MEANS OF A VOLUME-RATIO CALIBRATION SYSTEM, Raymond Holanda, June 1963 THE N-BODY CODE - A GENERAL FORTRAN CODE FOR THE NIDIERICAL TN D 1730 SOLUTION OF SPACE MECHANICS PROBLEMS ON AN IBM 7090 COMPUTER, William C. Strack and Vearl N. Huff, November 1963 LEAK-RATE TESTING OF THE NASA PLUM BROOK REACTOR CONTAINMENT TN D 1731 VESSEL, Edward G. Keshock and Claude E. DeBogdan, July 1963 POSSIBLE EFFECTS OF NONUNIFORM FLOWS ON PERFORMANCE OF ELECTRO- TND 1732 THERMAL THRUSTORS, John R. Jack and John W. Schaefer, June 1963 TN D 1733 NEUTRALIZER TESTS ON A FLIGHT-MODEL ELECTRON-BOMBARDMENT ION THRUSTOR, Robert F. Kemp, J. M. Sellen, Jr. and Eugene V.

Pawlik, July 1963 TN D 1734 DISPERSION AND DAMPING OF LONGITUDINAL ELECTRON OSCILLATIONS IN THERMAL PLASMAS, James F. Morris, June 1963 TN D 1735 TABLE OF 2FI (a,b;c;z) FOR a = 0(1/2)7, b = 0(1/2)7, AND c = 0(1/2)5/2 WITH COMMENTS ON CLOSED FORMS OF 2FI (a,b;c;z), K. David Steidley, September 1963 TN D 1736 THE YIELD OF NITRIC OXIDE FROM PREMIXED FLAMES OF HYDROGEN _D HYDROCARBONS WITH NITROUS OXIDE, Burton D. Fine and Albert Evans, May 1963 TN D 1737 A GENERAL IBM 704 OR 7090 COMPUTER PROGRAM FOR COMPUTATION OF CHEMICAL EQUILIBRIUM COMPOSITIONS, ROCKET PERFORMANCE, AND CHAPMAN-JOUGOET DETONATIONS. SUPPLEMENT I - ASSIGNED AREA RATIO PERFORMANCE, Sanford Gordon and Frank J. Zeleznik, October 1963 TN D 1738 EFFECTS OF REGENERATIVE AND RADIATION COOLING ON PERFORMANCE OF ELECTRO-THERMAL THRUSTORS, John W. Schaefer and John R.

Jack, November 1963 TN D 1739 COMPATIBILITY OF CESIUM VAPOR WITH SELECTED MATERIALS AT TEMPERATURES TO 1200 ° F., Joseph M. Lamberti and Neal T.

Saunders, August 1963 TN D 1740 A SIMPLIFIED METHOD OF DETERMINING THE ELASTIC STATE OF THERMAL STRESS IN A THIN FLAE PLATE OF FINITE DIMENSIONS, Ernest Roberts, Jr., and Alexander Mendelson, August 1963 TN D 1741 THEORETICAL ELASTIC STRESS DISTRIBUTIONS IN CASSINIAN DOMES, David A. Spera and Robert H. Johns_ July 1963 TN D 1742 A COMPARATIVE ANALYSIS OF CONVECTIVE HEAT TRANSFER IN A NUCLEAR ROCKET NOZZLE, Harvey E. Neumann and Paula J. Bettinger, August 1963 TN D 1743 COMPARISON OF EXPERIMENTAL TO PREDICTED HEAT TRANSFER IN A BELL- SHAPED NOZZLE WITH UPSTREAM FLOW DISTURBANCES, Anthony Fortini and Robert C. Ehlers, August 1963 TN D 1744 THERMAL DECOMPOSITION OF SOME LINEAR PERFLUOROALKANES IN AN INCONEL BOMB, William L. Fielder, July 1963 TN D 1745 ON A MODIFICATION OF HANSEN'S LUNAR THEORY, Peter Musen, June ION SHEATH EFFECTS NEAR ANTENNAS RADIATING WITHIN THE IONOSPHERE, TN D 1746 H. A. Whale, May 1963 VEHICLE TECHNOLOGY CONSIDERATIONS FOR A SOLAR PROBE, John A.

TN D 1747 Foschetti, April 1963 EXPERIENCE IN THERMAL-VACUUM TESTING EARTH SATELLITES AT GODDARD TN D 1748 SPACE FLIGHT CENTER, A. R. Timmins and K. L. Rosette, August 1963 TN D 1749 ENERGETIC PARTICLES IN THE INNER VAN ALLEN BELT, Wilmot N. Hess, July 1963 ON THE MOTION OF A 24-HOUR SATELLITE, Peter Musen and Ann E.

TN D 1750 Bailie, June 1963 ELECTRON DENSITY DISTRIBUTION IN THE UPPER F-REGION, S. Chandra, TN D 1751 March 1963 ON THE SECOND-ORDER SOLUTION OF ARTIFICIAL SATELLITE THEORY TN D 1752 WITHOUT AIR DRAG, Theodore L. Felsentreger, September 1964 POWER TRANSISTOR COOLING IN A SPACE ENVIRONMENT, James E. A.

TN D 1753 John and John J. Hilliard, July 1963 TN D 1754 CERENKOV-SCINTILLATION COUNTER MEASUREMENTS OF THE LIGHT, MEDIUM, AND HEAVY NUCLEI IN THE PRIMARY COSMIC RADIATION FROM SUNSPORT MINIMUM TO SUNSPOT MAXIMUM, F. B. McDonald and W. R. Webber, July 1963 SOME ASPECTS OF STRATOSPHERIC CIRCULATION DERIVED FROM METEORO- TN D 1755 LOGICAL ROCKET FIRINGS OVER THE UNITED STATES DURING THE WINTER OF 1961, Mohammad Rahmatullah, July 1963 TN D 1756 SATELLITE OBSERVATIONS OF THE EQUATORIAN IONOSPHERE, L. J.

Blumle, June 1963 A SCINTILLATION COUNTER TELESCOPE FOR CHARGE AND MASS IDENTIFI- TN D 1757 CATION OF PRIMARY COSMIC RAYS, D. A. Bryant, G. H. Ludwig, and F. B. McDonald, August 1963 THE USE OF SOLID CIRCUITS IN SATELLITE INSTRUMENTATION, Edgar TN D 1758 G. Bush, July 1964 SPECTRALLY SELECTIVE PHOTODETECTORS FOR THE MIDDLE AND VACUUM TN D 1759 ULTRAVIOLET, Lawrence Dunkelman, Walter B. Fowler, and John P. Hennes, May 1963 TN D 1760 THE EXCITATION OF ELECTROACOUSTIC WAVES BY ANTENNAS IN THE IONOSPHERE, H. A. Whale, June 1963 TND 1761 ONTHEBREAKDOWN VOLTAGES OF SOME ELECTRONEGATIVE GASES AT LOW PRESSURES, Stefan Schreier, June 1963 TND 1762 THEMAGNETIC FIELDOF THERADIATION BELTS,Syun-lchi Akasofu and Joseph C. Cain, June 196_ TN D 1764 A STUDY OF THEHYDROGEN, HELIUM,ANDHEAVY NUCLEIIN THE NOVEMBER 12, 1960, SOLAR COSMIC RAYEVENT,S. Biswas, C. E.

Fichtel, and D. E. Guss, May 1963 TN D 1765 AN EMERGENCY MIDCOURSE NAVIGATION PROCEDURE FORA SPACE VEHICLE RETURNING FROM THEMOON, C. DeweyHavill, March 1963 TN D 1766 WIND-TUNNEL TESTS OFTWO VTOLPROPELLERS IN DESCENT, Paul F.

Yaggy and Kenneth W. Mort, March 1963 TND 1767 SPRAY EJECTED FROM THELUNAR SURFACE BYMETEOROID IMPACT, Donald E. Gault, EugeneM. Shoemaker,and Henry J. Moore, April 1963 TND 1768 AN EXPERIMENTAL EVALUATION OF AERODYNAMIC DAMPING MOMENTS OF CONES WITHDIFFERENT CENTERS OF ROTATION, William R. Wehrend, Jr., March 1963 TND 1769 AN INVESTIGATION OF FLOW VISUALIZATION TECHNIQUES IN HELIUM AT MACH NUMBERS OF 15 AND20, Charles E. Duller, April 1963 TND 1770 SOME POSSIBILITIESFORDETERMINING THECHARACTERISTICS OFTHE ATMOSPHERES OFMARS ANDVENUS FROM GAS-DYNAMIC BEHAVIOR OF A PROBE VEHICLE,Alvin Seiff, April 1963 TN D 1774 AERODYNAMIC CHARACTERISTICS OF A FULL-SCALE PROPELLER TESTED WITHBOTH RIGID ANDFLAPPING BLADES ANDWITHCYCLIC PITCH CONTROL, Kenneth W. Mort and Paul F. Yaggy, May 1963 TN D 1775 EFFECT OF LIFT ONSEPARATION DISTANCE ANDLOADS FORAN ABORTING VEHICLE AT MAXIMUM DYNAMIC PRESSURE OF A LUNAR MISSION,Joseph J. Janos and John R. Unangst, April 1963 TN D 1776 AERODYNAMIC CHARACTERISTICS OF A FLEXIBLE-CANOPY PARAGLIDER MODEL AT A MACH NUMBER OF 4.5 FORANGLES OFATTACK TO 360° ANDSIDESLIPANGLES FROM 0° TO 90° , DeweyE. Wornomand Robert T. Taylor, April 1963 TN D 1778 ESTIMATES OF ATTENUATION ANDREFLECTION OFTELEMETERING SIGNALS BY IONIZEDFLOW FIELDSSURROUNDING TYPICAL REENTRY BODIES, Anthony J. Russo, Jr., August 1963 TND 1779 LOW-SPEED WIND-TUNNEL INVESTIGATION OFAN ANNULAR-JET CONFIGURA- TION IN GROUND PROXIMITY, JamesH. Otis, Jr. and Kenneth W.

Goodson,April 1963 TN D 1780 GEOMETRICAL CHARACTERISTICS OF LUNAR ORBITS ESTABLISHED FROM EARTH-MOON TRAJECTORIES, Robert H. Tolson, April 1963 TN D 1781 EFFECTS OF NOSE BLUNTNESS, FINENESS RATIO, CONE ANGLE,AND MODEL BASEONTHESTATICAERODYNAMIC CHARACTERISTICS OF BLUNT BODIES AT MACH NUNBERS OF 1.57, 1.80, AND2.16 ANDANGLES OF ATTACK UP TO 180° , David S. Shaw, Dennis E. Fuller, and C.

Donald Babb, May'1963 TN D 1783 DIRECT VELOCITY MEASUREMENTS IN LOW-DENSITY PLASMA FLOWS, W. D.

Beasley, J. D. Brooks, and R. L. Barger, May 1963 TN D 1786 STATICAERODYNAMIC CHARACTERISTICS OF A THREE-STAGE ROCKET VEHICLE HAVING VARIOUS FIN CONFIGURATIONS AT LOWSUBSONIC MACH NUMBERS ANDANGLES OFATTACK UP TO 28°, Clarence A. Brown, Jr., and LawrenceE. Putnam, April 1963 TN D 1787 HELIUM CONCENTRATIONS DOWNSTREAM OFA VENTEXHAUSTING HELIUM AT SONIC VELOCITY INTOA SUPERSONIC STREAM OF AIR AT MACH NUMBERS OF 3.51 AND4.50, Robert L. Stallings, Jr. and Paul W. Howard, May 1963 TN D 1789 AERODYNAMIC CHARACTERISTICS OF TOWED SPHERES, CONICAL RINGS,AND CONES USED AS DECELERATORS AT MACH NUMBERS FROM 1.57 TO 4.65, Nickolai Charczenko, April 1963 TN D 1790 HEAT-TRANSFER ANDPRESSURE DISTRIBUTIONS AT MACH NUMBERS OF 6.0 AND9.6 OVER TWO REENTRY CONFIGURATIONS FORTHEFIVE-STAGE SCOUT VEHICLE,Pau± F. Holloway and JamesC. Dunavant, May 1963 TN D 1791 TABULATED VALUES OF BOND DISSOCIATION ENERGIES, IONIZATION POTENTIALS, ANDELECTRON AFFINITIES FORSOME MOLECULES FOUND IN HIGH-TEMPERATURE CHEMICAL REACTIONS, Charles J. Schexnayder, Jr., May 1963 TND 1793 CENTER-LINE PRESSURE DISTRIBUTIONS ONTWO-DIMENSIONAL BODIES WITHLEADING-EDGE ANGLES GREATER THAN THATFORSHOCK DETACHMENT AT MACH NUMBER 6 ANDANGLES OFATTACK UP TO 25° , Theodore J.

Goldberg, George C. Ashby, Jr., and JamesG. Hondros, June 1963 TN D 1795 A COMPARISON OF EXPERIMENTAL ANDTHEORETICAL RESULTS FORTHE COMPRESSIBLE TURBULENT-BOUNDARY-LAYER SKIN FRICTION WITHZERO PRESSURE GRADIENT, John B. Peterson, Jr., March 1963 TN D 1797 MOVING-COCKPIT-SIMULATOR STUDY OF PILOTED ENTRIES INTOTHE EARTH'S ATMOSPHERE FORA CAPSULE-TYPE VEHICLE AT PARABOLIC VELOCITY,John W. Young and Lawrence E. Barker, Jr., May 1963 TN D 1799 SOME EFFECTS OF SIMULATED BENDING ANDFOURTH-STAGE SIZE ONLOCAL PRESSURES ANDNORMAL FORCE DISTRIBUTIONS OF A MODEL OFA SCOUT CONFIGURATION AT A MACH NUMBER OF 3.10, Byron M. Jaquet, May TN D 1800 AERODYNAMIC INTERACTION EFFECTS AHEAD OF RECTANGULAR SONIC JETS EXHAUSTING PERPENDICULARLY FROM A FLATPLATEINTOA MACH NUMBER 6 FREESTREAM, David J. Romeo,May ].963 TN D 1802 FLIGHTOPERATING PROBLEMS ANDAERODYNAMIC ANDPERFORMANCE CHARAC- TERISTICS OF A FIXED-WING, TILT-DUCT,VTOLRESEARCH AIRCRAFT, Henry L. Kelley and Robert A. Champine,July 1963 TN D 1804 PERFORMANCE OFA PLUG NOZZLE HAVING A CONCAVE CENTRAL BASE WITH ANDWITHOUT TERMINAL FAIRINGS AT TRANSONIC SPEEDS, Charles E.

Mercer and Leland B. Salters, Jr., May 1963 TN D 1805 ERROR ANALYSIS OF SEVERAL METHODS OF DETERMINING VEHICLE POSITION IN EARTH-MOON SPACE FROM SIMULTANEOUS ONBOARD OPTICAL MEASUREMENTS, Harold A. Hamerand Alton P. Mayo, June 1963 TN D 1808 INVESTIGATION OF CATALYST BEDS FOR98-PERCENT-CONCENTRATION HYDROGEN PEROXIDE, Jack F. Runckel, ConardM. Willis, and Leland B. Salters, Jr., June 1963 TND 1809 AERODYNAMIC EFFECTS OF MODIFYING WINGINBOARD TRAILING-EDGE CAMBER OF A MODEL AT HIGHSUBSONIC SPEEDS, Richard J. Re, May TND 1810 VIBRATIONAL-NONEQUILIBRIUM FLOW OFNITROGEN IN HYPERSONIC NOZZLES, WayneD. Erickson, June 1963 TND 1811 LONGITUDINAL RANGE ATTAINABLE BY THECONSTANT-ALTITUDE VARIABLE- PITCHREENTRY MANEUVER INITIATEDAT VELOCITIES UPTO ESCAPE VELOCITY, E. Brian Pritchard, June 1963 TND 1812 A STUDY OF SOME TRANSITION MATRIX ASSUMPTIONS IN CIRCUMLUNAR NAVIGATION THEORY, RubenL. Jones and Alton P. Mayo, October TN D 1813 A STATISTICAL MODEL FORSYNTHETIC WINDPROFILES FORAEROSPACE VEHICLE DESIGN ANDLAUNCHING CRITERIA,Robert M. Henry, July 1963 TN D 1814 AN EXPERIMENTAL EVALUATION OFTHREE TYPES OFTHERMAL PROTECTION MATERIALS AT MODERATE HEATING RATES ANDHIGHTOTAL HEATLOADS, Andrew J. Chapman,July 1963 TN D 1815 INVESTIGATION OFA SEMISPAN TILTING-PROPELLER CONFIGURATION AND EFFECTS OF RATIOOF WING CHORD TO PROPELLER DIAMETER ONSEVERAL SMALL-CHORD TILTING-WING CONFIGURATIONS AT TRANSITION SPEEDS, Kenneth P. Spreeman,July 1963 TN D 1817 A METHOD FORDETERMINING THEPROPELLANT REQUIRED TO MAINTAIN AN EARTH ORBITAL VEHICLEIN A USEFUL ORBITBETWEEN TWO SPECIFIED ALTITUDE LIMITS, JamesJ. Buglia and John F. Newcomb, August TN D 1818 IN-FLIGHTAERODYNAMIC NOISEMEASUREMENTS ONA SCOUT LAUNCH VEHICLE,David A. Hilton, Emedio M. Bracalente, and Harvey H.

Hubbard, July 1963 TN D 1819 TABLES FORTHEINTEGRAL OF THECIRCULAR BIVARIATE NORMAL FREQUENCY FUNCTION, William L. Weaverand Kathleen C. Wicker, July 1963 TN D 1820 TRAJECTORY ENTRY CONDITIONS AT THELUNAR SPHERE OF INFLUENCE FORAPPLICATION TO DETAILED STUDIES OFNEAR-MOON TRAJECTORY ANDIMPACT CONDITIONS, Harold A. Hamerand Ward F. Hodge, July TN D 1825 GASCHROMATOGRAPHIC MEASUREMENT OF TRACE CONTAMINANTS IN A SIMULATED SPACE CABIN, Herbert C. McKee, John W. Rhoades, Ralph J. Wheeler, and H. P. Burchfield, March 1963 TN D 1830 THESIGNIFICANCE OF ATMOSPHERIC BALLISTICSIN ROCKET TECHNOLOGY, G. H. R. Reisig, July 1963 TN D 1834 ONTHEERROR PROPAGATION OF SOME INTERPOLATION FORMULAS FOR SECOND-ORDER DIFFERENTIAL EQUATIONS, Erwin Fehlberg, July 1963 TND 1840 GALVANOMAGNETIC EFFECTS IN POLYCRYSTALLINE MANY VALLEYSEMI- CONDUCTORS, John H. Marburger III, October 1963 TN D 1841 CHARACTERISTICS OF PASSIVE COMMUNICATION SATELLITES WITH LAMBERTIAN SURFACES, Herbert P. Raabe, September 1963 TN D 1842 EARTH REFLECTED SOLAR RADIATION INCIDENT UPON AN ARBITRARILY ORIENTED SPINNING FLATPLATE,Fred G. Cunningham,July 1963 TN D 1844 COSMIC-RAY-INDUCED STABLE ANDRADIOACTIVE NUCLIDES IN METEORITES, Michael E. Lipschutz, June 1963 TN D 1845 TEMPERATURE OF A GRAY BODY MOST CLOSELY FITTINGTHESOLAR EXTRA- TERRESTRIAL SPECTRUM, William B. Fussell and John B. Schutt, August 1964 TN D 1847 A REVIEW OF GEODETIC PARAMETERS, William M. Kaula, May 1963 TN D 1848 TESSERAL HARMONICS OF THEGRAVITATIONAL FIELD ANDGEODETIC DATUM SHIFTSDERIVED FROM CAMERA OBSERVATIONS OF SATELLITES, William M. Kaula, June 1963 POSITRON-HYDROGEN SCATTERING, Aaron Temkin, August 1963 TND 1849 TND 1850 THEINFRARED HORIZON OF THEPLANET EARTH,R. A. Hanel, W. R.

Bandeen, and B. J. Conrath, September1963 TND 1851 MASS SPECTROMETERIC INVESTIGATIONS OF THEATMOSPHERE BETWEEN i00 AND227 KILOMETERS ABOVE WALLOPS ISLAND,VIRGINIA, Edith Meadows-Reed and Charles R. Smith, August 1963 TND 1852 MANUAL PROCEDURE FORDETERMINING POSITION IN SPACE FROM ON- BOARD OPTICAL MEASUREMENTS, Harold A. Hamer, December1964 TND 1853 ACHIEVING SATELLITE RELIABILITYTHROUGH ENVIRONMENTAL TESTS, John C. New, July 1963 TN D 1854 A THEORETICAL BASISFORMECHANICAL IMPEDANCE SIMULATION IN SHOCK ANDVIBRATION TESTING OF ONE-DIMENSIONAL SYSTEMS, F. J.

On and R. O. Belsheim, August 1963 TND 1856 GROUND OPERATION EQUIPMENT FORTHEORBITING ASTRONOMICAL OBSERVATORY, E. J. Habib, A. G. Ferris, H. W. Cooper and R. L.

McConaughy, December1963 TND 1857 LARGE-SCALE WIND-TUNNEL TESTS OFDESCENT PERFORMANCE OFAN AIRPLANE MODEL WITHA TILT WING ANDDIFFERENTIAL PROPELLER THRUST, Wallace H. Deckert, V. Robert Page, and Stanley O.

Dickinson, October 1964 A CONTRIBUTION TO THETHEORY OF CRITICALINCLINATION OF CLOSE TND 1858 EARTH SATELLITES, Shinko Aoki, September 1963 TN D 1859 PERIODIC SOLUTIONS OF THERESTRICTED THREE BODY PROBLEM REPRESENTING ANALYTIC CONTINUATIONS OF KEPLERIAN ELLIPTIC MOTIONS, Richard F. Arenstorf, May ].963 TN D 1861 EXPERIMENTAL INVESTIGATION OF INSULATING REFRACTORY-METAL HEAT-SHIELD PANELS, Gregory R. Wichorek and Bland A. Stein, December1964 TN D 1862 RADIATION DOSIMETRY ABOARD THESPACECRAFT OF THEEIGHTH MERCURY-ATLAS MISSION(MA-8), Carlos S. Warren and William L.

Gill, August 1964 TN D 1863 THEDIGITAL TAPERECORDER ANALYZER, Joseph A. Sciulli, October TND 1864 FLUXPATTERNS RESULTING FROM FREE-MOLECULE FLOW THROUGH CON- VERGING ANDDIVERGING SLOTS,Thaine W. Reynolds and EdwardA.

Richley, October 1964 INVESTIGATION OF AIR DAMPING OF CIRCULAR ANDRECTANGULAR PLATES, TN D 1865 A CYLINDER, ANDA SPHERE, David G. Stephens and Maurice A.

Scavullo, April 1965 TND 1866 DESCRIPTION ANDPERFORMANCE OF THREE TRAILBLAZER II REENTRY RESEARCH VEHICLES, Reginald R. Lundstom, Allen B. Henning, and W. Ray Hook, December1964 A REVIEW OF PHOTOGRAPHY OF THEEARTH FROM SOUNDING ROCKETS AND TN D 1868 SATELLITES, Paul D. Lowman,Jr., December1964 BEND TRANSITION TEMPERATURE OFARC-CAST MOLYBDENUM ANDMOLY- TN D 1869 BDENUM - 0.5 -PERCENT-TITANIUM SHEET IN WORKED, RECRYSTALLIZED, ANDWELDED CONDITONS, John H. Sinclair, October 1964 TN D 1870 AN INVESTIGATION OF RESONANT, NONLINEAR, NONPLANAR FREESURFACE OSCILLATIONS OF A FLUID, R. E. Hutton, May 1963 EVALUATION OF INFRARED SPECTROPHOTOMETRY FORCOMPOSITIONAL TN D 1871 ANALYSIS OF LUNAR ANDPLANETARY SOILS, R. J. P. Lyon, April 1963 TN D 1874 DIRECTIONAL BEHAVIOR OF EMITTED ANDREFLECTED RADIANT ENERGY FROM A SPECULAR, GRAY,ASYMMETRIC GROOVE, John R. Howell and Morris Perimutter, August 1963 RESONANCE IN A COLD MULTICONSTITUENT PLASMA AT ARBITRARY ORIENTA- TN D 1875 TION TO THEMAGNETIC FIELD, Eli Reshotko, July 1963 TND 1877 EXPERIMENTAL INVESTIGATION OF CHEMICAL REGENERATION OF SURFACES IN SIMULATED THERMIONIC DIODES,Helmut F. Butze and Arthur L.

Smith, July 1963 TND 1878 EFFECT OF VARIABLE THERMAL PROPERTIES ONONE-DIMENSIONAL HEAT TRANSFER IN RADIATING FINS, Norbert O. Stockmanand John L.

Kramer, October 1963 TND 1879 THERMIONIC EMISSION FROM CESIUM-COATED ELECTROSTATIC ION THRUSTOR ELECTRODES, Thaine W. Reynolds and EdwardA. Richley, September 1963 AN EXPERIMENTAL INVESTIGATION OF CHEMICAL REACTION BETWEEN PRO- TND 1882 PELLANT TANK MATERIAL ANDROCKET FUELS OROXIDIZERS WHEN IMPACTED BY SMALL HIGH-VELOCITY PROJECTILES, Robert P. Dengler, August TND 1883 ANALYTICAL ANDEXPERIMENTAL STUDY OF POOL HEATING OF LIQUID HYDROGEN OVER A RANGE OF ACCELERATIONS, Robert W. Graham, Robert C. Hendricks, and Robert C. Ehlers, February 1965 TND 1884 LARGE-SCALE WIND-TUNNEL TESTS IN GROUND EFFECT OF A 35° SWEPT- BACK WINGJET TRANSPORT MODEL EQUIPPED WITHBLOWING BOUNDARY- LAYER-CONTROL TRAILING-ANDLEADING-EDGE FLAPS,Kiyoshi Aoyagi and David H. Hickey, May 1963 TN D 1885 STUDY OF THENONEQUILIBRIUM FLOW FIELD BEHIND NORMAL SHOCK WAVES IN CARBON DIOXIDE, John T. Howe, .John R. Viegas, and Yvonne S.

Sheaffer, June 1963 TN D 1886 METHOD OF ASYMPTOTIC EXPANSIONS FOR SINGULAR PERTURBATION PROB- LEMS, APPLICABLE TO VISCOUS FLOW OVER FLAT PLATE, E. Dale Martin, July 1963 TN D 1887 FULL-SCALE WIND-TUNNEL TESTS OF A MEDIUM-WEIGHT UTILITY HELI- COPTER AT FORWARD SPEEDS, John L. McCloud III, James C. Biggers, and Ralph L. Maki, May 1963 TN D 1889 THE INFLUENCE OF HEATING RATE AND TEST STREAM OXYGEN CONTENT ON THE INSULATION EFFICIENCY OF CHARRING MATERIALS, Nick S. Vojvodich and Ernest L. Winkler, July 1963 TN D 1890 MEASUREMENT OF THE HEAT TRANSFER TO BODIES OF REVOLUTION IN FREE FLIGHT BY USE OF A CATCHER CALORIMETER, Gary T. Chapman and Charles T. Jackson, Jr., July 1963 TND 1891 SOME FLIGHT CHARACTERISTICS OF A DEFLECTED SLIPSTREAM V/STOL AIRCRAFT, Howard L. Turner and Fred J. Drinkwater III, July TND 1892 COMBUSTION TESTS OF OXYGEN HYDROGEN-HELIUM MIXTURES AT LOADING PRESSURES UP TO 8,000 POUNDS PER SQUARE INCH, Max E. Wilkins and Robert J. Carros, October 1963 TND 1894 ON THE FLOW STRUCTURE WITHIN A CONSTANT PRESSURE COMPRESSIBLE TURBULENT JET MIXING REGION, W. L. Chow and H. H. Korst, April 1963 TN D 1896 THERMAL PERFORMANCE AND RADIO-FREQUENCY TRANSMISSIVITY OF SEVERAL ABLATION MATERIALS, Marvin B. Dow, Claud M. Pittman, and William F. Croswell, November 1964 TND 1898 COMPUTATION OF GENERAL PLANETARY PERTURBATIONS, PART I, Lloyd Carpenter, August 1963 TN D 1899 EXPERIMENTS FROM A SMALL PROBE WHICH ENTERS THE ATMOSPHERE OF MARS, R. A. Hanel, L. E. Richmyer, R. A. Stamptl, and W. G.

Stroud, December 1963 TN D 1900 THE PURPOSES OF ENVIRONMENTAL TESTING FOR SCIENTIFIC SATELLITES, John H. Boeckel, July 1963 3O8 TN D 1901 THEPLASMA INTERPLANETARY SPACE,L. Biermann, October 1963 TN D 1904 THEORETICAL CONSIDERATIONS FORA PRELIMINARY DESIGN OF A SOLAR CELLGENERATOR ONA SATELLITE,Bernard J. Saint-Jean, September1963 TN D 1905 APPLICATION OF INTEGRATED CIRCUITS TO TELEMETRY SYSTEMS, J. Michael Balderston, July 1964 TN D 1906 A THEORETICAL MODEL FORSUNSPOT COOLNESS, R.K. Jaggi, October TN D 1907 MODELS FORSTARS OFVERYLOW MASS,Shiv S. Kumar, October 1963 TN D 1908 FLIGHTSHOCK ANDVIBRATION DATAOF THEECHO A-12 APPLICATION VERTICAL TESTS(AVT-I ANDAVT-2), W. B. Tereniak and S. A.

Clevenson, October 1963 TN D 1909 EXPLORATION OF THEATMOSPHERE OFVENUS BYA SIMPLE CAPSULE, Rudolf A. Hanel, July 1964 TN D 1910 AN ANALYSIS OF TIROSII RADIATION DATARECORDED OVER NEW ZEALAND AT NIGHT,Lewis J. Allison, March 1964 TN D 1911 FLUORINE UPTAKE OF FLUOROCARBON GREASES, Patricia M. O'Donnel, December1964 TN D 1912 ACOUSTIC HEATING OF THEPOLAR NIGHTMESOSPHERE, Kaichi Maeda, November1963 TN D 1913 THENATIONAL AERONAUTICS ANDSPACE ADMINISTRATION TOPSIDE SOUNDER PROGRAM, L° J. Blumle, R. J. Fitzenreiter, and J. E.

Jackson, November1963 TND 1914 CORIOLIS EFFECTS IN COMBINED ENVIRONMENT TESTING,Joseph C.

Boyle, June 1964 TN D 1915 THEAUTOMATIC PICTURE TRANSMISSION (APT) TV CAMERA SYSTEM FOR METEOROLOGICAL SATELLITES, Rudolf A. Stampfl and William G.

Stroud, November1963 TN D 1916 LAUNCH ENVIRONMENT PROFILES FORSOUNDING ROCKETS ANDSPACE- CRAFT,W. J. Neff and R. A. Montes de Oca, January 1964 TND 1917 PROBLEMS IN THECONSTRUCTION OFA SPACE ENVIRONMENT SIMULATOR, Dana S. Cope, March 1964 TND 1924 ROUGH-AIR EFFECT ONCREW PERFORMANCE DURING A SIMULATED LOW- ALTITUDE HIGH-SPEED SURVEILLANCE MISSION,GeorgeJ. Hurt, Jr., August 1963 TND 1925 AN ANALYSIS OFVGANDVGHOPERATIONAL DATAFROM A TWIN-ENGINE TURBOPROP TRANSPORT AIRPLANE, Paul A. Hunter and Walter G.

Walker, July 1963 TND 1926 TRANSONIC INVESTIGATION OF THEEFFECTS OF NOSE BLUNTNESS, FINENESS RATIO,CONE ANGLE,ANDBASESHAPE ONTHESTATIC AERODYNAMIC CHARACTERISTICS OF SHORT, BLUNT CONES AT ANGLES OF ATTACK TO 180° , Cuyler W. Brooks, Jr. and Charles D.

Trescot, Jr., August 1963 TND 1927 A COMPARISON OF THETHEORETICAL ANDEXPERIMENTAL STAGNATION- POINTHEATTRANSFER IN AN ARC-HEATED SUBSONIC STREAM, Ronald D. Brown, June 1964 TND 1928 ARREST OFA MOVING MASS BYAN ATTACHED MEMBRANE, Manuel Stein, July 1963 STATIC AERODYNAMIC CHARACTERISTICS OF THREE ROCKET-VEHICLE TND 1929 CONFIGURATIONS AT MACH NUMBERS FROM 1.80 TO 4.63 INCLUDING SOME EFFECTS OF FIN SIZE, FIN CANT,ANDAUXILIARY ROCKET MOTORS, Dennis E. Fuller and Gerald V. Foster, July 1963 TN D 1933 EFFECT OFFABRICATION-TYPE SURFACE ROUGHNESS ONTRANSITION ONOGIVE-CYLINDER MODELS AT MACH NUMBERS OF 1.61 AND2.01, Paul W. Howardand K. R. Czarnecki, July 1963 TND 1936 TRAILBLAZER I REENTRY-BODY WIND-TUNNEL TESTS AT A MACH NUMBER OF 6.7 WITHTHEORETICAL AERODYNAMICS ANDA LIMITED DYNAMIC ANALYSIS, Herbert R. Schippell, July 1963 TND 1937 LOW-SPEED INVESTIGATION OF CABLE TENSION ANDAERODYNAMIC CHARACTERISTICS OFA PARAWING ANDSPACECRAFT COMBINATION, William C. Sleeman, Jr., July 1963 TND 1938 A TRAJECTORY ANALYSIS OF A VARIABLE-DRAG PAYLOAD EJECTED FROM A VEHICLEIN A LOW EARTH ORBIT,Richard Reid and David B.

Middleton, July 1963 TND 1939 AN ANALYSIS OF THELUNAR RETURN MISSION,John P. Gapcynski and Robert H. Tolson, August 1963 TN D 1940 AN INVESTIGATION OF THENATURAL FREQUENCIES ANDMODE SHAPES OF DOUBLE CONICAL SANDWICH DISKS, William M. Thompson,Jr., and Robert R. Clary, August 1963 TN D 1942 APPLICATION OF DORODNITSYN'S INTEGRAL METHOD TONONEQUILIBRIUM FLOWS OVER POINTED BODIES,Jerry C. South, Jr., August 1963 THE COUPLED DYNAMIC RESPONSE OF A TANK PARTIALLY FILLED WITH A TND 1945 LIQUID AND UNDER-GOING FREE AND FORCED PLANAR OSCILLATIONS, David G. Stephens and H. Wayne Leonard, August 1963 TN D 1946 FULL-SCALE WIND-TUNNEL INVESTIGATION OF A FLEXIBLE-WING MANNED TEST VEHICLE, Joseph L. Johnson, Jr. and James L. Hassell, Jr., August 1963 TN D 1950 RANDOM DEVIATIONS FROM STABILIZED CRUISE ALTITUDES OF COMMERCIAL TRANSPORTS AT ALTITUDES UP TO 40,000 FEET WITH AUTOPILOT IN ALTITUDE HOLD, Joseph J. Kolnick and Barbara S. Bentley, July EVALUATION OF AN ELECTROMAGNETIC SHOCK TUBE FOR GENERATING TN D 1953 STRONG SHOCKS IN AIR, James F. Roach, October 1963 TN D 1955 EFFECTS OF PEAK DECELERATION ON RANGE SENSITIVITY FOR A MODULATED-LIFT REENTRY AT SUPERCIRCULAR SPEEDS, Charlie M.

Jackson, Jr. and Roy V. Harris, Jr., September 1963 AERODYNAMIC DAMPING OF A O.02-SCALE SATURN SA-I MODEL VIBRATING TN D 1956 IN THE FIRST FREE-FREE BENDING MODE, Perry W. Hanson and Robert V. Doggett, Jr., September 1963 TN D 1957 LOW-SPEED INVESTIGATION OF THE EFFECTS OF WING SWEEP ON THE AERODYNAMIC CHARACTERISTICS OF PARAWINGS HAVING EQUAL-LENGTH LEADING EDGES AND KEEL, Rodger L. Naeseth and Thomas G. Gainer, August 1963 TN D 1958 TRANSONIC WIND-TUNNEL INVESTIGATION OF THE STATIC AERODYNAMIC CHARACTERISTICS OF SEVERAL CONFIGURATIONS OF THE BLUE SCOUT LAUNCH VEHICLE, Thomas C. Kelly and Robert J. Keynton, September 1963 TN D 1959 EFFECTS OF ROUNDING CORNERS AND LEADING EDGES ON THE WINDWARD- SURFACE PRESSURES OF A DELTA WING SWEPT 65 ° AT A MACH NUMBER OF 5.96 AT ANGLES OF ATTACK FROM 65 ° TO 115 ° AND ANGLES OF ROLL FROM 0 ° TO 25 ° AT 90 ° ANGLE OF ATTACK, Theodore J. Goldberg and Doris K. Blanchard, July 1963 TN D 1960 SPECTROMETRIC MEASUREMENTS OF GAS TEMPERATURES IN ARC-HEATED JETS AND TUNNELS, David H. Greenshields, October 1963 TN D 1963 EFFECTS OF CROSS-SECTION SHAPE ON THE LOW-SPEED AERODYNAMIC CHARACTERISTICS OF A LOW-WAVE-DRAG HYPERSONIC BODY, Bernard Spencer, Jr. and W. Pelham Phillips, October 1963 TN D 1964 A SIMULATOR STUDY OF AIRSPACE REQUIREMENTS FOR THE SUPERSONIC TRANSPORT, Richard H. Sawyer, September 1963 TND 1965 FLIGHT-ANDFORCE-TEST INVESTIGATION OFA MODEL OFAN AERIAL VEHICLE SUPPORTED BY TWO UNSHROUDED PROPELLERS, Robert H.

Kirby, September1965 TN D 1966 STEADY-STATE CHARACTERISTICS OFA DIFFERENTIAL-PRESSURE SYSTEM FOREVALUATING ANGLES OF ATTACK ANDSIDESLIPOFTHERANGER IV VEHICLE,E. Carson Yates, Jr. and Annie G. Fox, November1963 TN D 1968 IN-FLIGHT SHOCK-WAVE PRESSURE MEASUREMENTS ABOVE ANDBELOW A BOMBER AIRPLANE AT MACH NUMBERS FROM 1.42 TO 1.69, DomenicJ.

Maglieri, Virgil S. Ritchie, and John F. Bryant, Jr., APPENDIX B: DESIGN ANDAERODYNAMIC CALIBRATION OF PRESSURE PROBE, Virgil S. Ritchie, October 1963 TN D 1970 DESCRIPTION OFAN ANALOG COMPUTER APPROACH TO V/STOLSIMULATION EMPLOYING A VARIABLE-STABILITY HELICOPTER, John F. Garren, Jr.

and JamesR. Kelly, January 1964 TND 1971 WIND-TUNNEL MEASUREMENTS OF PERFORMANCE, BLADE MOTIONS, AND BLADE AIR LOADS FORTANDEM-ROTOR CONFIGURATIONS WITHANDWITHOUT OVERLAP, Robert J. Huston, October i[963 TND 1972 HEATTRANSFER WITHLAMINAR FLOW IN CONCENTRIC ANNULIWITH CONSTANT ANDVARIABLE WALL TEMPERATURE ANDHEATFLUX, R. E.

Lundberg, W. C. Reynolds, and W. M. Kays, August 1963 TND 1973 BEHAVIORAL TESTING DURING A 7-DAYCONFINEMENT: THEINFORMATION PROCESSING TASK, Rollin M. Patton, December1963 TN D 1974 BEHAVIORAL TESTING DURING A 7-DAYCONFINEMENT: THEPATTERN DISCRIMINATION TASK,Rollin M. Patton and Robert J. Randle, Jr., December1963 TN D 1975 HEATTRANSFER TO BLUNT CONICAL BODIES HAVING CAVITIESTO PROMOTE SEPARATION, Frank J. Centolanzi, July 1963 TN D 1976 MOMENTUM ACCOMODATION OF N +, N2 +, ANDA+ INCIDENT ONCOPPER AND ALUMINUM FROM 0.5 TO 4 KEV, Howard F. Savageand Michel Bader, September1963 TN D 1977 A MICROMETEOROID VELOCITY DETECTOR, Frank Neuman,September1963 TND 1978 THERMAL RADIATION FROM ABLATION PRODUCTS INJECTED INTOA HYPER- SONICSHOCK LAYER,Roger A. Craig and William C. Davy, September TND 1979 EXPERIMENTAL ANDTHEORETICAL PRESSURES ONBLUNT CYLINDERS FOR EQUILIBRIUM ANDNONEQUILIBRIUM AIR AT HYPERSONIC SPEEDS, Donald M. Kuehn, November1963 SHOCK ENVELOPES OF BLUNT BODIES AT LARGE ANGLES OF ATTACK, George TN D 1980 E. Kaattari, December 1963 INVESTIGATION OF THE IMPACT OF COPPER FILAMENTS INTO ALUMINUM TN D 1981 TARGETS AT VELOCITIES TO 16,000 FEET PER SECOND, C. Robert Nysmith, James L. Summers, and B. Pat Denardo, February 1964 EXPERIMENTAL AND THEORETICAL STUDIES ON THE FORMATION OF DETONA- TN D 1983 TION WAVES IN VARIABLE GEOMETRY TUBES, Loren E. Bollinger, Michael C. Fong, James A. Laughrey, and Rudolph Edse, June 1963 PHOTOCHEMICAL PROBLEMS OF THE VENUS ATMOSPHERE, Paul Harteck, TN D 1984 Robert R. Reeves, Jr. and Barbara A. Thompson, June 1963 TN D 1985 RECIPROCITY IN QUANTUM MECHANICS, D. E. Bilhorn, L. L. Foldy, V. A. Madsen, R. M. Thaler, and W. Tobocman, August 1963 MICROMETEOROID SATELLITE (EXPLORER XIII) STAINLESS-STEEL PENETRA- TN D 1986 TION RATE EXPERIMENT, Staff of the Lewis Research Center, October ANGULAR DISTRIBUTION OF EMITTED AND REFLECTED RADIANT ENERGY FROM TN D 1987 DIFFUSE GRAY ASYMMETRIC GROOVES, Morris Perlmutter and John R.

Howell, October 1963 THE DESIGN OF MICROMETEOROID PENETRATION EXPERIMENTS AS SINGLE- TN D 1989 SAMPLING LIFE-TEST SAMPLING PLANS, Arthur G. Holms, March 1964 HEAT-TRANSFER AND WEIGHT ANALYSIS OF A MOVING-BELT RADIATOR TN D 199C SYSTEM FOR WASTE HEAT REJECTION IN SPACE, Richard J. Flaherty, August 1964 TN D 1992 SHEATH NEAR A PLANE ELECTRODE BOUNDING A COLLISIONLESS PLASMA IN A MAGNETIC FIELD, Arthur W. Goldstein, October 1963 MAGNETIC FIELD OF A FINITE HELICAL SOLENOID, A. R. Sass and James TN D 1993 C. Stoll, October 1963 TN D 1994 MINIMUM-OIL-FLOW REQUIREMENTS OF HIGH-SPEED BALL BEARINGS AT TEMPERATURES TO 800°F., Dean C. Glenn and William J. Anderson, October 1963 TN D 1995 EARTH ORBITAL SATELLITE LIFETIME, James E. Ladner and George C.

Ragsdale, January 1964 TN D 1996 ESTIMATION OF TOLERANCE LIMITS FOR METEOROID HAZARD TO SPACE VEHICLES 100-500 KILOMETERS ABOVE THE SURFACE OF THE EARTH, Charles C. Dalton, February 1964 TN D 1997 THE NATURE OF LIQUID FILM EVAPORATION DURING NUCLEATE BOILING, Robert R. Sharp, October 1964 TND 1998 EFFECTS OF COMPRESSIBILITY ANDHEATTRANSFER ONTHELAMINAR SUB- LAYER OF THETURBULENT BOUNDARY LAYER,K. R. Czarnecki and William J. Monta, October 1964 TND 2000 HEAT-TRANSFER ANDPRESSURE MEASUREMENTS ONA PRELIMINARY PROJECT FIRE MODEL AT MACH 3.51, Robert L. Stallings, Jr. and Kenneth V.

Haggard, November1964 TND 2003 DIGITAL OHMMETER, John Semyan,October 1964 TND 2004 THREE-BODY COLLISIONAL RECOMBINATION OF CESIUM SEED IONSAND ELECTRONS IN HIGH-DENSITY PLASMAS WITHARGON CARRIER GAS, John V. Dugan, Jr., APPENDIX D: COMPUTER PROGRAM FORSTUDYING RE- COMBINATION OF AN ATOMIC ION, Lynn U. Albers, October 1964 TN D 2006 AN ANALYSIS OF A VORTEX TYPEMAGNETO-HYDRODYNAMIC INDUCTION GENERATOR, L. L. Lengyel and SimonOstrach, September 1963 TN D 2008 SELECTION OF SPACE CABINATMOSPHERES: PARTI. OXYGEN TOXICITY, Emmanuel M. Roth, M. D., August ]963 TN D 2009 DEVELOPMENT OFA SMOKE-TRAIL VEHICLE FORAPPLICATION TO WIND- SHEAR MEASUREMENTS UP TO 80,000 FEET,WadeE. Lanford, TomW.

Perry, Jr., Hal T. Baber, Jr., and Franklin W. Booth, November TND 2010 CALCULATION OF ELECTRON ENERGY DEPOSITION IN THIN-FILMPOLYMERIC MATERIALS, Louis A. Teichman and Ernest S. Armstrong, October 1963 TN D 2011 THERELATIVE SUSCEPTIBILITY OF FOUR COMMERCIAL TITANIUM ALLOYS TO SALTSTRESS CORROSION AT 550°F., David N. Braski and George J.

Heimerl, December1963 TN D 2012 CALIBRATIONS OFAIRCRAFT STATIC-PRESSURE SYSTEMS BY GROUND-CAMERA ANDGROUND-RADAR METHODS, William Gracey and Joseph W. Stickle, August 1963 TND 2013 FULL-SCALE WIND-TUNNEL TESTOF THEVZ-2 VTOLAIRPLANE WITH PARTICULAR REFERENCE TO THEWING STALLPHENOMENA, Robert G.

Mitchell, December1963 TND 2014 WING PRESSURE MEASUREMENTS WITHINTHEPROPELLER SLIPSTREAM FORA LARGE-SCALE V/STOLWIND-TUNNEL MODEL SIMULATING TRANSITION, Matthew M. Winston and Robert J. Huston, October 1963 TND 2015 INVESTIGATION OF THECALORIMETRIC EFFICIENCY OFA SPLIT-RIB UMBRELLA-TYPE PARABOLOIDAL SOLAR ENERGY CONCENTRATOR, John D.

Camp and William D. Nowlin, March 1964 ANALYTICAL STUDY OF LUNAR LANDING TRAJECTORIES WITHREFERENCE TO TND 2016 THELUNAR-ORBIT-RENDEZVOUS MODE ANDPOSSIBLE ABORT SITUATIONS, JamesL. Williams and L. Keith Barker, December1963 ANALYSIS OF JET-PLUMING INTERFERENCE BY COMPUTER SIMULATION OF TN D 2018 MEASURED FLIGHTMOTIONS OF TWO RAM A FOURTH STAGES, William F.

Hinson and SherwoodHoffman, December1963 REAL-GAS HYPERSONIC-NOZZLE FLOW PARAMETERS FORNITROGEN IN TN D 2019 THERMODYNAMIC EQUILIBRIUM, Frank L. Clark and Charles B. Johnson, November1963 EXPERIMENTAL INVESTIGATION OF HEATTRANSFER ANDPRESSURES ONA TND 2020 SWEPT CYLINDER IN THEVICINITY OF ITS INTERSECTION WITHA WEDGE ANDFLATPLATEAT MACH NUMBER 4.15 ANDHIGHREYNOLDS NUMBERS, Ivan E. Beckwlth, July 1964 LATERAL-SPREAD SONIC-BOOM GROUND-PRESSURE MEASUREMENTS FROM AIR- TN D 2021 PLANES AT ALTITUDES TO 75,000 FEETANDAT MACH NUMBERS TO 2.0, DomenicJ. Maglieri, Tony L. Parrott, David A. Hilton, and William L. Copeland, November1963 AN AEROELASTIC MODEL APPROACH FORTHEPREDICTION OF BUFFET BENDING TN D 2022 LOADS ONLAUNCH VEHICLES, Robert V. Doggett, Jr. and Perry W.

Hanson, October 1963 TND 2023 DESCRIPTION ANDINITIAL CALIBRATION OFTHELANGLEY HOTSHOT TUNNEL WITHSOME REAL-GAS CHARTS FORNITROGEN, Fred M. Smith, Edwin F.

Harrison, and Pierce L. Lawing, December1963 TN D 2026 STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS ANDSURFACE PRES- SURE DISTRIBUTIONS FORA 1/15-SCALE MODEL OFA MODIFIED FOUR- STAGE SCOUT VEHICLE,ThomasC. Kelly, October 1963 CHARACTERISTICS OF A LUNAR LANDING CONFIGURATION HAVING VARIOUS TN D 2027 MULTIPLE-LEG LANDING-GEAR ARRANGEMENTS, Ulysse J. Blanchard, January 1964 HEAT-TRANSFER ANDPRESSURE INVESTIGATION OF A FIN-PLATEINTER- TND 2028 FERENCE MODEL AT A MACH NUMBER OF 6, Robert A. Jones, July 1964 WATER-FILM COOLING OFAN 80 ° TOTAL-ANGLE CONE AT A MACH NIfMBER TN D 2029 OF 2 FOR AIRSTREAM TOTAL TEMPERATURES UP TO 3,000°R., Howard S. Carter, October 1963 WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEED OF THE STATIC TN D 2030 LONGITUDINAL STABILITY CHARACTERISTICS OF A WINGED REENTRY VEHICLE HAVING A LARGE NEGATIVELY DEFLECTED FLAP-TYPE CONTROL SURFACE, Paul G. Fournier, October 1963 TN D 2031 LOW-SUBSONIC FLIGHTCHARACTERISTICS OF A MODEL OF SUPERSONIC- AIRPLANE CONFIGURATION WITHA PARAWING AS A LANDING AID, Joseph L. Johnson, Jr., November1963 TN D 2032 A MAGNETICALLY ROTATED ELECTRIC ARCAIR HEATER EMPLOYING A STRONG MAGNETIC FIELDANDCOPPER ELECTRODES, Robert F. Mayo, William L. Wells, and Milton A. Wal]io, November1963 TN D 2033 TRANSONIC INVESTIGATION OF A PYRAMIDAL REENTRY CONFIGURATION WITHCAMBERED VARIABLE-SWEEP WINGS ANDVARIOUS LONGITUDINAL CONTROLS, Bernard Spencer, Jr., December1963 TND 2034 SUBSONIC AERODYNAMIC HEATTRANSFER TOA SURFACE RECESSED WITHIN A FORWARD STAGNATION REGION SLIT, SamuelJ. Scott, December1963 TN D 2035 LANDING CHARACTERISTICS OFA REENTRY VEHICLE WITHA PASSIVE LANDING SYSTEM FORIMPACT ALLEVIATION, SandyM. Stubbs, January TN D 2037 AERODYNAMIC CHARACTERISTICS OF A SPOILER-SLOT-DEFLECTOR CONTROL ONA 45 ° SWEPTBACK-WING - FUSELAGE MODEL AT HIGH SUBSONIC SPEEDS, Alexander D. Hammond, November 1963 TN D 2041 AN ANALYTICAL STUDY OF THE MAGNETIC FIELD ENCOUNTERED BY ARTIFICIAL EARTH SATELLITES IN CIRCUTAR ORBITS, Ward F. Hodge and W. Thomas Blackshear, February 1964 TN D 2042 EFFECT OF AFTERBODY GEOMETRY AND STING DIAMETER ON THE AERODYNAMIC CHARACTERISTICS OF SLENDER BODIES AT MACH NUMBERS FROM 1.57 TO 2.86, Dennis E. Fuller and Victor E. Langhans, November 1963 TN D 2043 CALCULATED RADIO ATTENUATION DUE TO PLASMA SHEATH ON HYPERSONIC BLUNT-NOSED CONE, John S. Evans and Paul W. Huber, December 1963 TN D 2044 FREE-FLIGHT INVESTIGATION OF THE DEPLOYMENT OF A PARAWING RECOVERY DEVICE FOR A RADIO-CONTROLLED 1/5-SCALE DYNAMIC MODEL SPACECRAFT, Charles E. Libbey, December 1963 TND 2046 JET EFFECTS AT SUPERSONIC SPEEDS ON BASE AND AFTERBODY PRESSURES OFA MISSILE MODEL HAVING SINGLE AND MULTIPLE JETS, Nickolai Charczenko and Clyde Hayes, November 1963 TN D 2048 BOUNDARY-LAYER VELOCITY PROFILES AND SKIN FRICTION DUE TO SURFACE ROUGHNESS ON AN OGIVE CYLINDER AT MACH NUMBERS OF 1.61 AND 2.01, K. Ro Czarnecki and William J. Monta. December 1963 TND 2050 EFFECTS OF FLANK LOSSES IN THE THEORY OF SPACE-PROBE ENTRY UNDER CONDITIONS OF HIGH MASS LOSS, Frederick C. Grant, December 1963 THEDESIGN OF SAILPLANES FOROPTIMUM THERMAL SOARING PERFORMANCE, TN D 2052 Clarence D. Cone, Jr., January 1964 A WIND-COMPENSATION METHOD ANDRESULTS OF ITS APPLICATION TO TN D 2053 FLIGHTTESTS OF TWELVE TRAILBLAZER ROCKET VEHICLES, Allen B.

Henning, Reginald R. Lundstrom, and Jean C. Keating, April TN D 2054 EFFECT OF CONTROLLED SURFACE ROUGHNESS ONBOUNDARY-LAYER TRANSI- TIONANDHEAT TRANSFER AT MACH NUMBERS OF 4.8 AND6.0, Paul F.

Holloway and JamesR. Sterrett, April 1964 TN D 2056 PHENOMENA OFPNEUMATIC TIRE HYDROPLANE, Walter B. Horne and Robert C. Dreher, November1963 APPROXIMATE CALCULATION OF HYPERSONIC CONICAL FLOW PARAMETERS TN D 2058 FORAIR IN THERMODYNAMIC EQUILIBRIUM, Perry A. Newman, January A WIND-TUNNEL INVESTIGATION OF THEEFFECT OF CHANGES IN BASE TN D 2062 CONTOUR ONTHEDAMPING IN PITCHOF A BLUNTED CONE, William R.

Wehrend, Jr., November1963 TND 2063 THETRANSPORT OF CHEMICALLY REACTING SPECIES IN THECLASSICAL CAPILLARY, John T. Howe, December1963 A STUDY OF THECONVECTIVE ANDRADIATIVE HEATING OF SHAPES TN D 2064 ENTERING THEATMOSPHERES OF VENUS ANDMARS AT SUPERORBITAL SPEEDS, Fred A. Demele, December1963 TN D 2065 MINIMUM CREW SPACE HABITABILITYFORTHELUNAR MISSION,George A. Rathert, Jr., NormanM. McFadden,Richard F. Weick, R.

Mark Patton, Glen W. Stinnett, and Terence A. Rogers, February TN D 2066 EVALUATION OFA CONSTRICTED-ARC SUPERSONIC JET, Charles E.

Shepard, Velvin R. Watson, and HowardA. Stine, January 1964 TN D 2069 PROSPECTS FOROBTAINING AERODYNAMIC HEATING RESULTS FROM ANALYSIS OFMETEOR FLIGHTDATA,H. Julian Allen and Nataline A.

James, July 1964 A NUMERICAL ANALYSIS OFDIRECT NUCLEAR ELECTROGENERATOR CELLS TND 2070 THATUSECERIUM 144 BETA-EMITTING RADIOISOTOPE SOURCES, Allan J. Cohen, November1963 TN D 2071 ELECTROMAGNETIC WAVE PROPAGATION IN A COLD,COLLISIONLESS ATOMIC HYDROGEN PLASMA, Richard R. Woollett, April 1964 TN D 2072 LOW-THRUST ORBITRAISINGIN CONTINUOUS SUNLIGHT, Dennis W. Brown, April 1964 TN D 2073 FRICTION,WEAR, ANDDECOMPOSITION MECHANISMS FORVARIOUS POLYMER COMPOSITIONS IN VACUUM TO 10-9 MILLIMETER OFMERCURY, Donald H.

Buckley and Robert L. Johnson, Decen_er 1963 TN D 2074 AN INTEGRATED HOTWIRE-STILLWELL LIQUIDHYDROGEN ANDOTHER CRYOGENIC FLUIDS,William A. Olsen, Jr., November1963 TN D 2075 EFFECT OF CONTACT ANGLE ANDTANKGEOMETRY ONTHECONFIGURATION OF THELIQUID-VAPOR INTERFACE DURING WEIGHTLESSNESS, Donald A.

Petrash, Ralph C. Nussle, and EdwardW. Otto, October 1963 TN D 2077 HEATTRANSFER FROM FIN-TUBE RADIATORS INCLUDING LONGITUDINAL HEATCONDUCTION ANDRADIANT INTERCHANGE BETWEEN LONGITUDINALLY NONISOTHE_MAL FINITE SURFACE, E. M. Sparrow, V. K. Jonsson, and W. J. Minkowycz, December1963 TN D 2078 FIELDEMISSION CHARGING OF METALLIC COLLOIDS, N. Stankiewicz, December1963 TN D 2079 EXPERIMENTAL INVESTIGATION OF THEBEHAVIOR OF A CONFINED FLUID SUBJECTED TONONUNIFORM SOURCE ANDWALL HEATING, Bernhard H.

Anderson and Michael J. Kolar, November1963 TN D 2080 COMPILATION OFTHEORETICAL ROCKET PERFORMANCE FORTHECHEMICALLY FROZEN EXPANSION OF HYDROGEN, Ernie W. Spisz, December1963 TN D 2081 EVAPORATION RATES FORVARIOUS ORGANIC LIQUID ANDSOLIDLUBRI- CANTS IN VACUUM TO 10-8 MILLIMETER OFMERCURY AT 55° TO IIO0°F., Donald H. Buckley and Robert L. Johnson, December1963 TN D 2083 ANISOTROPIC EFFECTS IN HELICALLY WOUND SUPERCONDUCTING SOLENOIDS, Edmund E. Callaghan, December1963 TN D 2084 A STEADY-STATE ANALYSIS OFTHE"LAMINAR-INSTABILITY" PROBLEM DUETO HEATING PARAHYDROGEN IN LONG,SLENDER TUBES,David P.

Harry, III, February 1964 TN D 2085 FORTRAN PROGRAM FORCOMPUTING THEPRINCIPAL MOMENTS OF INERTIA OF A RIGID MOLECULE, Janet G. Ehlers and Glenn R. Cowgill, February 1964 TN D 2086 NONEQUILIBRIUM EXPANSION OFA PLASMA FROM A THERMONIC SOURCE, Peter M. Sockol, December1963 TND 2087 EFFECT OF _MBIENT AIR VELOCITY ONATOMIZATION OF TWO IMPINGING WATER JETS, David A. Bittker, February 1964 CAVITATION ANDEFFECTIVE LIQUIDTENSION OF NITROGEN IN A TUNNEL TN D 2088 VENTURI,Robert S. Ruggeri and ThomasF. Geld_r, February 1964 STABILITYOF FREE-CONVECTION BOUNDARY-LAYER FLOWS, Philip R.

TN D 2089 Nachtsheim, December1963 AERODYNAMIC ANDCONTROL-SYSTEM CONTRIBUTIONS TO THEX-15 TN D 2090 AIRPLANE LANDINGZGEAR LOADS,Richard B. Noll, Calvin R. Jarvis, Chris Pembo,Wilton P. Lock, and Betty J. Scott, October 1963 IONIZATION ASSOCIATED WITHHYPERVELOCITY IMPACT,J. F.

TN D 2091 Friichtenicht and J. C. Slattery, August 1963 ELECTRICITY IN THETERRESTRIAL ATMOSPHERE ABOVE THEEXCHANGE TN D 2092 LAYER,Elden C. Whipple, Jr., January 1964 DEVELOPMENT OF A RANGE ANDRANGE RATESPACECRAFT TRACKING SYSTEM, TN D 2093 E. J. Habib, G. C. Kronmiller, Jr., P. D. Engels, and H. J.

Franks, Jr., June 1964 COMPARISON OFTHEVONZEIPELANDMODIFIED HANSEN METHODS AS TN D 2094 APPLIED TOARTIFICIAL SATELLITES, David Fisher, November1963 THREE ANDFOUR COIL SYSTEMS FORHOMOGENEOUS MAGNETIC FIELDS, TN D 2095 M. E. Pittman and D. L. Waidelich, January 1964 THEEFFECT OF AURORAL BREMSSTRAHLUNG ONTHELOWER IONOSPHERE, TND 2096 A. C. Aikin and E. J. Maier, November1963 SYNCHROTRON RADIATION CALCULATIONS FORTHEARTIFICIALRADIATION TN D 2097 BELT,M. P. Nakada, January 1964 SOLAR CELLRADIATION DAMAGE STUDIES WITHi MEVELECTRONS AND TN D 2098 4.6 MEVPROTONS, William R. Cherry and Luther W. Slifer, February ENVIRONMENTAL TESTPROGRAM FORARIEL I, Warner H. Hord, Jr., TN D 2099 February 1964 DUST BOMBARDMENT ONTHELUNAR SURFACE, Curtis W. McCracken TND 2100 and Maurice Dubin, December1963 HIGHSPEED VACUUM PERFORMANCE OF GOLD PLATED MINIATURE BALL TN D 2101 BEARINGS WITHVARIOUS RETAINER MATERIALS ANDCONFIGURATIONS, Harold E. Evans and ThomasW. Flatley, December1963 ANALYTICAL INVESTIGATION OF REDUCTION IN TURBULENT SKIN FRICTION TN D 2102 ONA FLATPLATEBYMEANS OFAIR INJECTION THROUGH DISCRETE SLOTS, K. R. Czarnecki, November1964 TN D 2103 THEDRIFTOFA 24-HOUR EQUATORIAL SATELLITE DUETO AN EARTH GRAVITY FIELD THROUGH 4th ORDER, C. A. Wagner, February 1964 TND 2104 TRANSISTORIZED VHFTRANSMITTER DESIGN FORSPACECRAFT APPLICATIONS, Charles R. Somerlock, May 1964 TND 2105 COMPUTATIONS FORLARGE,UNIFORM CIRCULAR ARRAYS WITHTYPICAL ELEMENT PATTERNS, Capers R. Cockrell, October 1964 TN D 2106 EFFECTS OF NON-PHOTOCHEMICAL PROCESSES ONTHEMERIDIONAL DISTRIBUTION ANDTOTAL AMOUNT OFOZONE IN THEATMOSPHERE, CuddapahPrabhakara, June 1964 TN D 2107 THEROCKET-GRENADE EXPERIMENT, W. Nordberg and W. Smith, March TN D 2108 DEVELOPMENT OF A BRUSHLESS DCMOTOR FORSATELLITE APPLICATION, Philip A. Studer, February 1964 TN D 2109 THEWORLD MAGNETIC SURVEY, JamesP. Heppner, January 1964 TND 2110 DEPARTURES FROM LOCAL THERMODYNAMIC EQUILIBRIUM IN ANAO STARATMOSPHERE, Myron Lecar, March 1964 TND 2111 A DETECTOR-ANALYZER FORSTUDYING THEINTERPLANETARY PLASMA, K. W. Ogilvie, N. Mcllwraith, H. J. Zwally, and T. D. Wilkerson, February 1964 TND 2112 SUPERNOVAE, NEUTRINOS, ANDNEUTRON STARS,Hong-YeeChiu, June TND 2114 IONOSPHERIC WINDS: MOTIONS INTONIGHTANDSPORADIC E CORRELA- TIONS,N. W. Rosenberg, H. D. Edwards, and J. W. Wright, September1963 TN D 2115 NUMERICAL SOLUTIONS OF KNUDSEN FLOW ENTERING A CIRCULAR TUBE THROUGH A SMALL AXIAL ORIFICE, EdwardA. Richley and Carl D.

Bogart, February 1964 TN D 2116 WALL TEMPERATURES IN A TUBEWITHFORCED CONVECTION, INTERNAL RADIATION EXCHANGE, ANDAXIAL WALL HEATCONDUCTION. Robert Siegel and Edward G. Keshock, APPENDIX B: SOLUTION OF NON- LINEARINTEGRODIFFERENTIAL EQUATION, Carroll A. Todd, March TN D 2117 EVALUATION OF SHOCK-TUBE HEAT-TRANSFER EXPERIMENTS TOMEASURE THERMAL CONDUCTIVITY OFARGON FROM 700° TO 8600°K,, Milton R. Lauver, February 1964 TN D 2118 EFFECT OF SEEDING AND ION SLIP ON ELECTRON HEATING IN A MAGNETOHYDRODYNAMIC GENERATOR, Frederic A. Lyman, Arthur W.

Goldstein, and John E. Heighway, February 1964 TN D 2119 ONE-DIMENSIONAL HEAT-TRANSFER ANALYSIS OF THERMAL-ENERGY STORAGE FOR SOLAR DIRECT-ENERGY-CONVERSION SYSTEMS, Richard R. Cullom, William H. Robbins, and Carroll A. Todd, March A FORTRAN PROGRAM FOR ANALYSIS OF SPIN ZERO ELASTIC SCATTERING TN D 2120 WITH THE NUCLEAR OPTICAL MODEL, C. C. Giamati, W. Tobocman, and D. V. Renkel, April 1964 TN D 2121 CORRELATION OF A TURBULENT AIR-BROMINE COAXIAL-FLOW EXPERIMENT, Robert G. Ragsdale, Herbert Welnstein, and Chester D. Lanzo, February 1964 TN D 2122 A MONTE CARLO CALCULATION OF THE NUCLEAR COLLISION DENSITY OF PRIMARY GALACTIC PROTONS IN A SLAB OF ALUMINUM, Millard L.

Wohl, March 1964 TN D 2123 ANALYSIS OF MIXING OF COAXIAL STREAMS OF DISSIMILAR FLUIDS INCLUDING ENERGY-GENERATION TERMS, Herbert Weinstein and Carroll A. Todd, March 1964 TN D 2124 TWO-DIMENSIONAL GRAY-GAS RADIANT HEAT TRANSFER IN A COAXIAL- FLOW GASEOUS REACTOR, Robert G. Ragsdale and Thomas H. Einstein, February 1964 TN D 2126 NUMERICAL PREDICTIONS OF NONLINEAR DIFFUSSION WITH HOMOGENEOUS RECOMBINATION AND TIME-VARYING BOUNDARY CONDITIONS, Walter A.

Reinhardt, January 1964 TN D 2127 RETURN TRAJECTORIES FROM THE MOON: SOME LIMITS DUE TO RESTRIC- TIONS ON ENTRY RANGE AND LANDING LIGHTING CONDITIONS, Luigi S.

Cicolani, January 1964 TN D 2128 ON THE DIRECT SOLUTION OF THE GOVERNING EQUATION FOR RADIATION- RESISTED SHOCK WAVES, Walter E. Pearson, January 1964 TN D 2129 SECONDARY ERRORS AND OFF-DESIGN CONDITIONS IN OPTIMAL ESTIMATION OF SPACE VEHICLE TRAJECTORIES, Gerald L. Smith, January 1964 TN D 2130 EFFECTIVENESS OF RADIATION SHIELDS FOR THERMAL CONTROL OF VEHICLES ON THE SUNLIT SIDE OF THE MOON, John C° Arvesen and Frank M.

Hamaker, April 1964 TN D 2131 CHEMICAL RELAXATION BEHIND STRONG NORMAL SHOCK WAVES IN CARBON DIOXIDE INCLUDING INTERDEPENDENT DISSOCIATION AND IONIZATION PROCESSES, John T. Howe and Yvonne S. Sheaffer, February 1964 TND 2132 ONTHEEQUILIBRIUM SONIC-FLOW METHOD FOREVALUATING ELECTRIC-ARC AIR-HEATER PERFORMANCE, Warren Winovich, March 1964 TN D 2133 LARGE-SCALE WIND-TUNNEL TESTS OF AN AIRPLANE MODEL WITHAN UNSWEPT TILT WING OFASPECT RATIO5.5,AND WITHVARIOUS STALL CONTROL DEVICES, JamesA. Weiberg and Demo J. Giulianetti, February 1964 TND 2136 A GEOGRAPHICAL GRIDFORNIMBUS CLOUD PICTURES, EugeneM.

Darling, Jr., February 1964 TN D 2137 AN ANALYSIS OF ERRORS IN THEGEOGRAPHIC REFERENCING OF NIMBUS CLOUD PICTURES, EugeneM. Darling, Jr., January 1964 TN D 2138 INFRASONIC WAVES FROM THEAURORAL ZONE,Kaichi Maedaand Tomiya Watanabe, June 1964 TN D 2139 THERANGE ANDRANGE RATESYSTEM ANDDATAANALYSIS FORSYNCOM I (1963 4A), H. W. Shaffer, W. D. Kahn, W. J. Bodin, Jr., G. C.

Kronmiller, P. D. Engels, and E. J. Habib, June 1964 TND 2140 INTERPOLATION ANDCOORDINATE TRANSFORMATION PROGRAM PROVIDING ACCURATE LOCAL ANTENNA POINTING FROM PREDICTED SATELLITE POSITIONS, A. K. Berndt and J. H. Berbert, June 1964 TN D 2141 THEBACKWARD RECURRENCE METHOD FORCOMPUTING THEREGULAR BESSEL FUNCTION, ThomasE. Michels, March 1964 TN D 2142 FIELDWINDWEIGHTING ANDIMPACT PREDICTION FORUNGUIDED ROCKETS, Keith E. Hennigh, March 1964 TND 2143 ATTITUDE DETERMINATION FORTIROSSATELLITES, Joseph W. Siry and Joseph V. Natrella, June 1964 TN D 2144 TRIAXIALBALANCING TECHNIQUES (A STUDY OF SPACECRAFT BALANCE WITHRESPECT TOMULTIPLE AXES), William E. Lang, March 1964 TN D 2145 THEORY OF THE2s AND2p EXCITATION OF THEHYDROGEN ATOM INDUCTED BYELECTRON IMPACT,KazemOmidvar, June 1964 TND 2146 RESPONSE OFMODIFIED REDHEAD MAGNETRON ANDBAYARD-ALPERT VACUUM GAUGES ABOARD EXPLORER XVII, G. P. Newton, D. T. Pelz, G. E.

Miller, LTJG, USN, and R. Horowitz, February 1964 TND 2147 THERMAL RADIATION TOA FLATSURFACE ROTATING ABOUT ANARBITRARY AXIS IN AN ELLIPTICALEARTH ORBIT: APPLICATION TO SPIN-STABILIZED SATELLITES, Edward I. Powers, April 1964 TN D 2148 RESONANCE SCATTERING AT LYMAN-ALPHA BYAN ATOMIC HYDROGEN CELL, J. E. Blamont, P.Delache, and A. K. Stober, June 1964 TRAVELING WAVE TUBERE-ENTRANT AMPLIFIER SERRODYNE SYSTEM, W. K.

TND 2149 Allen, L. J. Ippolito, and D. A. Nace, June 1964 TN D 2150 EXPLORER VIII SATELLITE MEASUREMENTS IN THEUPPER IONOSPHERE, R. E. Bourdeauand J. L. Donley, June 1964 TN D 2151 AIRBORNE TRANSISTORIZED TELEMETER SYSTEM MODEL SST-I, R. J.

Stattel and J. E. Pownell, April 1965 ONTHESIMULTANEOUS COMPUTATION OF THESECULAR ANDRESONANCE TN D 2152 EFFECTS IN THEMOTION OF CELESTIAL BODIES,Peter Musen, June TN D 2154 A PARAMETRIC STUDY OF CONSTANT THRUST, ELECTRICALLY PROPELLED MARS ANDVENUS ORBITING PROBES, Leonard G. Rossa, October THESHAPE OFA MAGNETICALLY ROTATED ELECTRIC ARCCOLUMN IN AN TN D 2155 ANNULAR GAP,JamesR. Jedlicka, October 1964 POTENTIAL ADVANTAGES OF ANISOTROPIC SUPERCONDUCTORS IN "FORCE- TN D 2156 FREE"SOLENOIDS, Edmund E. Callaghan, October 1964 TN D 2157 LUNAR MISSION PERFORMANCE EVALUATION PROCEDURE FORORBIT-LAUNCHED NUCLEAR VEHICLES, Robert E. Austin and George B. Kearns, April TND 2159 REDUCTION OF FOLD-OVER ERRORS IN FLUX-GATE MAGNETOMETERS, John Dimeff, Murray S. Gardner, and Richard S. Murphy, October 1964 TN D 2160 PARAMETRIC PERFORMANCE ANALYSIS FORINTERPLANETARY MISSIONS UTILIZING FIRST-GENERATION NUCLEAR STAGES, Walter H. Stafford, SamH. Harlin, and CarmenR. Catalfamo, October 1964 TN D 2161 AN INSTRUMENT FORELECTRONIC DIFFERENTIATION OF CURRENT-VOLTAGE CHARACTERISTICS, Roman Krawec, October 1964 TN D 2162 EXAMINATION OFONBOARD TRAINING FOREXTENDED SPACE FLIGHTS,Richard Reid and R. T. Saucer, November1964 TN D 2163 AERODYNAMIC CHARACTERISTICS FROM MACH 0.22 TO 4.65 OFA TWO-STAGE ROCKET VEHICLE HAVING AN UNUSUAL NOSE SHAPE, John T. Suttles, November1964 TN D 2165 COMPARISON OF MEASUREMENTS OF INTERNAL TEMPERATURES IN ABLATION MATERIAL BY VARIOUS THERMOCOUPLE CONFIGURATIONS, Marvin B. Dow, November1964 TN D 2166 PREDICTION OF AERODYNAMIC PENALTIES CAUSED BY ICE FORMATIONS ON VARIOUS AIRFOILS, Vernon H. Gray, February 1964 TN D 2168 HEAT-REJECTION ANDWEIGHT CHARACTERISTICS OF FIN-TUBESPACE RADIATORS WITHTAPERED FINS, Henry C. Haller, Gordon C. Wesling, and SeymourLieblein, February 1964 TN D 2174 AN OPTIMIZED PRINTER PLOTTING SYSTEM CONSISTING OF COMPLEMENTARY 7090 (FORTRAN) AND1401 (SPS) SUBROUTINES. PARTI - INSTRUCTIONS FORUSERS, Lois T. Dellner and Betty Jo Moore, April 1964 TN D 2175 AN OPTIMIZED PRINTER PLOTTING SYSTEM CONSISTING OF COMPLEMENTARY 7090 (FORTRAN) AND1401 (SPS) SUBROUTINES. PARTII - SYSTEMS PROGRAMMERS MANUAL, Lois T. Dellner and Betty Jo Moore, April TN D 2180 AERODYNAMIC DATAONA LARGE SEMISPAN TILTINGWING WITH0.6- DIAMETER CHORD, FOWLER FLAP, ANDSINGLE PROPELLER ROTATING UP AT TIP, Marvin P. Fink, Robert G. Mitchell, and Lucy C.

White, February 1964 TN D 2182 INDUCED PRESSURES ANDSHOCK SHAPES ONBLUNT CONES IN HYPERSONIC FLOW, Richard D. Wagner, Jr. and Ralph Watson, March 1964 TN D 2183 PERFORMANCE CHARACTERISTICS OFA PREFORMED ELLIPTICALPARACHUTE AT ALTITUDES BETWEEN 200,000 ANDi00,000 FEETOBTAINED BY IN- FLIGHTPHOTOGRAPHY, Charles H. Whitlock and Harold N. Murrow, February 1964 TN D 2184 FORCE-COEFFICIENT ANDMOMENT-COEFFICIENT CORRELATIONS ANDAIR- HELIUM SIMULATION FORSPHERICALLY BLUNTED CONES, Julius E.

Harris, November1964 TN D 2189 DESCRIPTION OF VEHICLE SYSTEM ANDFLIGHTTESTS OFNINE TRAIL- BLAZER I REENTRY PHYSICS RESEARCH VEHICLES, William N. Gardner, Clarence A. Brown, Jr., Allen B. Henning, W. Ray Hook, Reginald R. Lundstrom, and Ira W. Ramsey,Jr., April 1964 TND 2193 EFFECTS OFLAMINAR-BOUNDARY-LAYER DISPLACEMENT ONA HEMISPHERE IN HELIUM FLOW, Davis H. Crawford, April 1964 TN D 2194 THEECHO I INFLATION SYSTEM, DeweyL. Clemmons,Jr., June 1964 TND 2195 SOME OBSERVATIONS DURING WEIGHTLESSNESS SIMULATION WITHSUBJECT IMMERSED IN A ROTATING WATER TANK,Ralph W. Stone, Jr. and William Letko, September1964 TND 2197 FREE-FLIGHT INVESTIGATION OFMASS-TRANSFER COOLING ONA BLUNT CONE TO A MACH NUMBER OF 10.6, ThomasE. Walton, Jr., April TN D 2199 HEATTRANSFER TOA DELTA-WING - HALF-CONE COMBINATION AT MACH NUMBERS OF 7 ANDi0, JamesC. Dunavant, March 1964 TN D 2201 LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF BLUNTED CONES AT MACH NUMBERS OF 3.5, 4.2, AND6.0, J. WayneKeyes, February TND 2204 LONGITUDINAL AERODYNAMIC CHARACTERISTICS ANDSURFACE PRESSURE MEASUREMENTS FORA 1/10-SCALEMODEL OF THERAM B LAUNCH VEHICLE, ThomasC. Kelly and Robert J. Keynton, April 1964 TND 2205 LOW-SPEED CHARACTERISTICS OF A 1/20-SCALEFOUR-ENGINE TRANSPORT MODEL WITHLARGE BODIES MOUNTED ABOVE THEFUSELAGE, Vernard E.

Lockwood,March 1964 TN D 2207 EFFECT OF ELECTRON IRRADIATION ONSOME PROPERTIES OF THEECHO II LAMINATE, ThomasG. James, October 1964 TN D 2208 UNIFIEDS-BAND TELECOMMUNICATIONS TECHNIQUES FORAPOLLO. VOLUME I - FUNCTIONAL DECRIPTION, John H. Painter and GeorgeHondros, March FLOW ANDHEATTRANSFER BETWEEN HEATED PLATES OF FINITE LENGTH IN TN D 2209 A FREE-MOLECULE FLOW ENVIRNMENT, Morris Perlmutter, October 1964 TN D 2210 TWO-DIMENSIONAL FLUXANDCRITICALITYCALCULATIONS FORTHEPLUM BROOK REACTOR, John H. Lynch, October 1964 TN D 2211 MONTE CARLO SOLUTION FORTHECHARACTERISTICS OFA HIGHLY RAREFIED IONIZEDGASFLOWING THROUGH A CHANNEL WITHA TRANSVERSE MAGNETIC FIELD, Morris Perlmutter, October 1964 TN D 2212 ONTHEUSEOF SINGLE TOTAL-ANDSTATIC-PRESSURE PROBES TO MEASURE THEAVERAGE MASS VELOCITY IN THIN RECTANGULAR CHANNELS, Joseph M.

Savino and Andrew J. Hilovsky, October 1964 TN D 2213 HEAT TRANSFER FORLAMINAR SLIP FLOW OFA RAREFIED GASIN A PARALLEL-PLATE CHANNEL ORA CIRCULAR TUBE WITHUNIFORM WALL TEMPERATURE, Robert M. Inman, November1964 TND 2221 IDEAL-GAS TABLES FOROBLIQUE-SHOCK FLOW PARAMETERS IN AIR AT MACH NUMBERS FROM 1.05 TO 12.0, John S. Dennardand Patricia B. Spencer, March 1964 TN D 2222 SOUNDING ROCKET RELIABILITYREASSESSMENT, AbromHisler, November TND 2223 EVALUATION OF JOURNAL BEARINGS OFVARIOUS MATERIALS IN LOW- VISCOSITY FLUIDS,LIQUID NITROGEN, ANDLIQUID OXYGEN, Robert E.

Cunninghamand William J. Anderson, November1964 TN D 2224 A STUDY OF OXIDATION KINETICSOFNICKELMETAL IN FLOWING AIR AND OXYGEN-NITROGEN MIXTURES, D. J. Progar and B. W. Lewis, December TN D 2225 PARAMETRIC STUDY OF MASS-RATIO ANDTRAJECTORY FACTORS IN FAST MANNED MARS MISSIONS,DuaneW. Dugan, February 1965 TN D 2226 INVESTIGATION OFPLASMA AFTERGLOWS WITHAPPLICATION IN NITROGEN, K. C. Stoz, November1963 TN D 2228 ADHESION BETWEEN ATOMICALLY CLEAN SURFACES, Douglas V. Keller, Jr., February 1964 TN D 2230 MEASUREMENT OFHEATTRANSFER ANDRECOVERY FACTOR OF A COMPRES- SIBLETURBULENT BOUNDARY LAYER ONA SHARP CONE WITHFOREIGN GASINJECTION,C. C. Pappas and Arthur F. Okuno, April 1964 TN D 2232 IMPACT FLASH AT LOW AMBIENT PRESSURES, Robert W. MacCormack, March 1964 TN D 2233 THETOTAL ENTHALPY OFA ONE-DIMENSIONAL NOZZLE FLOW WITHVARIOUS GASES, Leland H. Jorgensen, March 1964 TN D 2234 GENERAL SOLUTION OF THELAMINAR COMPRESSIBLE BOUNDARY LAYER IN THESTAGNATION REGION OF BLUNT BODIESIN AXISYMMETRIC FLOW,Fred W. Matting, July 1964 TN D 2235 SPUTTERING AT OBLIQUE ANGLES OF ION INCIDENCE, ThomasW. Snouse, April 1964 TN D 2236 EFFECTS OF SPANWISE VARIATION OFLEADING-EDGE SWEEP ONTHELIFT, DRAG,ANDPITCHING MOMENT OFA WING-BODY COMBINATION AT MACH NUMBERS FROM 0.7 TO 2.94, Raymond M. Hicks and EdwardJ.

Hopkins, April 1964 TND 2238 MIDCOURSE GUIDANCE USINGRADAR TRACKING ANDON-BOARD OBSERVATION DATA,Gerald L. Smith and Eleanor V. Harper, April 1964 TND 2239 AERODYNAMIC ANDROCKET BRAKING OF BLUNT NONLIFTING VEHICLES ENTERING THEEARTH'S ATMOSPHERE AT VERY HIGHSPEEDS, Kenneth K.

Yoshikawa and Bradford H. Wick, April 1964 TND 2240 INVESTIGATION OFMECHANISMS OF POTENTIAL AIRCRAFT FUELTANK VENT FIRESANDEXPLOSIONS CAUSED BYATMOSPHERIC ELECTRICITY, Melvin Gerstein, January 1964 TND 2241 COMPARISON OF FLIGHTPRESSURE MEASUREMENTS WITHWIND-TUNNEL DATA ANDTHEORY FORTHEFORWARD FUSELAGE OFTHEX-15 AIRPLANE AT MACH NUMBERS FROM 0.8 TO 6.0, Jon S. Pyle, January 1964 TND 2242 HIGH-SPEED PHOTOGRAPHIC INVESTIGATION OF THEFORMATION OF DETONA- TION WAVES IN A STOICHIOMETRIC HYDROGEN-OXYGEN MIXTURE,JamesA.

Laughrey, Loren E. Bollinger, and Rudolph Edse, April 1964 RADAR INVESTIGATION OFMETEORS AT HIGHRATES OF DETECTION, C.

TN D 2244 Ellyett, C. S. L. Keay, and E. C. McLauchlan, January 1964 THEORETICAL STUDIES OF A RADIATION-BALANCE, Michael T. Surh TND 2246 and Melvin G. Whybra, April 1964 WINDTUNNEL INVESTIGATION OF TURBULENT BOUNDARY LAYER NOISEAS TN D 2247 RELATED TO DESIGN CRITERIA FORHIGHPERFORMANCE VEHICLES, J. S.

Murphy, D. A. Bies, W. V. Speaker and P. A. Franken, April 1964 THEEDGE OF THEPOLAR PLATEAU FORGALACTIC COSMIC RAYS AND TN D 2248 THEIRCHARGED ALBEDO, J. A. Van Allen and W. C. Lin, April 1964 + IN THEDAYGLOW TN D 2249 AN OBSERVATION OFTHE (0,0) NEGATIVE BAND OF N2 E. C. Zipf, Jr. and W. G. Fastie, April 1964 TND 2250 INSTRUMENTATION FORFARULTRAVIOLET ROCKET SPECTROPHOTOMETRY, William G. Fastie, April 1964 ANALYTICAL EVALUATION OF POSSIBLE NON-CRYOGENIC PROPELLANTS FOR TN D 2253 ELECTROTHERMAL THRUSTORS, John W. Schaefer and John Ferrante, March 1964 TRANSITION CHARACTERISTICS OF A VTOLAIRCRAFT POWERED BY FOUR TN D 2254 DUCTED TANDEM PROPELLERS, Edwin E. Davenport and Kenneth P.

Spreemann,April 1964 FORMATION OFDETONATION WAVES IN HYDROGEN-OXYGEN MIXTURES FROM TN D 2256 0.2 TO 2 ATMOSPHERES INITIAL PRESSURE IN A 54-METER LONG TUBE, Loren E, Bollinger, April 1964 TND 2257 CODING AN ANALOG VARIABLE FORCONSTANT PERCENTAGE ERROR, Rodger A. Cliff, March 1964 AN INSTABILITYEFFECT ONTWO-PHASE HEAT TRANSFER FORSUBCOOLED TN D 2259 WATER FLOWING UNDER CONDITIONS OF ZERO GRAVITY,S. Stephen Papel!, November1964 ROLLING ELEMENT SLIP RINGSFOR VACUUM APPLICATION, Edward J.

TN D 2261 Devine, April 1964 SIMILARSOLUTIONS OF THEBOUNDARY-LAYER EQUATIONS FORPURELY TN D 2262 VISCOUS NON-NEWTONIAN FLUIDS, C. Sinclair Wells, Jr., April EFFECTS OF CESIUM VAPOR ONBAYARD-ALPERT IONIZATION GAGES AT TN D 2264 PRESSURE LESSTHAN10-5 TORR,Robert L. Summers, March 1964 TND 2267 HYDROSTATIC STABILITYOF THELIQUID-VAPOR INTERFACE IN A GRAVITATIONAL FIELD, William J. Masica, Donald A. Petrash, and EdwardW. Otto, May 1964 TN D 2268 PRELIMINARY ANALYSIS OF A SIMULATED METEOR REENTRY AT 9.8 KILO- METERS PERSECOND, W. O. Jewell and A. R. Wineman,April 1964 TND 2269 WIDERANGE PHASE DETECTOR, George B° Robinson, April 1964 TN D 2270 FLIGHTTESTPERFORMANCE ANDDESCRIPTION OF A ROCKET VEHICLE FORPKODUCING LOW-SPEED ARTIFICIALMETEORS, Clarence A. Brown, Jr. and Jean C. Keating, April 1964 TND 2271 LOW-SPEED FREE-FLIGHT STABILITYANDDRAG CHARACTERISTICS OF RADIALLY VENTED PARACHUTES, Sanger M. Burk, Jr., March 1964 TN D 2272 HALLEFFECT DEVICES ASMAGNETOMETERS IN CRYOGENIC APPLICATIONS, ThomasB. Sanford, April 1964 TN D 2273 FREQUENCY RANGES FOREXISTENCE OF WAVES IN A COLD,COLLISION- LESSHYDROGEN PLASMA, Richard R. Woollett, April 1964 TN D 2274 SURFACE FAILURE OFALUMINA BALLSDUETO REPEATED STRESSES APPLIEDIN ROLLING CONTACT AT TEMPERATURES TO 2000°F., Richard J. Parker, Salvatore J. Grisaffe, and Erwin V. Zaretsky, May TN D 2275 SURFACE TOPOGRAPHY OF SINGLE CRYSTANS OF FACE-CENTERED-CUBIC, BODY-CENTERED-CUBIC, SODIUM CHLORIDE, DIAMOND, ANDZINC- BLENDE STRUCTURES, Robert J. Bacigalupi, April 1964 EXPERIMENTAL DETERMINATION OF SODIUM VAPOR EXPANSION CHARACTER- TND 2276 ISTICS WITHINERT-GAS-INJECTION PRESSURE-MEASURING TECHNIQUE, Landon R. Nichols, Stanley M. Nosek, Charles H. Winzig, and Louis J. Goldman,April 1964 TND 2277 COMPARISON ANDEVALUATION OF SEVERAL CHEMICALS AS AGENTS FOR ROCKET-VEHICLE PRODUCTION OF SMOKE TRAILSFORWIND-SHEAR MEASUREMENTS, WadeE. Lanford, Josep J. Janos, and Hal T.

Baber, Jr., September1964 TN D 2278 ANALYTICAL INVESTIGATIONS OF COIL-SYSTEM DESIGN PARAMETERS FOR A CONSTANT-VELOCITY TRAVELING MAGNETIC WAVE PLASMA ENGINE, Raymond W. Palmer, Robert E. Jones, and GeorgeR. Seikel, May TN D 2279 TRANSPORT EQUATIONS FORA PARTIALLY IONIZEDGASIN AN ELECTRIC FIELD, Peter M. Sockol, April 1964 EXPERIMENTAL LOCAL HEAT-TRANSFER ANDAVERAGE FRICTION DATAFOR TND 2280 HYDROGEN ANDHELIUM FLOWING IN A TUBE AT SURFACE TEMPERATUES UP TO 5600°R., Maynard F. Taylor, April 1964 RESEARCH ONRESISTANCE-HEATED HYDROGEN THRUSTORS, John R. Jack, TND 2281 Ernie W. Spisz, and Paul F. Brinich, April 1964 STATICSTABILITYCHARACTERISTICS OF BLUNT LOW-FINENESS-RATIO TN D 2282 BODIES OF REVOLUTION AT A MACH NUMBER OF 24.5 IN HELIUM,Robert D. Witcofski and William C. Woods, May 1964 A STUDY OF THESTABILITYANDLOCATION OF THECENTER OF PRESSURE TN D 2283 ONSHARP, RIGHTCIRCULAR CONES AT HYPERSONIC SPEEDS, Jim A.

Penland, May 1964 CRYOGENIC SOLUTIONS ANDSOLUBILITIES IN LIQUID FLUORINE, Robert TN D 2286 E. Seaver, June 1964 TN D 2288 ADAPTATION OFAN MoS 2 "IN SITU" PROCESS FORLUBRICATING SPACE- CRAFT MECHANICAL COMPONENTS, Charles E. Vest, May 1964 PILOTINGPERFORMANCE DURING THEBOOST OFTHEX-15 AIRPLANE TO TN D 2289 HIGHALTITUDE,Euclid C. Holleman, April 1964 INITIATION OF COOLING DUETO BUBBLE GROWTH ONA HEATING SURFACE, TND 2290 Robert C. Hendricks and Robert R. Sharp, April 1964 A CORRELATION OF FILM-BOILINGHEAT-TRANSFER COEFFICIENTS OBTAINED TN D 2294 WITHHYDROGEN, NOTROGEN, ANDFREON 113 IN FORCED FLOW, UweH.

von Glahn, May 1964 DESIGN ANDOVERALL PERFORMANCE OF AN AXIAL-FLOW-PUMP ROTOR WITH TND 2295 A BLADE TIP DIFFUSION FACTOR OF 0.43, JamesE. Crouse and Donald M. Sandercock, May 1964 MONTE CARLO COMPUTATION OF THESTATISTICS OF THEMIDCOURSE VELOCITY TN D 2296 CORRECTIONS FORA LUNAR MISSION,Gerald L. Smith and Burnett L.

Gadeberg, May 1964 FORCES ACTING ONBUBBLES IN NUCLEATE BOILINGUNDER NORMAL AND TN D 2299 REDUCED GRAVITY CONDITIONS, Edward G. Keshock and Robert Siegel, August 1964 ONTHEAPPLICATION OF PFAFF'SMETHOD IN THETHEORY OF VARIATION TN D 2301 OFASTRONOMICAL CONSTANTS, Peter Musen, April 1964 HEAT-TRANSFER DISTRIBUTION ON70 ° SWEPT SLAB DELTA WINGS AT MACH TN D 2302 NUMBER OF 9.86 AND ANGLES OF ATTACK UP TO 90 ° , Philip E. Everhart and James C. Dunavant, October 1964 GODDARD SPACE FLIGHT CENTER CONTRIBUTIONS TO THE COSPAR MEETING TN D 2303 JUNE 1963, June 1964 TN D 2304 HIGH SPEED VACUUM PERFORMANCE OF MINIATURE BALL BEARINGS LUBRI- CATED WITH COMBINATIONS OF BARIUM, GOLD, AND SILVER FILMS, Thomas W. Flatley, June 1964 TN D 2305 SECULAR AND NON-SECULAR BEHAVIOR FOR THE COLD PLASMA EQUATIONS, David Montgomery and Derek A. Tidman, June 1964 TN D 2308 ANALYTICAL DETERMINATION OF THE TAKE-OFF PERFORMANCE OF SOME REPRESENTATIVE SUPERSONIC TRANSPORT CONFIGURATIONS, Robert L.

Weirich, June 1964 TN D 2309 ANALYSIS OF THE TRAJECTORY AND LARGE-AMPLITUDE MOTIONS OF A SCOUT VEHICLE DURING FOURTH-STAGE REENTRY FLIGHT, Uriel M.

Lovelace, Sherwood Hoffman, and Robert J. Mayhue, June 1964 TN D 2310 DEMODULATION SYSTEM FOR VECTOR MEASUREMENTS FROM SPINNING SATELLITE, William J. Kerwin and Robert Munoz, September 1965 TN D 2311 THE MRIR-PCM TELEMETRY SYSTEM - A PRACTICAL EXAMPLE OF MICRO- ELECTRONIC LOGIC DESIGN, Paul M. Feinberg, July 1964 TN D 2312 DETERMINATION OF MEAN ELEMENTS FOR VINTI'S SATELLITE THEORY, N. L. Bonavito, June 1964 TN D 2313 DATA REPORT ON WHISTLERS OBSERVED BY VANGUARD III (1959 HI), Ivan R. Shapiro, John D. Stolarik, and James P. Heppner, July 1964 TN D 2314 FLIGHT VIBRATION DATA OF THE AEROBEE 150A SOUNDING ROCKET, James A. Nagy and Gomer L. Coble, Jr., June 1964 TN D 2315 A MEDIUM-DATA-RATE DIGITAL TELEMETRY SYSTEM, Marjorie R.

Townsend, Paul M. Feinberg, and John G. Lesko, Jr., June 1964 TN D 2316 DEVELOPMENT OF A 1200 FOOT ENDLESS-LOOP TAPE TRANSPORT FOR SATELLITE APPLICATIONS, Kenneth W. Stark, June 1964 TN D 2317 AN EFFICIENT PCM ERROR CORRECTION AND SYNCHRONIZATION CODE, Marvin S. Maxwell and Richard L. Kutz, June 1964 TN D 2318 EXPLORER XVII (1963 9A) REAL TIME PCM TELEMETRY DATA PROCESSING AND DISPLAY TEST STAND, M. M. Grant, C. C. Stephanides, and W. N. Stewart, June 1964 TN D 2319 A SOLID STATE SATELLITE SEPARATION SEQUENCE TIMER, Justin C.

Shaffert and Thomas D. Clem, July 1964 TN D 2320 DESIGNING TOROIDAL INDUCTORS WITH DC BIAS, G. D. Smith, June TN D 2322 AN INTEGRATED SYSTEM FORCOLLECTING ANDANALYZING ENVIRONMENTAL TESTDATA,Philip Yaffee, Fred Starbuck, JamesW. Bailey, Clifford W. Scott, Augustus C. Johnson, C. Frank Riley, Jr., William E.

Flowers, and Richard K. Hovey, June 1964 TN D 2323 A SMALL MULTI-PURPOSE ROCKET PAYLOAD FORIONOSPHERIC STUDIES, S. J. Bauer and J. E. Jackson, June 1964 TN D 2324 VOLUME ION PRODUCTION IN A TENUOUS HELIUM PLASMA, Ronald J.

Sovie and Barry M. Klein, May 1964 TN D 2325 AN EVALUATION OF ETCHANTS ANDTECHNIQUES USED TO PRODUCE DIS- LOCATION ETCH PITS ONSODIUM CHLORIDE, Carl A. Stearns, June TN D 2326 AN EXPERIMENTAL INVESTIGATION OF HIGHLY UNDEREXPANDED FREEJETS IMPINGING UPON A PARALLEL FLATSURFACE, Allen R. Vick and Earl H. Andrews, Jr., June 1964 TN D 2327 COMPARISONS OF EXPERIMENTAL FREE-JET BOUNDARIES WITHTHEORETICAL RESULTS OBTAINED WITHTHEMETHOD OF CHARACTERISTICS, Allen R.

Vick, Earl H. Andrews, Jr., John S. Dennard, and Charlotte B.

Craidon, June 1964 TN D 2328 COMPARISON OFTHEHYPERSONIC AERODYNAMIC CHARACTERISTICS OF SOME SIMPLE WINGED SHAPES IN AIR ANDHELIUM,ThomasA. Blackstock and Charles L. Ladson, June 1964 TN D 2329 VISIBLE RADIATION DAMAGE EFFECTS OF 40-MEVALPHA PARTICLES ON SODIUM CHLORIDE CRYSTALS, Michael Hacskaylo and C. C. Giamati, June 1964 TND 2330 NUMERICAL SOLUTIONS OF FREE-MOLECULE FLOW IN CONVERGING AND DIVERGING TUBES ANDSLOTS,EdwardA. Richlev and Thaine W.

Reynolds. APPENDIX C: FORTRAN II CODE FORTUBES ANDSLOTS, Carl D. Bogart, June 1964 TN D 2333 A THEORETICAL STUDY OF THEMARTIAN ANDCYTHERIAN IONOSPHERES, R. B. Norton, July 1964 TN D 2334 EFFECTS OF DISTRIBUTED ROUGHNESS HEIGHT ONAERODYNAMIC CHARAC- TERISTICS ANDBOUNDARY-LAYER TRANSITION OF A WING-BODY-TAlL CONFIGURATION AT A MACH NUMBER OF 1.61, Roy V. Harris, Jr., June 1964 TN D 2337 FLIGHTEVALUATION OF THREE TECHNIQUES OFDEMONSTRATING THE MINIMUM FLYINGSPEED OF A DELTA-WING AIRPLANE, Bruce G. Powers and Nell W. Matheny, July 1964 TND 2338 A SIMPLE ABORT SCHEME FORLUNAR LANDINGS, G. Kimball Miller, Jr.

and L. Keith Barker, June 1964 TND 2339 CORRELATION GRAPHS FORSUPERSONIC FLOW AROUND RIGHTCIRCULAR CONES Af ZERO YAW IN AIR AS A PERFECT GAS, Mitchel H. Bertram, June 1964 HEAT-TRANSFER MEASUREMENTS ONA FLATPLATEANDATTACHED FINS AT TN D 2340 MACH NUMBERS OF 3.51 AND4.44, Earl A. Price, Paul W. Howard, and Robert L. Stallings, Jr., June 1964 TND 2341 A NUMERICAL METHOD FORTHEDESIGN OF CAMBER SURFACES OF SUPER- SONIC WINGS WITHARBITRARY PLANFORMS, Harry W. Carlson and Wilbur D. Middleton, June 1964 TN D 2342 A PARAMETRIC STUDY OF HYPERSONIC FLOW FIELDSABOUT BLUNT-NOSED CYLINDERS AT ZERO ANGLE OFATTACK, JamesE. Terry and Carlton S. James, July 1964 TN D 2344 FLOW EVALUATION IN ANARC-HEATED HYPERSONIC WINDTUNNEL, Roger B. Stewart and John E. Grimaud, July 1964 TN D 2346 LOW-SPEED LONGITUDINAL AERODYNAMIC INVESTIGATION OFPARAWINGS AS AUXILIARY LIFTINGDEVICES FORA SUPERSONIC AIRPLANE CONFIGURA- TION, W. Pelham Phillips, July 1964 TN D 2347 SPECTROGRAPHIC DATA OBTAINED FROM REENTRIES AT 10.9 AND8.1 KILO- METERS PERSECOND OF TWO STAGES OF TRAILBLAZER IIb, Kenneth H.

Crumbly, July 1964 TND 2348 FUSED FLUORIDE COATINGS AS SOLIDLUBRICANTS IN LIQUID SODIUM, HYDROGEN, VACUUM, ANDAIR, Harold E. S]iney, ThomasN. Strom, and Gordon P. Allen, August 1964 TND 2349 LOW-SUBSONIC AERODYNAMIC CHARACTERISTICS OFA DELTA-WING RECOVERY DEVICE FORNONLIFTING SPACECRAFT, GeorgeM. Ware, July 1964 TN D 2350 AFTERBODY PRESSURES ONTWO-DIMENSIONAL BOATTAILED BODIES HAVING TURBULENT BOUNDARY LAYERS AT MACH 5.98, W. Frank Staylor and Theodore J. Goldberg, July 1964 TND 2351 ATMOSPHERIC ACOUSTICS AS A FACTOR IN SATURN STATIC TESTING, Richard N. Tedrick, July 1964 TND 2352 AERODYNAMIC CHARACTERISTICS OF SEVERAL PROPOSED VERSIONS OFTHE SATURN V LAUNCH VEHICLE AT MACH NUMBERS 1.57 TO 4.65, Dennis E.

Fuller and Roger H. Fournier, July 1964 A FLIGHTINVESTIGATION OFABLATION ONA BLUNTED CYLINDER-FLARE TN D 2354 CONFIGURATION TO A MACH NUMBER OF 8.48, Clyde W. Winters and William G. Witte, July 1964 RADIANCE OF THEEARTH ANDITS LIMB IN THEMIDDLE ULTRAVIOLET, TND 2355 William C. Hrasky and ThomasB. McKee, July 1964 NUMERICAL INTEGRATION OF DIFFERENTIAL EQUATIONS BYPOWER SERIES TN D 2356 EXPANSIONS, ILLUSTRATED BYPHYSICAL EXAMPLES, Erwin Fehlberg, October 1964 THEORETICAL STUDY OF ZERO-FIELD ELECTRON WORK FUNCTION OF TN D 2357 METAL IMMERSED IN GAS-DIRECT APPLICATION TO CESIUM THERMONIC DIODE,KeungP. Luke and John R. Smith, July 1964 TN D 2362 ROCKET SPECTROPHOTOMETER AIRGLOW MEASUREMENTS IN THEFARULTRA- VIOLET, W. G. Fastie, H. M. Crosswhite, and D. F. Heath, July TN D 2363 QUANTUM MECHANICAL STUDY OF MOLECULES, Roop C. Sahni, July 1964 TN D 2364 AN EXPERIMENTAL INVESTIGATION OF RADIATION EFFECTS IN SEMI- CONDUCTORS, W. Dale Compton, 3uly 1964 ANALYSIS OF NON-LINEAR NOISEIN FDM TELEPHONY TRANSMISSION OVER TN D 2365 AN SSB-PM SATELLITE COMMUNICATION SYSTEM, Paul J. Hefferman, July 1964 AN ANALOG STUDY OF A ROTATING-SOLID-ROCKET CONTROL SYSTEM ANDITS TN D 2366 APPLICATION TO ATTITUDE CONTROL OF A SPACE-VEHICLE UPPER STAGE, A. ThomasYoung and Jack E. Harris, August 1964 TN D 2367 MECHANICAL PROPERTIES OF ECHO II LAMINATE, HowardL. Price and George F. Pezdirtz, August 1964 TN D 2368 AERODYNAMIC CHARACTERISTICS OFA FULL-SCALE FAN-IN-WING MODEL INCLUDING RESULTS IN GROUND EFFECT WITHNOSE-FAN PITCHCONTROL, Jerry V. Kirk, David H. Hickey, and Leo P. Hall, July 1964 TND 2369 ONTHETRANSPORT PROPERTIES OF A PARTIALLY IONIZEDGASIN THE PRESENCE OF ELECTRIC ANDMAGNETIC FIELDS, H. A. Hassan, July 1964 TN D 2371 VACANCY FORMATION IN GOLD UNDER HIGHPRESSURE, Hubert H. Grimes, July 1964 TN D 2373 A REVIEW OFTHESTALLCHARACTERISTICS. OF SWEPT WINGS,Charles W.

Harper and Ralph L. Maki, July 1964 TND 2374 WIND-TUNNEL INVESTIGATION OF BOUNDARY-LAYER CONTROL BY BLOWING ONAN NACA 655-424 AIRFOIL TO EFFECT DRAG REDUCTION, ThomasR.

Turner, July 1964 TN D 2375 ON A MODIFICATION OF HILL'S METHOD OF GENERAL PLANETARY PERTURBA- TIONS, Peter Musen, July 1964 TN D 2377 FLASHING-BEACON EXPERIMENT FOR MERCURY-ATLAS 9 (MA-9) MISSION, Charles C. Laney, Jr., August 1964 TN D 2379 APPROXIMATE SOLUTIONS FOR FLIGHT-PATH ANGLE OF A REENTRY VEHICLE IN THE UPPER ATMOSPHERE, Jack A. _ite and Katherine G. Johnson, July 1964 TN D 2380 INTERFERENCE EFFECTS OF SINGLE AND MULTIPLE ROUND OR SLOTTED _ETS ON A VTOL MODEL IN TRANSITION, Raymond D. Vogler, August 1964 TN D 2381 EFFECT OF WING STALLING IN TRANSITION ON A 1/4-SCALE MODEL OF THE VZ-2 AIRCRAFT, Robert O. Schade and Robert H. Kirby, August ]q64 TN D 2382 FORCE-TEST INVESTIGATION OF A 1/4-SCALE MODEL OF THE MODIFIED VZ-2 AIRCRAFT, Robert H. Kirby, Robert O. Schade, and Louis P. Tosti, August 1964 HEAT-TRANSFER RATES AND ABLATION ON A BLUNTED CYLINDER-FLARE TN D 2383 CONFIGURATION IN FREE FLIGHT UP TO A MACH NUMBER OF 8.98, Clyde W. Winters, August 1964 TN D 2384 DIFFUSER PERFORMANCE OF A MACH 6 OPEN-JET TUNNEL AND MODEL- BLOCKAGE EFFECTS AT STAGNATION TEMPERATURES TO 3,600°F., Raymond E. Midden and Bennie W. Cocke, Jr., July 1964 TN D 2385 COMPARISON OF HEAT-REJECTION AND WEIGHT CHARACTERISTICS OF SEVERAL RADIATOR FIN-TUBE CONFIGURATIONS, Henry C. Haller, July 1964 HEAT TRANSFER ON UNSWEPT AND 38 ° Sk_PT CYLINDRICALLY BLUNTED TN D 2386 WEDGE FINS IN FREE FLIGHT TO MACH NUMBER 4.11, Floyd G. Howard, August 1964 HEAT-TRANSFER AND PRESSURE MEASUREMENTS ON DELTA WINGS AT MACH TN D 2387 NUMBERS OF 3.51 AND 4.65 AND ANGLES OF ATTACK FROM -45 ° TO 45 ° , Robert L. Stallings, Jr., Paige B. Burbank, and Dorothy T.

Howell, August 1964 TN D 2388 VECTORIAL REFLECTANCE OF THE EXPLORER IX SATELLITE MATERIAL, Gerald M. Keating and James A. Mullins, August 1964 SUPERSONIC AERODYNAMIC CHARACTERISTICS OF A SERIES OF BODIES TN D 2389 HAVING VARIATIONS IN FINENESS RATIO AND CROSS-SECTION ELLIPTICITY, Bernard Spencer, Jr., W. Pelham Phillips, and Roger H. Fournier, August 1964 TN D 2390 NUMERICAL CALCULATION OF SUPERSONIC FLOWS OF A PERFECT GASOVER BODIES OF REVOLUTION AT SMALL ANGLES OF YAW,John V. Rakich, July 1964 FULL-SCALE WIND-TUNNEL TESTSOFA NON-ARTICULATED HELICOPTER TN D 2392 ROTOR, John L. McCloud III and JamesC. Biggers, July 1964 TN D 2393 LAMINAR SLIP FLOW HEATTRANSFER IN A PARALLEL-PLATE CHANNEL OR A ROUND TUBE WITHUNIFORM WALL HEATING, Robert M. Inman, August TN D 2400 MAGNETIC FIELDFROM A FINITE THIN CONE BYUSEOF LEGENDRE POLYNOMIALS, Lawrence Flax and Edmund E. Callaghan, August 1964 EXPERIMENTAL INVESTIGATION OFHEAVY-MOLECULE PROPELLANTS IN AN TN D 2401 ELECTRON-BOMBARDMENT THRUSTOR, David C. Byers, William R. Kerslake, and Jack Grobman,August 1964 TN D 2402 THEEFFECTS OFHIGHALTITUDE EXPLOSIONS, Wilmot N. Hess, September1964 TN D 2403 A SIMPLE MODEL OF THEINTERPLANETARY MAGNETIC FIELD. PARTI: CALCULATION OF THEMAGNETIC FIELD, David Stern, August 1964 TN D 2404 A SIMPLE MODEL OF THEINTERPLANETARY MAGNETIC FIELD, PARTII: THECOSMIC RAYANISOTROPY, David Stern, August 1964 TN D 2405 RADIOMETER-PYROMETER FORANALYSIS OF GASEOUS COMBUSTION PRODUCTS, Donald R. Buchele, August 1964 TN D 2406 NONLINEAR-AVERAGING ERRORS IN RADIATION PYROMETRY, Donald R.

Buchele, August 1964 TND 2407 FLIGHT-INFORMATIONAL SENSORS, DISPLAY,ANDSPACE CONTROL OF THE X-15 AIRPLANE FORATMOSPHERIC ANDNEAR-SPACE FLIGHTMISSIONS, Jack Fischel and Lannie D. Webb, August 1964 TN D 2408 MOBILITYOF POSITIVEIONSIN THEIROWN GAS: DETERMINATION OF AVERAGE MOMENTUM-TRANSFER CROSS SECTION, John W. Sheldon, August 1964 TND 2411 ANALYSIS OF FULLYDEVELOPED LAMINAR HEATTRANSFER IN THIN RECTANGULAR CHANNELS WITHHEATING ONTHEBROAD WALLS EXCEPT NEAR THECORNERS, Joseph M. Savino, Robert Siegel, and Edward C. Bittner, August 1964 TN D 2412 AERODYNAMIC DATAONLARGE SEMISPAN TILTINGWING WITH0.6- DIAMETER CHORD, SINGLE-SLOTTED FLAP, ANDSINGLEPROPELLER ROTATING DOWN AT TIP, Marvin P. Fink, Robert G. Mitchell, and Lucy C. White, August 1964 TN D 2413 APPLICATION OF PENETROMETERS TO THESTUDY OF PHYSICAL PROPERTIES OF LUNAR ANDPLANETARY SURFACES, John Locke McCarty, Alfred G.

Beswick, and George W. Brooks, August 1964 TN D 2414 AN INITIAL VALUE METHOD FORTHENUMERICAL TREATMENT OF THEORR- SOMMERFELD EQUATION FORTHECASE OF PLANE POISEUILLE FLOW, Philip R. Nachtsheim, August 1964 TN D 2415 TECHNIQUE FORTHESIMULATION OF LUNAR ANDPLANETARY GRAVITATIONAL FIELDSINCLUDING PILOTMODEL STUDIES,Huey D. Carden, Robert W.

Herr, and George W. Brooks, October 1964 TN D 2417 HEAT-TRANSFER MEASUREMENTS AT A MACH NUMBER OF 8 IN THEVICINITY OFA 90 ° INTERIOR CORNER ALINED WITH THE FREE-STREAM VELOCITY, P. Calvin Stainback, August 1964 TN D 2420 BASE PRESSURE COEFFICIENTS OBTAINED FROM THE X-15 AIRPLANE FOR MACH NUMBERS UP TO 6, Edwin J. Saltzman, August 1964 TN D 2421 HEAT TRANSFER FOR LAMINAR SLIP FLOW OF A RAREFIED GAS BETWEEN PARALLEL PLATES WITH UNSYMMETRICAL WALL HEAT FLUX, Robert M.

Inman, August 1964 TN D 2422 THE COMPOSITION AND THERMODYNAMIC PROPERTIES OF THE PRODUCTS OF CYANOGEN-OXYGEN COMBUSTION, Charles J. Schexnayder, Jr._ August TN D 2423 BREAKUP OF VARIOUS LIQUID JETS BY SHOCK WAVES AND APPLICATIONS TO RESONANT COMBUSTION, Gerald Morrell and Frederick P. Povinelli, August 1964 TN D 2424 BREAKUP OF A LIQUID JET IN A TRANSVERSE FLOW OF GAS, Bruce J.

Clark, August 1964 TND 2425 EFFECT OF INITIAL VELOCITY ON ONE-DIMENSIONAL, AMBIPOLAR, SPACE- CHARGE CURRENTS, Walton L. Howes, August 1964 TND 2426 STUDY OF POWERED-DESCENT TRAJECTORIES FOR MANNED LUNAR LANDINGS, Floyd V. Bennett and Thomas G. Price, August ±964 TND 2427 EFFECT OF AIR INJECTION THROUGH A POROUS SURFACE AND THROUGH SLOTS ON TURBULENT SKIN FRICTION AT MACH 3, Donald I. McRee, John B. Peterson, Jr., and Albert L. Braslow, August 1964 TN D 2428 HEAT-TRANSFER MEASUREMENTS ON A FLAT PLATE AND ATTACHED PRO- TUBERANCES IN A TURBULENT BOUNDARY LAYER AT MACH NUMBERS OF 2.05, 3.51 AND 4.44, Robert L. Stallings, Jr. and Ida K.

Collins, September 1964 ANALYTICAL INVESTIGATION OF THERADIATOR AREA CHARACTERISTICS TN D 2429 OF OUT-OF-PILE THERMIONIC GASCYCLE SPACE POWER SYSTEMS, Michael R. Vanco and Arthur J. Glassman, August 1964 TND 2432 MINIMUM DRAG BODIES WITHCROSS-SECTIONAL ELLIPTICITY, Jerrold H. Suddath and Waldo I. Oehman,September 1964 TND 2433 MEASUREMENT OFERRORS IN MANUALLY RECORDING TRANSIT TIMESOF STARS ANDDISTANT PLANETS, Kenneth R. Garren and Patrick A.

Gainer, August 1964 TN D 2435 LAMINAR ANDTURBULENT HYDROGEN HEATTRANSFER ANDFRICTION COEFFICIENTS OVER PARALLEL PLATES AT 5000°R., Jack G. Slaby, William L. Maag, and Byron L. Siegel, August 1964 TN D 2437 DETAILED DESCRIPTION ANDFLIGHTPERFORMANCE OF THERAM B VEHICLE,JamesL. Raper, Robert J. Keynton, and Gerard E.

Woodbury, September1964 TN D 2438 FREE-FLIGHT TESTRESULTS ONTHEPERFORMANCE OF CORK AS A THERMAL PROTECTION MATERIAL, Randolph A. Graves, Jr., and ThomasE.

Walton, Jr., September 1964 TN D 2440 A POSSIBLE REGENERATIVE, MOLTEN-SALT, THERMOELECTRIC FUELCELL, Jacob Greenberg, Lawrence H. Thaller, and Donald E. Weber, August 1964 TN D 2441 SOME OPTICAL TECHNIQUES FORTEMPERATURE ANDCONCENTRATION MEASUREMENTS OF COMBUSTION IN SUPERSONIC STREAMS, Erwin A.

Lezberg and Donald R. Buchele, August 1964 TN D 2442 A METHOD FORDETERMINING NODAL ARRIVAL TIMESAT THEMOON FROM PRECESSING NEAR-EARTH PARKING ORBITS HAVING VARIOUS INCLINATIONS, John R. Unangst and Jesse D. Timmons, August 1964 TN D 2444 HYDROSTATIC STABILITYOF THELIQUID-VAPOR INTERFACE IN A LOW- ACCELERATION FIELD, William J. Masica, Joseph D. Derdul, and Donald A. Petrash, August 1964 TN D 2446 EXPERIMENTAL TECHNIQUE FORMEASURING TOTAL AERODYNAMIC HEATING RATES TO BODIES OFARBITRARY SHAPE WITHRESULTS FORMACH 7, L. RoaneHunt and R. R. Howell, September 1964 TN D 2448 ACCURACY OFNAVIGATION IN VARIOUS REGIONS OF EARTH-MOON SPACE WITHVARIOUS COMBINATIONS OF ONBOARD OPTICAL MEASUREMENTS, Alton P. Mayo, RubenL. Jones, and William M. Adams, September 1964 TN D 2449 STUDY OF CONTAMINATION-INDUCED LUMINOSITY AHEAD OF A BLUNT BODY IN THELANGLEY HOTSHOT TUNNEL, William D. Harvey and William V.

Feller, August 1964 TN D 2450 ONTHESTABILITYOF A LIQUIDLAYER OFUNIFORM THICKNESS SPREAD OVER A RIGID CIRCULAR CYLINDER SUBJECTED TO LATERAL ACCELERATIONS, Richard M. Beam,August 1964 TN D 2451 A PILOTED MOTION SIMULATOR INVESTIGATION OF VTOLHEIGHT-CONTROL REQUIREMENTS, Ronald M. Gerdes, August 1964 TN D 2452 THEX-IRRADIATION OF HYDRAZINE ANDI, I-DIMETHYLHYDRAZINE, Harold Lucien and Murray L. Pinns, August 1964 TN D 2453 FRICTION,WEAR, ANDDYNAMIC SEALSTUDIES IN LIQUID FLUORINE ANDLIQUIDOXYGEN, W. F. Hady, G. P. Allen, H. E. Sliney, and R. L. Johnson, August 1964 TN D 2454 TABLES OF X-COEFFICIENTS ANDA-FACTORS FORTRIPLEANGULAR CORRELATION ANALYSIS,Jag J. Singh and Chris Gross, September TN D 2457 SUFFICIENT CONDITIONS FORSTABILITY" IN THELARGE" OF A NON- LINEARSYSTEM OF DIFFERENTIAL EQUATIONS, Jerrold H. Suddath, September1964 TN D 2458 TIME RESPONSE OF LIQUID-VAPOR INTERFACE AFTER ENTERING WEIGHT- LESSNESS, Clifford E. Siegert, Donald A. Petrash, and Edward W. Otto, August 1964 TN D 2460 LOW-COVERAGE HEATS OF A ADSORPTION. III - ALKALI METAL IONSON TUNGSTEN; ATOM-METAL INTERACTION THEORY, Harold E. Neustadter and Keung P. Luke, August 1964 TN D 2462 WIND-TUNNEL MEASUREMENTS ONA LIFTING ROTOR AT HIGHTHRUST CO- EFFICIENTS ANDHIGHTIP-SPEED RATIOS,George E. Sweet, Julian L. Jenkins, Jr., and Matthew M. Winston, September1964 TN D 2463 THEORETICAL LAMINAR CONVECTIVE HEATTRANSFER ANDBOUNDARY- LAYER CHARACTERISTICS ONCONES AT SPEEDS TO 24 KM/SEC,Gary T. Chapman,August 1964 TN D 2465 EFFECTS OF CONFIGURATION GEOMETRY ONTHETRANSONIC AERODYNAMIC CHARACTERISTICS OF CANARD AIRPLANE CONFIGURATIONS, JamesA.

Blackwell, Jr. and ThomasC. Kelly, September 1964 TN D 2466 COMPARISON OFGROUND TESTS ANDORBITAL LAUNCH RESULTS FORTHE EXPLORER IX ANDEXPLORERE XIX SATELLITES, Charles V. Woerner and Claude W. Coffee, Jr., September 1964 TND 2468 THEMICROMETEOROID SATELLITE EXPLORER XIII (1961 CHI) COLLECTED PAPERS ONDESIGN ANDPERFORMANCE, Charles T. D'Aiutolo, November TN D 2469 POWER SPECTRAL MEASUREMENT OF ATMOSPHERIC TURBULENCE IN SEVERE STORMS ANDCUMULUS CLOUDS, Richard H. Rhyne and Roy Steiner, October 1964 TN D 2471 THEEQUILIBRIUM FREESURFACE OF A CONTAINED LIQUIDUNDER LOW GRAVITY ANDCENTRIFUGAL FORCES, W. ThomasBlackshear and Donald G. Eide, October 1964 TND 2472 HYPERVELOCITY IMPACT DAMAGE CHARACTERISTICS IN ARMORED SPACE RADIATOR TUBES,SeymourLieblein, Nestor Clough, and A. R.

McMillan, September 1964 TN D 2473 HEAT-TRANSFER MEASUREMENT FORBINARY GASLAMINAR BOUNDARY LAYERS WITHHIGHRATES OF INJECTION,C. C. Pappas and Arthur F. Okuno, September 1964 TN D 2474 ANALYSIS ANDDESIGN PROCEDURES FORA FLAT, DIRECT-CONDENSING, CENTRAL FINNED-TUBE RADIATOR, Richard P. Krebs, Henry C. Haller, and Bruce M. Auer, September 1964 TN D 2475 ANALYTICAL STUDY OF THEEXPANSION ANDCONDENSATION BEHAVIOR OF ALKAI-METAL ANDMERCURY VAPORS FLOWING THROUGH NOZZLES, Arthur J. Glassman, September 1964 TN D 2476 RESONANT INTERACTION OF VERTICALLY POLARIZED PLANE ELECTRO- MAGNETIC WAVES WITHTHIN SLABS OF PLASMA, Paul D. Rowley and Virginia L. Sorensen, September 1964 TN D 2478 EXPERIMENTAL RESULTS OF COOLING _ 12.5 ° SEMIVERTEX ANGLE CONE BY EJECTION OF HYDROGEN AND HELIUM FROM ITS APEX AT MACH 7, George F. Klich and Edward W. Leyhe, September 1964 TN D 2480 MEASUREMENTS OF EFFLUX PATTERNS AND FLOW RATES FROM CYLINDRICAL TUBES IN FREE-MOLECULE AND SLIP FLOWS, Harlan Cook and Edward A. Richley, September 1964 TN D 2481 BLADE-ELEMENT PERFORMANCE OF 0.7 HUB-TIP RADIUS RATIO AXIAL- FLOW-PUMP ROTOR WITH TIP DIFFUSION FACTOR OF 0.43, James E.

Crouse and Donald M. Sandercock, September 1964 TND 2484 SEMICLASSICAL CALCULATION OF THE DIFFERENTIAL SCATTERING CROSS SECTION WITH CHARGE EXCHANGE: CESIUM IONS IN CESIUM VAPOR, John W. Sheldon, September 1964 TN D 2485 A MODERN TRANSISTORIZED INSTRUMENTATION SYSTEM FOR ACOUSTICAL DATA ACQUISITION, Wade D. Dorland, C. C. Thornton, and Denis U. Noiseux, September 1964 TN D 2487 SUMMARY OF BRAYTON CYCLE ANALYTICAL STUDIES FOR SPACE-POWER SYSTEM APPLICATIONS, Arthur J. Glassman, September 1964 TN D 2488 A SERIESSOLUTION FORSOME PERIODIC ORBITS IN THERESTRICTED THREE-BODY PROBLEM ACCORDING TO THEPERTURBATION METHOD, Su- Shu Huang, September1964 TN D 2489 LONGITUDINAL CHARACTERISTICS OF SEVERAL CONFIGURATIONS AT HYPERSONIC MACH NUMBERS IN CONICAL ANDCONTOURED NOZZLES, JamesP. Arrington, Roy C. Joiner, Jr., and Arthur Henderson, Jr., September 1964 TN D 2490 A RUTILETRAVELING WAVE MASER, C. Curtis Johnson, September1964 TN D 2491 BOUNDARY LAYERS ONROTATING SPHERES ANDOTHER AXISYMMETRIC SHAPES, Jay Fox, September1964 TN D 2492 LOW-SPEED FORCE ANDFLIGHTINVESTIGATION OFA MODEL OFA MODIFIED PARAWING UTILITY VEHICLE,Joseph L. Johnson, Jr., March 1965 TN D 2493 EVALUATION OF SELECTED REFRACTORY OXIDEMATERIALS FORUSEIN HIGH-TEMPERATURE PEBBLE-BED WIND-TUNNEL HEATEXCHANGERS, John D. Buckley and Bennie W. Cocke,Jr., September1964 TN D 2494 SUPERPOSITION CALCULATION OFTHICKSOLENOID FIELDSFROM SEMI- INFINITE SOLENOID TABLES,Gerald V. Brown and LawrenceFlax, September 1964 TN D 2495 PROGRESS IN SUPERALLOYS, John C. Freche, October 1964 TN D 2496 REAL-GAS INVISCIDNOZZLE CONTOURS FORNITROGEN AT MACH 15, 17, AND19 WITHTABULATED PROPERTIES FORTHECALCULATION OF BOUNDARY-LAYER EFFECTS, Charles B. Johnson and JamesC. Ellison, November1964 TND 2497 DYNAMIC MODEL INVESTIGATION OF THELANDING CHARACTERISTICS OF A MANNED SPACECRAFT, William C. Thompson,March 1965 TND 2498 WIND-TUNNEL TESTOFA FULL-SCALE, i.I PRESSURE RATIO,DUCTED LIFT-CRUISEFAN, DemoJ. Giulianetti, JamesC. Big_ers, and Victor R. Corsiglia, November1964 TND 2501 SURFACE PRESSURE ANDTURBULENT AIRFLOW IN TRANSVERSE RECTANGULAR NOTCHES, Jay Fox, November1964 TN D 2502 APPROXIMATE FORMULAS FORVISCOSITY ANDTHERMAL CONDUCTIVITY OF GASMIXTURES, Richard S. Brokaw, November1964 TN D 2504 A SIMPLIFIEDGUIDANCE SCHEME FORABORTING LUNAR LANDINGS, G.

Kimball Miller, Jr., December1964 GASEOUS ENVIRONMENT CONSIDERATIONS ANDEVALUATION PROGRAMS TN D 2506 LEADING TO SPACECRAFT ATMOSPHERE SELECTION, Edward L. Michel, George B. Smith, Jr., and Richard S. Johnston, January 1965 TN D 2507 EXPERIMENTAL OBSERVATIONS OF TRANSIENT BOILINGOF SUBCOOLED WATER ANDALCOHOL ONA HORIZONTAL SURFACE, Robert W. Graham, January 1965 TN D 2508 CALIBRATION OF SOLAR CELLSUSINGHIGH-ALTITUDE AIRCRAFT, Henry W.Brandhorst, Jr. and Earle O. Boyer, February 1965 TN D 2509 PERFORMANCE OF SOLAR REFLECTORS WHEN APPLIED TO STORAGE OF CRYOGENIC PROPELLANTS IN SPACE,Curt H. Liebert and Robert R. Hibbard, November1964 TN D 2510 METALLURGICAL BONDING OF PLASMA-SPRAYED TUNGSTEN ONHOT MOLYBDENUM SUBSTRATES, William A. Spitzig and Salvatore J.

Grisaffe, November1964 TN D 2511 TURBULENT TEMPERATURE FLUCTUATIONS ANDTWO-DIMENSIONAL HEAT TRANSFER IN A UNIFORM SHEAR FLOW, Jay Fox, November1964 TN D 2512 VAPORIZATION OF TANTALUM-CARBIDE-HAFNIUM-CARBIDE SOLIDSOLUTIONS AT 2500 ° TO 3000 ° K., Daniel L. Deadmore, November 1964 TN D 2513 INFLUENCE OF CRYSTAL STRUCTURE ON FRICTION CHARACTERISTICS OF RARE-EARTH AND RELATED METALS IN VACUUM TO i0 -I0 MILLIMETER OF MERCURY, Donald H. Buckley and Robert L. Johnson, November 1964 TN D 2514 STUDY OF WETTING AND NONWETTING MERCURY CONDENSING PRESSURE DROPS, Alfred Koestel, Martin U. Gutstein, and Robert T. Wainwright, November 1964 TN D 2515 APPROXIMATE PREDICTIONS OF THE TRANSPORT OF THERMAL RADIATION THROUGH AN ABSORBING PLANE LAYER, Max A. Heaslet and Franklyn B. Fuller, November 1964 TN D 2516 RELAY i TRAPPED RADIATION MEASUREMENTS, C. E. Mcllwain, R. W.

Fillius, J. Valerio, and A. Dave, December 1964 TN D 2518 EFFECTS OF DIELECTRIC COVERS OVER SHUNT SLOTS IN A WAVEGUIDE, William F. Croswell and Robert B. Higgins, December 1964 TN D 2519 EXPERIMENTAL INVESTIGATION OF SLOSH-SUPPRESSION EFFECTIVENESS OF ANNULAR-RING BAFFLES IN SPHERICAL TANKS, Irving E. Sumner, November 1964 TN D 2520 APPLICATION OF A LUNAR LANDING TECHNIQUE FOR LANDING FROM AN ELLIPTIC ORBIT ESTABLISHED BY A HOHMANN TRANSFER, L. Keith Barker, December 1964 EXPERIMENTAL HEAT-TRANSFER ANDBOUNDARY-LAYER BEHAVIOR WITH TND 2521 100-CPSFLOW OSCILLATIONS, Charles E. Feiler, December1964 INTENSITY ANDINTENSITY RATIOOF PRINCIPAL SINGLET ANDTRIPLET TND 2522 LINES OFMOLECULAR HYDROGEN, GeorgeM. Prok and Clifford A.

McLean, December1964 NASAENGINEERING MODELS OF THEMARS ATMOSPHERE FORENTRY VEHICLE TN D 2525 DESIGN,GeorgeM. Levin, Dallas E. Evans, and Victor Stevens, November1964 NUMERICAL CALCULATION OF POTENTIAL-ENERGY CURVES BYRYDBERG- TN D 2526 KLEIN-REES METHOD, Frank J. Zeleznik, December1964 TN D 2527 THEORETICAL MODEL ATMOSPHERES OF VENUS, Robert B. Owen, January RADIOMETRIC OBSERVATIONS OFTHEEARTH'S HORIZON FROM ALTITUDE TN D 2528 BETWEEN 300 AND600 KILOMETERS, ThomasB. McKee,Ruth I. Whitman, and Charles D. Engle, December1964 SOLAR-CELL PERFORMANCE AT HIGHTEMPERATURES, Jacob D. Broder, TN D 2529 Harold E. Kautz, Joseph Mandelkorn, Lawrence Schwartz, and Robert P. Ulman, December1964 PRELAUNCH ANALYSIS OF HIGHECCENTRICITY ORBITS,Barbara E.

TN D 2530 Shute, December1964 TND 2531 A TECHNIQUE FORVISUALDETECTION OF DISTANT OBJECTS IN SPACE BYUSEOF OPTICAL FILTERING,Kenneth R. Garren, December1964 VIBRATION ANDSTABILITYANALYSIS OF COMPRESSED ROCKET VEHICLES, TN D 2533 Rudolf F. Glaser, January 1965 RADIATION CLIMATOLOGY IN VISIBLE ANDINFRARED FROM TIROSMETEOR- TND 2534 OLOGICAL SATELLITES (WITHLIST OF REFERENCES), W. R. Bandeen, M. Halev, and I. Strange, June 1965 CONVERSION OF A SPACECRAFT DESIGNED FORMANNED SPACE FLIGHTTO A TND 2535 RECOVERABLE ORBITING ASTRONOMICAL OBSERVATORY, Windsor L. Sherman, December1964 GRAPHICAL RESULTS FORLARGE-AMPLITUDE UNSTEADY ONE-DIMENSIONAL TN D 2536 WAVES IN _GNETIZEDCOLLISION-FREE PLASMAS WITHDISCRETE STRUCTURE, Wm.Prichard Jones and Vernon J. Rossow, January 1965 WIND-TUNNEL INVESTIGATION OFA TILT-WINGVTOLAIRPLANE WITH TN D 2538 ARTICULATED ROTORS, JamesA. Weiberg and DemoJ. Giulianetti, March 1965 SONIC-BOOM EXPOSURES DURING FAACOMMUNITY-RESPONSE STUDIES OVER TN D 2539 A 6-MONTH PERIOD IN THEOKLAHOMA CITY AREA,David A. Hilton, Vera Huckel, Roy Steiner, and DomenicJ. Maglieri, December1964 EFFECTS OF CONCENTRATION ANDVIBRATIONAL RELAXATION ONINDUCTION TN D 2540 PERIOD OF HYDROGEN-OXYGEN REACTION, Frank E. Belles and Milton R. Lauver, December1964 RADIATION PROCESSES RELATED TO OXYGEN-HYDROGEN COMBUSTION AT HIGH TN D 2541 PRESSURES, Marshall C. Burrows, December1964 ANALYTIC SOLUTIONS TO THEIGNITIONKINETICSOF THEHYDROGEN-OXYGEN TN D 2542 REACTION, Richard S. Brokaw, December1964 EFFECT OF ENVIRONMENTAL PARAMETERS ONTHEPERFORMANCE OF LOW- TN D 2543 DENSITY SILICONE-RESIN ANDPHENOLIC-NYLON ABLATION MATERIALS, Ronald K. Clark, January 1965 TN D 2545 NON-HOOKEAN, PREMACROYIELD STRESS-STRAIN BEHAVIOR OF SEVERAL IONIC SINGLECRYSTALS, Carl A. Stearns and Edward R. Gotsky, December1964 TND 2546 USEOF ARBITRARY QUASI-ORTHOGONALS FORCALCULATING FLOW DISTRI- BUTION IN THEMERIDIONAL PLANE OF A TURBOMACHINE, Theodore Katsanis, December1964 TN D 2547 ENERGY TRANSFER FROM A LIQUID TOGASBUBBLES FORMING AT A SUB- MERGED ORIFICE, M. R. L'Ecuyer and S. N. B. Murthy, January RELATION OF EMITTED ULTRAVIOLET RADIATION TO COMBUSTION OF TN D 2548 HYDROGEN ANDOXYGEN AT 20 ATMOSPHERES, Marshall C. Burrows and Ronald Razner, December1964 FINITE GEOMETRY CORRECTIONS TO GAMMA-RAY ANGULAR CORRELATION TN D 2549 MEASUREMENTS, Jag J. Singh and Chris Gross, January 1965 APPLICATION OFGENERALIZED NEWTONIAN THEORY TO THREE-DIMENSIONAL TN D 2550 SHARP-NOSE SHOCK-DETACHED BODIES AT MACH 6 FORANGLES OF ATTACK UP TO 25° , George C. Ashby, Jr. and Theodore J. Goldberg, January EFFECTS OF CANOPY SHAPE ONLOW-SPEED AERODYNAMIC CHARACTERISTICS TN D 2551 OF A 55 ° SWEPT PARAWING WITH LARGE-DIAMETER LEADING EDGES, Delwin R. Croom, Rodger L. Naeseth, and William C. Sleeman, Jr., December LARGE-SCALE WIND-TUNNEL TESTS ON AN ASPECT RATIO 2.17 DELTA-WING TN D 2552 MODEL EQUIPPED WITH MIDCHORD BOUNDARY-LAYER CONTROL FLAPS, David G. Koenig and Victor P. Corsiglia, December 1964 TND 2553 PERFORMANCE OF 84 ° FLAT-PLATE HELICAL INDUCER AND COMPARISON WITH PERFORMANCE OF SIMILAR 78 ° AND 80.6 ° INDUCERS, Douglas A.

Anderson, Richard F. Soltis, and Donald M. Sandercock, December TN D 2554 MAGNETIC BREAKDOWN IN A FINITE ONE-DIMENSIONAL MODEL, Gabriel Allen, December 1964 TN D 2555 MASS SPECTRA OF POSITIVE AND NEGATIVE IONS IN NITROUS AND NITRIC OXIDES, C. S. Harden and E. E. Muschitz, Jr., December 1964 TND 2556 RADIANT-INTERCHANGE VIEW FACTORS AND LIMITS OF VISIBILITY FOR DIFFERENTIAL CYLINDRICAL SURFACES WITH PARALLEL GENERATING LINES, Carol J. Sotos and Norbert O. Stockman, December 1964 TN D 2557 PRELIMINARY EXPERIMENTS WITH A VELOCITY-SELECTED ATOMIC-BEAM APPARATUS, Eugene J. Manista and John W. Sheldon, December 1964 TN D 2558 ANALYSIS OF A DOUBLE FIN-TUBE FLAT CONDENSER-RADIATOR AND COMPARISON WITH A CENTRAL FIN-TUBE RADIATOR, Henry C. Haller, December 1964 TND 2559 FLIGHT INVESTIGATION OF STEEP INSTRUMENT APPROACH CAPABILITIES OF A C-47 AIRPLANE UNDER MANUAL CONTROL, Albert W. Hall and Donald J. McGinley, Jr., January 1965 TN D 2560 WIND-TUNNEL-WALL EFFECTS AND SCALE EFFECTS ON A VTOL CONFIGURA- TION WITH A FAN MOUNTED IN THE FUSELAGE, Edwin E. Davenport and Richard E. Kuhn, January 1965 TN D 2562 FILTER-WHEEL SOLAR SIMULATOR, Joseph Mandelkorn, Jacob D. Broderp and Robert P. Ulman, January 1965 TN D 2564 GRADUAL TRANSITION OF NUCLEATE BOILING FROM DISCRETE-BUBBLE REGIME TO MULTI-BUBBLE REGIME, Yih-Yun Hsu, December 1964 TND 2565 REAL-GAS EFFECTS IN CRITICAL-FLOW-THROUGH NOZZLES AND TABULATED THERMODYNAMIC PROPERTIES. Robern C. Johnson, APPENDIX B: CURVE FITS FOR EQUATIONS OF STATE, Jeanne V. Szel, January 1965 TN D 2567 A METHOD FOR CALIBRATION OF GAS-COMPOSITION-SENSITIVE PRESSURE GAGES IN CONDENSIBLE VAPORS, Leonard T. Melfi, Jr., and Paul R. Yeager, January 1965 TN D 2568 ANOMALOUS ELECTRICAL RESISTIVITY OF PALLADIUM-DEUTERIUM SYSTEM BETWEEN 4.2 ° AND 300°K., Robert J. Smith, January 1965 TN D 2570 A NUMERICAL METHOD FOR CALCULATING THE FLAT-PLATE PRESSURE DISTRIBUTIONS ON SUPERSONIC WINGS OF ARBITRARY PLANFORM, Wilbur D. Middleton and Harry W. Carlson, January 1965 SOME TRANSIENT ELECTRICAL CHARACTERISTICS OF THEEXHAUST OF A TN D 2571 SELF-CROWBARRED COAXIAL PLASMA GUN,Charles J. Michels, January PHOTOGRAPHIC STUDY OFPROPELLANT OUT-FLOW FROM A CYLINDRICAL TN D 2572 TANKDURING WEIGHTLESSNESS, Ralph C. Nussle, Joseph D. Derdul, and Donald A. Petrash, January 1965 TN D 2573 METEORIC FLUXANDDENSITY FIELDSABOUT A FINITE ATTRACTIVE CENTER GENERATED BYA STREAM MONOENERGETIC ANDMONODIRECTIONAL AT INFINITY, D. P. Hale and J. J. Wright, January 1965 TN D 2574 METEORIC FLUXANDDENSITY FIELDSABOUT AN INFINITESIMAL ATTRACTIVE CENTER GENERATED BY A STREAM MONOENERGETIC ANDMONODIRECTIONAL AT INFINITY, D. P. Hale and J. J. Wright, January 1965 TN D 2575 SOME ASPECTS OF THEDISTRIBUTION OFMETEORIC FLUXABOUR AN ATTRAC- TIVE CENTER, R. D. Shelton, H. E. Stern, and D. P. Hale, January PERFORMANCE OF SEVERAL ABLATION MATERIALS EXPOSED TOLOWCONVECTIVE TN D 2577 HEATING RATES IN AN ARC-JET STREAM, Marvin B. Dowand William D.

Brewer, January 1965 A FORTRAN PROGRAM TO CALCULATE THEFLOW FIELDANDPERFORMANCE OF TN D 2579 AN AXIALLYSYMMETRIC deLAVAL NOZZLE, D. Thompson,E. H. Ingram, C. T. K. Young, and J. B. Cox, January 1965 TN D 2580 TRANSPORT PROPERTIES OF DILUTEGASMIXTURES, Richard S. Brokaw, Roger A. Svehla, and Charles E. Baker, January 1965 TN D 2581 EFFECTIVENESS OF VARIOUS AGENTS FORSUPPRESSING IGNITIONOF RP-I ANDHYDROGEN UNDER FLOW CONDITIONS, J. B. Gayle and H. E. Tubbs, January 1965 TND 2583 APPARATUS FORMEASURING EMITTANCE ANDABSORPTANCE ANDRESULTS FOR SELECTED MATERIALS, Henry B. Curtis and Ted W. Nyland, January TND 2584 SOME EFFECTS OF UNCERTAINTIES IN ATMOSPHERE STRUCTURE ANDCHEMICAL COMPOSITION ONENTRY INTOMARS,Robert L. McKenzie, January 1965 TN D 2585 AN ANALYSIS OFTHEPROBLEM OF TANKPRESSURIZATION DURING OUTFLOW, William H. Roudebush,January 1965 TN D 2586 MODEL INVESTIGATION OFTECHNIQUE FORCONDUCTING FULL-SCALE LANDING- IMPACT TESTS AT SIMULATED LUNAR GRAVITY,Ulysse J. Blanchard, March 1965 TN D 2587 EXPERIMENTAL EFFECTS OF PROPELLANT-INTRODUCTION MODE ONELECTRON- BOMBARDMENT ION ROCKET PERFORMANCE, Paul D. Reader, January 1965 TND 2588 QUADRATURE FORMULAS FORTHE A AND _ OPERATORS OF RADIATIVE TRANSFER, Mark Cane, January 1965 TN D 2589 APPLICATION OF THEDOUBLE SPHERICAL HARMONICS METHOD TO THEONE- DIMENSIONAL RADIATION-TRANSFER EQUATION, Leo G. Le sage, February TN D 2591 MEASUREMENT OF THEEFFECTS OF FAST-NEUTRON RADIATION ONLIQUID OTTHO- ANDPARA-HYDROGEN, JamesW. Blue and Theodore E. Fessler, February 1965 TND 2592 FRAGMENTATION OFANTHRACENE IN AN ELECTRON-BOMBARDMENT ION SOURCE, Nelson L. Milder, January 1965 TND 2593 A FLIGHTINVESTIGATION OF THESCOUT FOURTH-STAGE DIAPHRAGM SEPARATION DISTURBANCES, SeymourSalmirs, February 1965 TND 2594 IMPROVED METHOD OF PREDICTING SURFACE TEMPERATURES IN HYDROGEN- COOLED NUCLEAR ROCKET REACTOR AT HIGHSURFACE-TO BULK-TEMPERATURE RATIOS,John V. Miller and Maynard F. Taylor, January 1965 TN D 2595 EXPERIMENTAL LOCAL HEAT-TRANSFER DATAFORPRECOOLED HYDROGEN AND HELIUM AT SURFACE TEMPERATUES UP TO 5300°R., Maynard F. Taylor, January 1965 TN D 2597 AN EXPERIMENTAL EVALUATION OFARRAY OF THREE ELECTRON-BOMBARDMENT ION THRUSTORS, EugeneV. Pawlik, January 1965 TN D 2598 USEOFTEMPERATURE BUFFERED ARGON ARCIN SPECTROGRAPHIC TRACE ANALYSIS,William A. Gordon, January 1965 TN D 2600 COMPOSITION ANDTHERMODYNAMIC PROPERTIES OFREACTING GASMIXTURES UNDER HIGHPRESSURE USINGTHELEWISANDRANDALL RULE,WayneD.

Erickson and JamesF. Roach, January 1965 TN D 2601 ZERO-DENSITY COSMOLOGICAL MODELS ANDTHEIRAPPLICABILITY TO THE OBSERVED UNIVERSE, Windsor L. Sherman,February 1965 TN D 2605 MARS NONSTOP ROUND-TRIP TRAJECTORIES, Roger W. Luidens and Jay M. Kappraff, January 1965 TN D 2606 AERODYNAMIC CHARACTERISTICS OFLENTICULAR ANDELLIPTIC SHAPED CONFIGURATIONS AT A MACH NUMBER OF 6, J. WayneKeyes, February TN D 2608 RADIATION MEASUREMENTS ONTHENINTHMERCURY-ATLAS MISSION(MA-9), Carlos S. Warren and BennyR. Baker, February 1965 TN D 2609 THERMAL DESIGN ANDTHERMAL DATAANALYSIS OF SA-5 PAYLOAD, Tommy C. Bannister and Cliff L. Lumpkin, February 1965 TN D 2610 LAMINAR BOUNDARY-LAYER SEPARATION INDUCED BY FLARES ONCYLINDERS WITHHIGHLY COOLED BOUNDARY LAYERS AT MACH NUMBER OF 15, Donald M. Kuehn, January 1965 TN D 2611 A CRITICALEVALUATION OFMETHODS FORCALCULATING TRANSPORT CO- EFFICIENTS OFPARTIALLY ANDFULLYIONIZEDGASES, Warren F. Ahtye, January 1965 DIFFUSION OF AURORAL ELECTRONS IN THEATMOSPHERE, Kaichi Maeda, TN D 2612 February 1965 SOLAR SIMULATION TESTING OF AN EARTH SATELLITE AT GODDARD SPACE TN D 2614 FLIGHTCENTER, R. E. Bernier, R. H. Hoffman, A. R. Timmins, and E. I. Power, January 1965 TN D 2615 INLETNOISESTUDIES FOR AN AXIAL-FLOW SINGLE-STAGE COMPRESSOR, W. Latham Copeland, February 1965 TN D 2616 MECHANICAL PROPERTIES, OXIDATION CHARACTERISTICS, ANDWELDABILITY OF TWO UNCOATED ANDCOATED VANADIUM-BASE ALLOYS,Dick M. Royster, Charles R. Manning, Jr., and Cynthia A. Dysleski, February 1965 TN D 2617 DISTORTION OF ATOMIC-BEAMVELOCITY DISTRIBUTIONS DUETO CLASSICAL HARD-SPHERE GASSCATTERING, EugeneJ. Manista, January 1965 FOUR-DIMENSIONAL DERIVATION OF THEELECTRODYNAMIC JUMP CONDITIONS, TND 2618 TRACTIONS, ANDPOWER TRANSFER AT A MOVING BOUNDARY, Robert C.

Costen, February 1965 EXPERIMENTAL INVESTIGATION OF ELECTRIC DRAG ONSPHERICAL SATELLITE TN D 2619 MODELS, William C. Pitts, and Earl D. Knechtel, February 1965 TN D 2620 EFFECTS OF 1.2 AND0.30 MEVELECTRONS ONTHEOPTICAL TRANSMISSION PROPERTIES OF SEVERAL TRANSPARENT MATERIALS, Gilbert A. Haynes and William E. Miller, March 1965 OFF-DESIGN PERFORMANCE PREDICTION WITHEXPERIMENTAL VERIFICATION TN D 2621 FORA RADIAL-INFLOW TURBINE,SamuelM. Futral, Jr. and Charles A. Wasserbauer, February 1965 TND 2622 TRANSONIC AERODYNAMIC CHARACTERISTICS OF A SERIES OF BODIES HAVING VARIATIONS IN FINENESS RATIOANDCROSS-SECTIONAL ELLIPTICITY, Bernard Spencer, Jr. and W. PelhamPhillips, February 1965 EFFECT OF FIN-FLARE COMBINATIONS ONTHEAERODYNAMIC CHARACTERISTICS TN D 2623 OFA BODY AT MACH NUMBERS 1.61 AND2.20, Clyde Hayes and Roger H.

Fournier, February 1965 NEWTONIAN AERODYNAMICS FORBLUNTED RAKED-OFF CIRCULAR CONES AND TN D 2624 RAKED-OFF ELIPTICALCONES, Edward E. Mayo, Robert H. Lamb, and Paul O. Romere,May 1965 TN D 2625 ANALYSIS OF NOTCH NETWORKS CONTAINING SYNCHRONOUSLY COMMUTATED CAPACITORS OR RC COMBINATIONS, Bernard A. Asner, Jr., February TN D 2626 EXPERIMENTAL STUDY OF SUBCOLLED NUCLEATE BOILING OF WATER FLOWING IN I/4-1NCH DIAMETER TUBES AT LOW PRESSURES, Frank A. Jeglic, James R. Stone, and Vernon H. Gray, January 1965 TN D 2627 FLYBACK VOLTAGE REGULATOR, Gail D. Smith, February 1965 TN D 2628 WIND-TUNNEL INVESTIGATION OF A LIFTING ROTOR OPERATING A TIP- SPEED RATIOS FROM 0.65 TO 1.45, Julian L. Jenkins, Jr., February TN D 2630 THE SYNTHESIS OF METEROID DISTRIBUTIONS FROM MONOENERGETIC MONO- DIRECTIONAL KERNELS, R. D. Shelton, H. E. Stern, J. J. Wright, and D. P. Hale, February 1965 TN D 2631 SIMULATOR STUDY OF ABILITY OF PILOTS TO ESTABLISH NEAR-CIRCULAR ORBITS USING SIMPLIFIED GUIDANCE TECHNIQUES, G. Kimball, Jr. and Herman S. Fletcher, February 1965 TN D 2633 EXPERIMENTAL INVESTIGATION OF JET IMPINGEMENT ON SURFACES OF FINE PARTICLES IN A VACUUM ENVIRONMENT, Norman S. Land and Leonard Clark, February 1965 TN D 2634 TRAINING FOR A FLOATING-POINT DISPLAY OF NUMBERS, Robert J.

Randle, Jr. and Clayton R. Coler, February 1965 TN D 2635 FIELD-ENHANCED THERMIONIC EMISSION FROM ELECTRODE OF CESIUM ION THRUSTOR, Joseph F. Wasserba, January 1965 TN D 2637 EVALUATION OF 40-MILLIMETER-BORE BALL BEARINGS OPERATING IN LIQUID OXYGEN AT DN VALUES TO 1.2 MILLION, Robert E. Cunningham and William Anderson, January 1965 TN D 2641 EXPLORATORY STUDY OF MAN'S SELF-LOCOMOTION CAPABILITIES WITH A SPACE SUIT IN LUNAR GRAVITY, Amos A. Spady, Jr. and William D.

Krasnow, July 1966 TN D 2642 THE STATIONARY LAMINAR VELOCITY BOUNDARY LAYER WITH CONSTANT FLUID PROPERTIES AND ARBITRARY DISTRIBUTIONS OF PRESSURE AND MASS TRANS- FER, Ernst W. Adams and Benton K. Berry, February 1965 TN D 2643 PARAMETRIC PERFORMANCE ANALYSIS FOR LUNAR ORBIT BRAKING AND DESCENT, Charles M. Akridge and Sam H. Harlin, February 1965 TN D 2644 PROPAGATION OF CYLINDRICAL AND SPHERICAL ELASTIC WAVES BY METHOD OF CHARACTERISTICS, Pei Chi Chou and Herbert Abraham Koenig, February 1965 ORBITING GEOPHYSICAL OBSERVATORIES, George Ludwig, March 1965 TN D 2646 MASS SPECTROMETRIC INVESTIGATION OF REACTIONS OF OXYGEN ATOMS TN D 2648 WITHHYDROGEN ANDAMMONIA, Edgar L. Wongand AndrewE. Potter, Jr., February 1965 THEORETICAL BOUNDARIES ANDINTERNAL CHARACTERISTICS EXHAUST TN D 2650 PLUMES FROM THREE DIFFERENT SUPERSONIC NOZZLES, Earl H. Andrews, Jr., Allen R. Vick, and Charlotte B. Craidon, March 1965 Applicable NACA Technical Reports TR 688 AERODYNAMIC CHARACTERISTICS OF HORIZONTAL TAIL SURFACES, Abe Silverstein and S. Katzoff, 1940 This report presents a collection of data on 17 different horizon- tal tail surfaces including two with end plates and several with balanced elevators. Data are presented in the form of curves of (a) Normal force coefficient as a function of angle of attack with elevator deflection as a parameter, (b) Elevator hinge moment coefficient as a function of elevator deflection with angle of attack as a parameter and (c) Tail drag coefficient as a function of angle of attack with elevator deflection as a param- eter.

Some correlation of the data and comparison with theory is attempted. The conclusions reached were: i. The lifting line theory predicts values of the slope of the lift curve of the normal force coefficient about 10% higher than the experimental values obtained for tail surfaces with aspect ratios of from 3.5 to 4.

2. Experimental results for the effect of end plates are in good agreement with theory.

3. Thin-airfoil theory predicts values of the elevator effective- ness and hinge moments that are somewhat larger than the experimen- tal values.

TR 689 PRELIMINARY WIND-TUNNEL INVESTIGATION OF AN NACA 23012 AIRFOIL WITH VARIOUS ARRANGEMENTS OF VENETIAN-BLIND FLAPS, Carl J.

Wenzinger and Thomas A. Harris, 1940 The results of tests indicated that the venetian-blind flap, when operated near the wing trailing edge, was superior to any pre- viously tested flap as a lift-increasing device and was also superior on the basis of low drag coefficients at high CL. The wing with this flap, however, had very large pitching-moment coefficients. The venetian-blind flaps, when operated as split flaps, produced less lift than simple split flaps of the same overall chord.

The tests also indicated that the best spacing of the slots in the venetian-blind flap was one slot-chord length and that there was no advantage in using i0 small slots in preference to 4 large slots in a flap of a given overall chord length.

TR 695 DETERMINATION OF GROUND EFFECT FROM TESTS OF A GLIDER IN TOWED FLIGHT, J. W. Wetmore and L. I. Turner, Jr., 1940 An investigation was made to determine the effect of flight near the ground (ground effect) on the aerodynamic characteristics of an aircraft. A glider (Franklin PS-2) was towed at various alti- tudes above the ground by an automobile. The lift, drag, and angle of attack of the glider were determined at each altitude.

Two aircraft wing configurations were used: The plain wing and the wing with a nearly full span 30-percent-chord split flap deflected 45 ° .

For both configurations it was found that at a fixed lift co- efficient both the drag and the angle of attack decreased in the proximity of the ground. For the plain wing at a height of 14 percent of the span (one chord length) the maximum lift was in- creased by 15% due to ground effect.

The experimental results were compared with several theoretical predictions of the ground effect.

TR 703 DESIGN CHARTS RELATING TO THE STALLING OF TAPERED WINGS, H. A.

Soule and R. F. Anderson, 1940 Design charts were prepared to show the effects of wing taper, wing thickness ratio and Reynolds number on the spanwise location of the initial stalling point. A discussion is given of the various means of moving the stalling point inboard on the wing, these include an increase of the percentage of camber of the airfoil sections from root to tip, washout, central sharp leading edges and leading edge tip slots.

An example is given of the use of the charts to determine the span- wise location of the initial slotting point on a typical wing.

Each of the methods of moving the stalling point inboard is dis- cussed to determine which method would be best suited for the given wing.

Methods are presented, also, for estimating the increase in drag associated with each method of moving the stalling point.

TR 706 WIND-TUNNEL INVESTIGATION OF SPOILER, DEFLECTOR AND SLOT LATERAL- CONTROL DEVICES ON WINGS WITH FULL-SPAN SPLIT AND SLOTTED FLAPS, Carl J. Wenzinger and Francis M. Rogallo, 1941 An investigation was made of spoiler, deflector and slot types of lateral-control devices on wings with full span split and slotted flaps. Tests were made in the NACA 7-by-10 foot wind tunnel at speeds of 40 mph which corresponds to an effective Reynolds number of approximately 2 x 106 . Two models were tested; one a Clark Y airfoil with a 20% chord split flap and one a NACA 23012 airfoil section with a full span 25.66% chord slotted flap. To these wing sections were added various spoilers, deflectors and retractable ailerons both individually and in combination.

The data are presented in graphical form with Rolling moment and Yawing moment coefficients plotted as a function of the control device projection above or below the wing. In some cases hinge moments for the devices are also plotted.

Measurements were also made of the lag (time) between deflection of the control surface and the time when the force due to the control surface reached 1/2 its total value.

It was found that: i. Spoilers alone were generally unsuitable for lateral control on wings with full span split or slotted flaps due to excessive lag and ineffectiveness at small deflection.

2. Deflectors alone were not as effective as spoilers at large deflections but were generally more effective at small deflec- tions and had less lag then spoilers alone.

3. A slot-closing deflector for use with wings with slotted flaps was effective in decreasing wing drag when the slotted flap was in neutral and augmented lateral control when the flap was deflected.

4. The addition of a slot to a combination of a spoiler and a deflector offered improvement of the static moment and the lag characteristics.

TR 708 TESTS OF THE NACA 0025 AND 0035 AIRFOILS IN THE FULL SCALE WIND TUNNEL, W. Kenneth Bulllvant, 1941 Tests were conducted in the NACA full-scale wind tunnel to deter- mine the aerodynamic characteristics of 6-by-36 foot rectangular NACA 0025 and 0035 rectangular planform airfoils. Measurements were made of the lift, drag and pitching moments of these wings with no flaps and also with a 20% chord split flap. In addition to force measurements the profile drag was obtained by the momentum method, and the boundary layer transition point was determined from measurements of the local velocity profiles.

Data are presented in the form of drag coefficient, moment coeffi- cient and angle of attack curves as functions of lift coefficient.

The average velocity for the tests was 57 mph, corresponding to a Reynolds number of 3.2 x 106 . The angle of attack range extended from -8 ° through the angle of attack for maximum llft. Flap de- flections of 15 ° , 30 °, 45 ° , 60 ° , 75 ° and 90 ° were tested.

The data were comparedwith similar data obtained previously for thinner airfoils.

Within the range of Reynolds number covered (2 x 106 to 6 x 106) the section profile drag coefficients for the two wings were prac- tically independent of Reynolds number. For the 0025 airfoil CDo= 0.0082, for the 0035 airfoil CDo= 0.0112. For a Reynolds number of 3 x 106 and with 20%c-full span flaps, the maximumlift coefficient for the 0025 airfoil was 2.57 and for the 0035 air- foil was 2.54 TR 718 PRESSURE DISTRIBUTION OVER AN NACA23021 AIRFOILWITHA SLOTTED ANDA SPLIT FLAP, ThomasA. Harris and John G. Lowry, 1941 An investigation was madeof the pressure distribution on an NACA23021 airfoil fitted with a slotted flap or with a split flap. Tests were conducted at an average dynamic pressure of 11.05 psf corresponding to an air speed of @pproximately 65 mph and to a Reynolds number of about 1.84 x i00. The effective Reynolds number was approximately 3.56 x 106. Reynolds numbers were based on chord.

The data were obtained to furnish data for aerodynamic and structural design of high lift devices on relatively thick wings.

The data are presented in the form of pressure distributions over the airfoil for the flap undeflected configuration and for several configurations in which the flap was deflected. In addition, the pressure distributions were integrated to obtain airload informa- tion which is also presented.

The results for this airfoil were comparedwith results, pre- viously obtained, for an NACA23012 airfoil with similar flap arrangements. This comparison showed: i. The flap pitching momentcoefficients were approximately the samefor the range tested.

2. The flap normal force coefficients were approximately the sameat high angles of attack.

3. The flap chord force coefficients on the 23021 airfoil were slightly higher than for the flap on the 23012 airfoil.

TR 722 A GRAPHICAL METHOD OF DETERMINING PRESSURE DISTRIBUTION IN TWO DIMENSIONAL FLOW, Robert T. Jones and Doris Cohen, 1941 A procedure is developed for effecting localized modifications of airfoil shapes and for determining graphically the resulting changes in the pressure distribution over the body. The method is a generalization of the Jonkowski method. It is also shown how the method can be used to determine the pressure distribution over airfoils of original design.

Formulas for the lift, moment, and the aerodynamic center of the airfoil are presented in a appendix.

TR 723 WIND-TUNNEL INVESTIGATION OFNACA23012, 23021, AND23030 AIRFOILS EQUIPPED WITH40-PERCENT-CHORD DOUBLE SLOTTED FLAPS,ThomasA.

Harris and Isidore G. Recant, 1941 A study was madeto determine the aerodynamic characteristics of three NACAairfoils fitted with 40-percent-chord double slotted flaps. The tests were conducted in the NACA7-by-10 foot tunnel at a dynamic pressure of 16.37 psf corresponding to a velocity of about 80 mph and to an average Reynolds number (based on chord) of about 2.19 x 106 or an effective Reynolds number of approximate- ly 3.5 x 106. The three airfoil sections were the NACA23012 (12%thick), the 23021 (21%thick), and the 23030 (30%thick).

Data are presented in the form of lift, drag and pitching moment curves with the primary flap deflection and the secondary flap deflection as parameters.

The maximum section lift coefficient of an airfoil with 40%chord double slotted flap was found to increase slowly with increasing thickness, reaching a value of 3.7 for the 30%thick airfoil.

For a given airfoil thickness the 40%chord double slotted flap gives a higher value of section maximum lift coefficient than either the 40%chord or the 25.66% chord single slotted flap.

The high lift coefficients for the double slotted flaps were accompaniedby large pitching momentcoefficients.

TR 730 AN INVESTIGATION OFTHEDRAG OFWINDSHIELDS IN THE8-FOOT HIGH- SPEED WINDTUNNEL, Russell G. Robinson and JamesB. Delano, 1942 The drag of closed-cockpit and transport-type windshields was determined from tests madeat speeds corresponding to a Mach number range of approximately 0.25 to 0.58. This corresponds to a Reynolds number range of 2.51 x 106 to 4.83 x 106 based on the meanaerodynamic chord of the full-span model.

For closed cockpit windshields: The windshield drag for airplanes of small to mediumsize may account for 15%of the airplane drag or may be reduced to 1%.

Sharp junctures at the front of windshiels are to be avoided.

A radius of at least 25%of the windshield height should be used if the drag is to be kept low at mediumspeeds. A larger radius should be used for a high speed plane. The optimum length for a conical windshield nose was twice the windshield height and, for a streamline nose, was more than three times its height.

Tail fairings whether conical or streamline, should be about four times as long as their height.

Steps for telescoping hoods increased the drag of a good wind- shield from 25 to 50%; retaining strips added drag measureably.

Poor windshields becamerelatively poorer as speed was increased because of compressibility and low_r critical speeds. The best windshields at low speed had the least compressibility effect over a wide speed range and had the highest critical speeds.

For transport-type windshields : The windshield drag may account for 21%of the fuselage drag or may be reduced to 2%without completely fairing the windshield area.

Recessedwindshield windows added ?% more to the fuselage drag than did flush windows.

Sharp edges between windshield panels and cabin roof or sides added 2 to 14% to the fuselage drag.

TR 750 HIGH-SPEED TESTS OF A MODEL TWIN-ENGINE LOW-WING TRANSPORT AIRPLANE, John V. Becker and Lloyd H. Leonard, 1942 Force tests were made of a i/8-scale model of twin-engine low-wing transport airplane to investigate compressibility and interference effects at speeds up to 450 mph. In addition to tests of the standard arrangement of the model, tests were made with several modifications designed to reduce the drag.

The results show serious increases in drag at critical Mach num- bers ranging from about 0.47 to 0.60 due to the occurrence of compressibility burbles on the standard radial-engine cowlings, on sections of the wing as a result of wing-nacelle interference, and on the semiretracted main landing wheels. The critical speed at which the shock occurred on the standard cowlings was 20 mph lower in the presence of only the wing. The drag of the complete model was reduced 25% at 300 mph by completely retracting the landing gear, fairing the windshield irregularities, and substi- tuting streamline nacelles (with allowance made for proper amount of cooling air flow) for the standard nacelle arrangement. The values of the critical Mach number were considerably increased as a result of the afore-mentioned improvements.

TR 800 EFFECT OF SMALL ANGLES OF SWEEP ANDMODERATE AMOUNTS OFDIHEDRAL ONSTALLING ANDLATERAL CHARACTERISTICS OFA WING-FUSELAGE COM- BINATION EQUIPPED WITHPARTIAL-ANDFULL-SPAN DOUBLE SLOTTED FLAPS,JeromeTeplitz, 1944 Tests of a wlng-fuselage combination incorporating NACA 65-series airfoil sections were conducted. The investigation included tests with flaps neutral and with partial- and full-span double slotted flaps deflected to determine the effects of (i) variations of wing sweepbetween -4 ° and 8 ° on stalling and lateral stability and control characteristics and (2) variations of dihedral between 0 ° and 6.75 ° on lateral stability characteristics.

Deflection of the flaps noticeably reduced dihedral effect.

Sweepback increased considerably the effective dihedral and de- creased the adverse effect of flap deflection on dihedral effect; sweepforward reduced the effective dihedral and increased the adverse effect of flap deflection. More favorable variations of effective dihedral with C L were obtained with sweepback.

Stalling characteristics were less satisfactory with sweepback than with normal sweep or sweepforward in that the point of initial stall moved outboard, but increased maximum lift coeffi- cients were noted for every flap condition. Aileron effectiveness was reduced about 10% with sweepback and flaps neutral but varied little with speed with flaps deflected.

Agreement with theory was noted for the effect of changes in dihedral angle on lateral stability characteristics. The test results showed that the change in slope of the curve of rolling- moment coefficient against angle of yaw was approximately 0.00026 per degree change in geometric dihedral angle.

WIND-TUNNEL INVESTIGATION OF THE EFFECTS OF PROFILE MODIFICATION TR 803 AND TABS ON THE CHARACTERISTICS OF AILERONS ON A LOW-DRAG AIRFOIL, Robert M. Crane and Ralph W. Holtzclaw, 1944 An investigation was made to determine the effect of control- surface profile modifications on the aerodynamic characteristics of an NACA low-drag airfoil equipped with a 0.20c and a 0.15c aileron. Tab characteristics were obtained for a 0.20-aileron chord tabs on two of the 0.20c ailerons (NACA 661 2-216).

Thickening the aileron profile or thickening and beveling the trailing edge of the aileron was found to reduce the aileron effectiveness, reduce the slope of the wing-section lift curve, and reduce the hinge-moment coefficients. Thinning the profile had the opposite effect. The effects of profile thickness on the aileron characteristics decreased with increasing angle of attack, there being practically no effect at an angle of attack of 12 ° .

For the thickened and beveled trailing edges, the effects were maximum for the bevel, the length of which was 0.20 aileron chord, and decreased for both increasing and decreasing bevel lengths.

Thickening the profile or thickening and beveling the trailing edge caused a slight increase in minimumprofile-drag coefficient, but thinning the profile had no effect.

It was shownthat deviations of the order of + O.005-aileron chord from the specified profile on the ailerons of a typical pursuit airplane can cause stick-force variations of + 20 pounds for a large roll rate at an indicated airspeed of 300 mph. It was also shown that the danger of overbalance at small deflections of close- ly balanced ailerons can be dimished by thickening of the aileron profile if the internal-balance chord is simultaneously reduced to maintain the samestick force for a large rate of roll.

Thickening and beveling the trailing edge on a typical aileron installation caused a reduction of 50%in the control force for a rate of roll at high speed. Whenused in conjunction with internal balance, the thickened and beveled profile resulted in a 30%re- duction in the nose balance required for a given control force at high speed. Under these conditions, the variation of control force with rate of roll was more nearly linear for the aileron of normal profile than for the ailerons with thickened and beveled trailing edges.

TR 824 SUMMARY OF AIRFOIL DATA, Ira H. Abbott, Albert E. von Doenhoff, and Louis S. Stivers, Jr., 1945 Recent airfoil data for both flight and wind-tunnel tests was collected insofar as possible. The flight data consisted largely of drag measurementsmadeby the wake-survey method. Most of the data on airfoil section characteristics were obtained in the Langley two-dimensional low-turbulence pressure tunnel. Detail data necessary for the application of NACA 6-series airfoils to wing design were presented in supplementary figures, together with recent data for the NACA 00-, 14-, 24-, 44-, and 230-series air- foils. The general methods used to derive the basic thickness forms for NACA6- and 7-series airfoils and their corresponding pressure distributions were presented. Data and methodswere given for rapidly obtaining the approximate pressure distributions for NACA four-digit, five-digit, 6-, and 7-series airfoils. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Data on high- lift devices were presented. Problems associated with lateral- control devices, leading-edge air intakes, and interference were briefly discussed.

The followin$ conclusions may be drawn from the data presented: i. Airfoil sections permitting extensive laminar flow, such as the NACA6- and 7-series sections, result in substantial reductions in drag at high-speed and cruising lift coefficients as comparedwith other sections if, and only if, the wing surfaces are fair and smooth.

2. Experience with full-size wings has shown that extensive laminar flows sre obtainable if the surface finish is as smooth as that provided by sanding in the chordwise direction with No.

320 carborundumpaper and if the surface is free from small scattered defects and specks. Satisfactory results are usually obtained if the surface is sufficiently fair to permit a straight- edge to be rocked smoothly in the chordwise direction without jarring or clicking.

3. For wings of moderate thickness ratios with surface conditions corresponding to those obtained with current constructions methods, minimumdrag coefficients on the order of 0.0080 may be expected.

The values of the minimumdrag coefficient for such wings depend primarily on the surface condition rather than on the airfoil section.

4. Substantial reductions in drag coefficient at high Reynolds numbersmay be obtained by smoothing the wing surfaces, even if extensive laminar flow is not obtained.

5. The maximum lift coefficients for moderately camberedsmooth NACA 6-series airfoils with the uniform-load type of meanline are as high as those for NACA24- and 44-series airfoils. The NACA 230-series airfoils have somewhat higher maximum lift coefficients for thickness ratios less than 0.20.

6. The maximum lift coefficients of airfoils with flaps are about the samefor moderately thick NACA 6-series sections as for the NACA23012 section but appear to be considerably lower for thinner NACA6-series sections.

7. The lift-curve slopes for smooth NACA 6-series airfoils are slightly higher than for NACA 24-, 44-, and 230-series airfoils and usually exceed the theoretical value for thin airfoils.

8. Leading-edge roughness causes large reductions in maximum lift coefficient for both plain airfoils and airfoils equipped with split flaps deflected 60 ° . The decrement in maximum lift coeffi- cient resulting from standard roughness is essentially the same for the plain airfoils as for the airfoils equipped with the 60 ° split flaps.

9. The effect of leading-edge roughness is to decrease the lift- curve, slope, particularly for the thicker sections having the position of minimum pressure far back.

i0. Characteristics of airfoil sections with the expected surface conditions must be known or estimated to provide a satisfactory basis for the prediction of the characteristics of practical- construction wings and the selection of airfoils for such wings.

ii. The NACA 6-series airfoils provide higher critical Mach numbers for high-speed and cruising lift coefficients than earlier types of sections and have a reasonable range of lift coefficients within which high critical Machnumbersmay be obtained.

12. The NACA 6-series sections provide lower predicted critical Machnumbers at moderately high lift coefficients than the earlier types of sections. The limited data available suggest, however, that the NACA 6-series sections retain satisfactory lift charac- teristics up to higher Machnumbers than the earlier sections.

13. The NACA 6-series airfoils do not appear to present unusual problems with regard to the application of ailerons.

14. Problems associated with the avoidance of boundary-layer separation caused by interference are expected to be similar for conservative NACA6-series sections and other good airfoils.

Detail shapes for optimuminterferring bodies and fillets may be different for various sections if local excessive expansions in the flow are to be avoided. I 15. Satisfactory leading-edge air intakes may be provided for NACA6-series sections, but insufficient information exists to allow intakes to be designed without experimental development.

200 pages of graphs are given for almost any general airfoil.

This would be an excellent report for a design manual because it characterizes certain airfoils.

TR 833 GENERAL THEORY OFAIRFOIL SECTIONS HAVING ARBITRARY SHAPE OR PRESSURE DISTRIBUTION, H. Julian Allen, 1945 In this report a theory of thin airfoils of small camber is developed which permits either the velocity distribution corresponding to a given airfoil shape, or the airfoil shape corresponding to a given velocity distribution to be calculated.

The procedures to be employed in these calculations are outlined and illustrated with suitable examples.

TR 903 THEORETICAL ANDEXPERIMENTAL DATAFORA NUMBER OFNACA6A-SERIES AIRFOIL SECTIONS, Laurence K. Loftin, Jr., 1948 The NACA6A-series airfoil sections were designed to eliminate the trailing edge cusp which is characteristic of the NACA6- series sections. Theoretical data were presented for NACA6A- series basic thickness forms having the position of minimumpres- sure at 30, 40, and 50%chord and with thickness ratios varying from 6%to 15%. The experimental results of a two-dlmensional wind tunnel investigation of the aerodynamic characteristics of five NACA 64A-series airfoil sections and two NACA 63A-series airfoil sections were presented. An analysis of these results, which were obtained at Re = 3 x i06, 6 x 106 , and 9 x 106 , indicat- ed that the section mlnlmum-drag and maximum-llft characteristics of comparable NACA 6-serles and 6A-serles airfoils are essentially the same. The quarter-chord pltching-moment coefficients and angles of zero llft of NACA 6A-series airfoil sections are slight- ly more negative than those of corresponding NACA 6-series airfoil sections. The position of the aerodynamic center and the lift- curve slope of smooth NACA 6A-serles airfoil sections appear to be essentially independent of airfoil thickness ratio in contrast to the trends shown by NACA 6-serles sections. The addition of standard leadlng-edge roughness causes the lift-curve slope of the newer sections to decrease with increasing airfoil thickness ratio.

TR 942 INVESTIGATION IN THE LANGLEY 19-FOOT PRESSURE TUNNEL OF TWO WINGS OF NACA 65-210 AND 64-210 AIRFOIL SECTIONS WITH VARIOUS TYPE FLAPS, James C. Sivells and Stanley H. Spooner, 1949 From the results of tests in the Langley 19-foot pressure tunnel of a wing with NACA 65-210 airfoil sections and a wing with NACA 64-210 airfoil sections with several types of flaps, it was found that: At a Reynolds number = 4.4 x 106 , maximum lift coefficients of 2.48 and 2.76, respectively were obtained with the NACA 65-210 and 64-210 wings with full span double slotted flaps. These values were approximately 205% of the flap neutral values of 1.21 and 1.35 for the respective wings.

Addition of the fuselage or the leading-edge roughness caused reductions of 0.i to 0.3 in the Clmax'S of the wings. The NACA 64-210 wing was affected to a greater extent than was the NACA 65-210 wing, although the CLmax'S for the NACA 64-210 wing were still higher.

Increases in the CLmax with increases in Reynolds number were obtained at Reynolds numbers < 4.4 x 106 . Above this value, the test Mach number was high enough to be above the limits of this review project and into compressibility.

The stall of the NACA 64-210 wing was somewhat more abrupt but slightly farther inboard than that of the NACA 65-210 wing. The pattern of stall was not appreciably altered by the leading-edge roughness or by the various flap configurations. The fuselage, however, caused the stall to begin inboard near the wlng-fuselage function.

TR 950 INVESTIGATION OF A SYSTEMATIC GROUP OFNACAI-SERIES COWLINGS WITH ANDWITHOUT SPINNERS, Mark R. Nichols and Arvid L. Kelth, Jr., 1949 An investigation has been conducted to study cowling-spinner combinations based on the NACA1-series nose inlets and to obtain systematic design data for one family of approximately ellipsoidal spinners.

For each spinner there is a single minimuminlet-velocity ratio below which boundary-layer separation from the spinner occurs at or ahead of the inlet. In the case of the NACA1-series spinners, this inlet-velocity ratio is often higher than necessary to obtain an essentially uniform pressure distribution on the cowling and, thus, determines the high-speed design conditions.

Short conical spinners are superior to comparable NACA1-series spinners with regard to the minimuminlet-velocity ratio for which flow separation is avoided.

Separation bubbles occur on the inner-lip surface of the NACAl- series cowlings at high inlet-velocity ratios and, in the case of the open nose cowlings, initiate importantseparation of the in- ternal flow. In the case of the cowling-spinner combinations, propeller operation causes a strong outwardly increasing total- pressure gradient in the inlet which delays and tends to eliminate much separation. A revised inner-lip shape of the type investi- gated can be used to delay the formation of such separation bub- bles to considerably higher Inlet-velocity ratios.

Within the usual range of proportions, the addition of NACAl- series spinners to NACA1-series cowlings does not change appre- ciably the design critical Machnumbers for the cowlings, but frequently causes large changes in the inlet-velocity ratios re- quired to obtain essentially uniform pressure distributions on the cowlings. Wherethe design conditions are not determined by the flow-separation characteristics of the spinner, the design inlet-velocity ratio increases rapidly with increases in the slope of the spinner surface just ahead of the inlet; important increases maybe obtained when short conical spinners are substi- tuted for conventional spinners of the sameoverall proportions.

With a propeller having approximately oval shanks, propeller operation retards flow separation from the spinner and inner cowling-lip surface and, within the usual range of high-speed operating conditions, does not reduce the design critical Mach number.

Increases in flight Machnumber reduce the effective _ of the cowling lip for given values of inlet-velocity ratios less than unity and, thus, reduce the minimumvalue of inlet-velocity ratio for which a near-uniform surface pressure distribution on the cowling is obtained and tend to make the inner cowling-lip surface more susceptible to flow separation.

Inasmuchas the present tests were conducted at low airspeeds, the investlgatlon necessarily included a study of the procedure required to determine the design operating conditions at the design flight Machnumber from the low speed test results. In this study, existing relations for open-nose cowlings were generalized to the case of the cowling-spinner combination and extended to the case of compressible flow. The derived relations were then used to calculate the effect of Machnumber on the design inlet-velocity ratio and to establish a simple correction procedure.

The design conditions for the NACA1-series cowlings and cowling- spinner combinations were presented in the form of charts from which, for wide ranges of spinner proportions and rates of internal flow, cowlings with near-maximumpressure recovery can be selected for critical Machnumbers ranging from 0.70 to about 0.85. In addition, the characteristics of the spinners and the effects of the spinners and the propeller on the cowling design conditions were presented separately to provide initial quantitative data for use in a general design procedure through which NACA 1-series cowlings can be selected for use with spinners of other shapes.

By use of this general design procedure, correlation curves established from the test data, and the equations used, NACA l- series cowlings and cowling-spinner combinations can be designed for critical Machnumbers as high as 0.90.

TR 1176 DETERMINATION OFMEAN CAMBER SURFACES FORWINGS HAVING UNIFORM CHORDWISE LOADING ANDARBITRARY SPANWISE LOADING IN SUBSONIC FLOW, S. Katzoff, M. Frances Faison and Hugh C. DuBose, 1954 The field of a uniformly loaded wing in subsonic flow is discussed in terms of the acceleration potential. It is shown that, for the design of such wings, the slope of the meancambersurface at any point can be determined by a line integration around the wing boundary. By an additional line integration around the wing boundary, this methods is extended to include the case where the local section lift coefficient varies with spanwise location.

For the uniformly loaded wing of polygonal plan form, the integra- tions necessary to determine the local slope of the surface and the further integrations of the slopes to determine the ordinate can be done analytically. An outline of these integrations and the resulting formulas are included.

Calculated results are given for sweptback wing with uniform chordwise loading and a highly tapered spanwise loading, a uni- formly loaded delta wing, a uniformly loaded sweptback wing, and the samesweptback wing with uniform chordwise loading but ellip- tical span load distribution.

WIND-TUNNEL ANDFLIGHTINVESTIGATIONS OF THEUSEOFLEADING-EDGE TR 1276 AREASUCTION FORTHEPURPOSE OF INCREASING THEMAXIMUM LIFT CO- EFFICIENT OF A 35 ° SWEPT-WING AIRPLANE, Curt A. Holzhauser and Richard S. Bray, 1956 An investigation was undertaken to determine the increase in maxi- mum lift coefficient that could be obtained by applying area suc- tion near the leading edge of a wing. This investigation was first performed with a 35 ° swept-wing model in the wind tunnel, and then with an operational 35 ° swept-wing airplane (F-86F) which was modified in accordance with wind tunnel results.

Results i. The maximum lift coefficient was increased more than 50% by the use of area suction.

Configuration CLmax Stalling Characteristics 1.82 Controllable, no stall (i) Porous leading edge suction on warning 1.58 Not controllable, no (2) Cambered leading edge stall warning 1.36 Controllable, adequate (3) Normal leading edge slats extended stall warning 1.27 Controllable, adequate (4) Normal leading edge slats stall warning closed 1.08 Controllable, adequate (5) Porous leading edge suction stall warning off BLOWING-TYPE BOUNDARY-LAYER CONTROL AS APPLIED TO THE TRAILING- TR 1369 EDGE FLAPS OF A 35 ° SWEPT-WING AIRPLANE, Mark W. Kelly, Seth B.

Anderson and Robert C. Innis, 1958 Flight investigations were made on an F-86D aircraft with boundary layer control on the trailing-edge flaps: I. Correlation of flap lift with jet momentum coefficient was good for the range of pressure ratios obtainable from turbojet engine bleed air systems.

2. The lift increment obtained by preventing flow separation on the flap can be predicted up to 60 ° flap deflection by the linear inviscid fluid theory of NACA Report 1071.

3. Higher lift increments than those obtained by preventing flow separation on the flaps can be achieved by further increasing the momentum coefficient to values above that required to prevent flow separation. However, once the flow is attached to the flap, large values of momentum coefficient are required to increase the lift significantly.

4. Lateral stability was increased slightly by blowing over the flaps, and the maximum roll power of the ailerons was increased by about 25%.

5. When the blowing nozzle was located in the upper surface of the flap, it was found that the chordwise position of the nozzle could be anywhere between the minimum pressure point on the flap and the wing-flap juncture without seriously affecting the flap lift. If the nozzle is located too far downstream of the minimum pressure point, large losses in flap lift may result.

6. When the blowing nozzle was located in the wing shroud ahead of the flap, it was necessary to position the flap close to the nozzle to obtain the same coefficients of lift at low momentum coefficients as those for the plain-blowing-flap configuration.

7. The blowing flap lift is relatively insensitive to spacers or structural members in the nozzle throat. It is also insensi- tive to flow disturbances such as those caused by leading-edge slots.

8. Blowing with the flaps deflected 55 ° reduced the average approach speed by as much as 12 knots in a carrier-type approach compared to the slotted flap deflected 38 ° . In sinking type approaches smaller reductions in speed were realized.

9. Blowing with flaps deflected 66 ° reduced the calculated land- ing distance by 30% compared to the standard 38 ° slotted flap. In take-off performance calculations, the catapult end speed required at a given gross weight was reduced by 8 knots due to blowing.

For a field-type take-off, the gains calculated were relatively small.

I0. Improvements were noted by the pilots in control of the glide path with blowing on. Improvements were noted also in take-off since the airplane would tend to fly off without as much rotation in attitude required.

ii. The longitudinal term changes due to flap deflection and application of blowing were considered excessive by the pilots.

12. In some cases, the stalling characteristics were made less desirable with blowing on.

AREA-SUCTION BOUNDARY-LAYER CONTROL AS APPLIED TO THETRAILING- TR 1370 EDGE FLAPSOF A 35° SWEPT-WING AIRPLANE, Woodrow L. Cook, Seth B.

Anderson and GeorgeE. Cooper, 1958 The results of wind-tunnel and flight tests of a 35 ° swept-wing airplane (F-86) having area suction (through a porous metal at the leading edge of the flap) applied to the trailing edge flaps indicated that trailing edge flap effectiveness could be improved to values approaching theory for flap deflections ranging from 45 ° to 64 ° of deflection. The primary effects of boundary layer control applied to trailing edge flaps was to increase lift at a given angle of attack. Although the flap boundary layer control reduced the stall speed only slightly, a reduction in minimum comfortable approach speed of about 12 knots was obtained by a number of pilots, particularly those giving visibility and alti- tude or longitudinal control as the limiting-factor. The improve- ments in flap effectiveness were accomplished with low values of flow quantity and suction horsepower; flow coefficients ranging from 0.0003 to 0.0008 were required; and suction power ranging from i0 to 25 horsepower would be required in the normal landing- approach and take-off speed ranges.

Not Applicable NACA Technical Reports TR 681 THE UNSTEADY LIFT OF A WING OF FINITE ASPECT RATIO, Robert T.

Jones, 1940 TR 694 THE APPLICATION OF BASIC DATA ON PLANINGSSURFACES TO THE DESIGN OF FLYING-BOAT HULLS, Walter S. Diehl, 1940 TR 702 THE CALCULATED EFFECT OF VARIOUS HYDRODYNAMIC AND AERODYNAMIC FACTORS ON THE TAKE-OFF OF A LARGE FLYING BOAT, R. E. Olson and J. M. Allison, 1940 TR 716 A SIMPLIFIED THEORETICAL METHOD OF DETERMINING THE CHARACTERIS- TICS OF A LIFTING ROTOR IN FORWARD FLIGHT, F. J. Bailey, 1941 TR 728 ON THE USE OF RESIDUE THEORY FOR TREATING THE SUBSONIC FLOW OF A COMPRESSIBLE FLUID, Carl Kaplan, 1942 TR NONSTATIONARY FLOW ABOUT A WING-AILERON-TAB COMBINATION INCLUDING AERODYNAMIC BALANCE, Theodore Theodorsen and I. E. Garrick, 1942 TR GROUND EFFECT ON DOWNWASH ANGLES AND WAKE LOCATION, S. Katzoff and Harold H. Sweberg, 1942 TR 742 WIND-TUNNEL INVESTIGATION OF AN NACA 23012 AIRFOIL WITH 30-PERCENT- CHORD VENETIAN-BLIND FLAPS, F. M. Rogallo and Bartholomew S. Spano, TR THE MEAN AERODYNAMIC CHORD AND THE AERODYNAMIC CENTER OF A TAPERED WING, Walter S. Diehl, 1942 TR ON A NEW METHOD FOR CALCULATING THE POTENTIAL FLOW PAST A BODY OF REVOLUTION, Carl Ka_lan, 1943 TR TESTS OF AIRFOILS DESIGNED TO DELAY THE COMPRESSIBILITY BURBLE, John Stack, 1943 TR 764 A METHOD FOR CALCULATING HEAT TRANSFER IN THE LAMINAR FLOW REGION OF BODIES, H. Julian Allen and Bonnie C. Look, 1943 TR AERODYNAMIC AND HYDRODYNAMIC TESTS OF A FAMILY OF MODELS OF FLYING- BOAT HULLS DERIVED FROM A STREAMLINE BODY-- NACA MODEL 84 SERIES, John B. Parkinson, Roland E. Olson, Eugene C. Draley and Arvo A.

Luoma, 1943 TR 768 THE FLOW OF A COMPRESSIBLE FLUID PAST A CURVED SURFACE, Carl Kaplan, 1943 TR 770 JET-BOUNDARY CORRECTIONS FOR REFLECTION-PLANE MODELS IN RECTANGULAR WIND TUNNELS, Robert S. Swanson and Thomas A. Toll, 1943 TR 772 DETERMINATION OF GENERAL RELATIONS FOR THE BEHAVIOR OF TURBULENT BOUNDARY LAYERS, Albert E. von Doenhoff and Neal Tetervin, 1943 TR 78O COMPRESSIBLE POTENTIAL FLOW WITH CIRCULATION ABOUT A CIRCULAR CYLINDER, Max A..Heaslet, 1944 TR 782 WALL INTERFERENCE IN A TWO-DIMENSIONAL-FLOW WIND TUNNEL, WITH CONSIDERATION OF THE EFFECT OF COMPRESSIBILITY, H. Julian Allen and Walter G. Vincenti, 1944 TR 788 ON THE PLANE POTENTIAL FLOW PAST A LATTICE OF ARBITRARY AIRFOILS, I. E. Garrick, 1944 TR 789 ON THE FLOW OF A COMPRESSIBLE FLUID BY THE HODOGRAPH METHOD. I- UNIFICATION AND EXTENSION OF PRESENT-DAY RESULTS, I. E. Garrick and Carl Kaplan, 1944 TR 790 ON THE FLOW OF A COMPRESSIBLE FLUID BY THE HODOGRAPH METHOD. II- FUNDAMENTAL SET OF PARTICULAR FLOW SOLUTIONS OF THE CHAPLYGIN DIFFERENTIAL EQUATION, I. E. Garrick and Carl Kaplan, 1944 TR 793 EXPERIMENTS ON DRAG OF REVOLVING DISKS, CYLINDERS, AND STREAMLINE RODS AT HIGH SPEEDS, Theodore Theodorsen and Arthur Regier, 1944 TR 794 THE FLOW OF A COMPRESSIBLE FLUID PAST A CIRCULAR ARC PROFILE, Carl Kaplan, 1944 TR A METHOD FOR THE CALCULATION OF EXTERNAL LIFT, MOMENT, AND PRESSURE DRAG OF SLENDER OPEN-NOSE BODIES OF REVOLUTION AT SUPERSONIC SPEEDS, Clinton E. Brown and Hermon M. Parker, 1945 TR 829 SUMMARY OF MEASUREMENTS IN LANGLEY FULL-SCALE TUNNEL OF MAXIMUM LIFT COEFFICIENTS AND STALLING CHARACTERISTICS OF AIRPLANES, Harold H. Sweberg and Richard C. Dingeldein, 1945 TR 830 A METHOD FOR DETERMINING THE RATE OF HEAT TRANSFER FROM A WING OR STREAMLINE BODY, Charles W. Frick, Jr. and George B. McCullough, TR 832 A SYSTEMATIC INVESTIGATION OF PRESSURE DISTRIBUTIONS AT HIGH SPEEDS OVER FIVE REPRESENTATIVE NACA LOW-DRAG AND CONVENTIONAL AIRFOIL SECTIONS, Donald J. Graham, Gerald E. Nitzberg, and Robert N.

Olson, 1945 TR 834 EFFECT OF COMPRESSIBILITY AT HIGH SUBSONIC VELOCITIES ON THE LIFTING FORCE ACTING ON AN ELLIPTIC CYLINDER, Carl Kaplan, 1946 TR 835 PROPERTIES OF LOW-ASPECT-RATIO POINTED WINGS AT SPEEDS BELOW AND ABOVE THESPEED OF SOUND, Robert T. Jones, 1946 TR 839 THEORETICAL LIFT ANDDRAG OF THINTRIANGULAR WINGS AT SUPERSONIC SPEEDS, Clinton E. Brown, 1946 TR 840 STALLING OF HELICOPTER BLADES, F. B. Gustafson and G. C. Myers, Jr., TR 841 APPLICATION OF THEMETHOD OF CHARACTERISTICS TO SUPERSONIC ROTATION- AL FLOW,Antonio Ferri, 1946 TR 842 SOME EFFECTS OF COMPRESSIBILITY ONTHEFLOW THROUGH FANS ANDTUR- BINES, W. Perl and H. T. Epstein, 1946 TR 843 JET-BOUNDARY ANDPLAN-FORM CORRECTIONS FORPARTIAL-SPAN MODELS WITHREFLECTION PLANE,ENDPLATE,ORNOENDPLATEIN A CLOSED CIRCULAR WINDTUNNEL, JamesC. Sivells and OwenJ. Deters, 1946 TR 844 TANKTESTS TO DETERMINE THEEFFECT ONPLANING-TAIL HULLS OF VARYING LENGTH, WIDTH,ANDPLAN-FORM TAPER OF AFTERBODY, John R. Dawson, Robert C. Walter and Elizabeth S. Hay, 1946 TR 849 THEEFFECT OF WALL INTERFERENCE UPON THE AERODYNAMIC CHARACTER- ISTICS OF AN AIRFOIL SPANNING A CLOSED-THROAT CIRCULAR WIND TUNNEL, Walter G. Vincenti and Donald J. Graham, 1946 TR 851 THIN OBLIQUE AIRFOILS AT SUPERSONIC SPEED, Robert T. Jones, 1946 TR 854 COMPRESSIBILITY EFFECTS ON THE LONGITUDINAL STABILITY AND CONTROL OF A PURSUIT-TYPE AIRPLANE AS MEASURED IN FLIGHT, William N.

Turner, Paul J. Steffen and Lawrence A. Clousing, 1946 TR WIND PLAN FORMS FOR HIGH-SPEED FLIGHT, Robert T. Jones, 1947 TR 865 METHOD FOR CALCULATING WING CHARACTERISTICS BY LIFTING-LINE THEORY USING NONLINEAR SECTION LIFT DATA, James C. Sivells and Robert H.

Neely, 1947 TR 869 ISOLATED AND CASCADE AIRFOILS WITH PRESCRIBED VELOCITY DISTRIBUTION, Arthur W. Goldstein and Meyer Jerison, 1947 TR 870 TANK INVESTIGATION OF A POWERED DYNAMIC MODEL OF A LARGE LONG-RANGE FLYING BOAT, John B. Parkinson, Roland E. Olson and Marvin I. Haar, TR 872 THEORETICAL STUDY OF AIRFORCES ON AN OSCILLATING OR STEADY THIN WING IN A SUPERSONIC MAIN STREAM, I. E. Garrick and S. I. Rubinow, APPLICATION OF THE ANALOGY BETWEEN WATER FLOW WITH A FREE SURFACE TR 875 AND TWO-DIMENSIONAL COMPRESSIBLE GAS FLOW, W. James Orlin, Norman J. Lindner, and Jack G. Bitterly, 1947 THE STABILITY OF THE LAMINAR BOUNDARY LAYER IN A COMPRESSIBLE FLUID, TR 876 Lester Lees, 1947 SUMMARY REPORT ON THE HIGH-SPEED CHARACTERISTICS OF SIX MODEL TR 877 WINGS HAVING NACA 651-SERIES SECTIONS, William T. Hamilton and Warren H. Nelson, 1947 INTERFERENCE METHOD FOR OBTAINING THE POTENTIAL FLOW PAST AN TR 879 ARBITRARY CASCADE OF AIRFOILS, S. Katzoff, Robert S. Finn and James C. Laurence, 1947 884 EFFECTS OF SWEEP-BACK ON BOUNDARY LAYER AND SEPARATION, Robert TR T. Jones, 1947 A THEORY OF UNSTAGGERED AIRFOIL CASCADES IN COMPRESSIBLE FLOW, TR 888 Robert A. Spurr and H. Julian Allen, 1947 VOLTERRA'S SOLUTION OF THE WAVE EQUATION AS APPLIED TO THREE- TR 889 DIMENSIONAL SUPERSONIC AIRFOIL PROBLEMS, Max A. Heaslet, Harvard Lomax, and Arthur L. Jones, 1947 INVESTIGATIONS OF EFFECTS OF SURFACE TEMPERATURE AND SINGLE TR 890 ROUGHNESS ELEMENTS ON BOUNDARY-LAYER TRANSITION, Hans W.

Liepmann and Gertrude H. Fila, 1947 VELOCTIY DISTRIBUTIONS ON TWO-DIMENSIONAL WING-DUCT INLETS BY TR 893 CONFORMAL MAPPING, W. Perl and H. E. Moses, 1948 ON SIMILARITY RULES FOR TRANSONIC FLOWS, Carl Kaplan, 1948 TR 894 PRESSURE-SENSITIVE SYSTEM FOR GAS-TEMPERATURE CONTROL, Richard TR 896 S. Cesaro and Norman Matz, 1948 THE USE OF SOURCE-SINK AND DOUBLET DISTRIBUTIONS EXTENDED TO THE TR 900 SOLUTION OF BOUNDARY-VALUE PROBLEMS IN SUPERSONIC FLOW, Max A.

Heaslet and Harvard Lomax, 1948 TR 902 SUBSONIC FLOW OVER THIN OBLIQUE AIRFOILS AT ZERO LIFT, Robert T.

Jones, 1948 FULL-SCALE INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF A TR 905 TYPICAL SINGLE-ROTOR HELICOPTER IN FORWARD FLIGHT, Richard C.

Dingeldein and Raymond F. Schaefer, 1948 TR 907 EQUATIONS FOR THE DESIGN OF TWO-DIMENSIONAL SUPERSONIC NOZZLES, I. Irving Pinkel, 1948 TR LAMINAR-BOUNDARY-LAYER OSCILLATIONS ANDTRANSITION ONA FLAT PLATE,G. B. Schubauerand H. K. Skramstad, 1948 TR 913 EXPERIMENTS ONSTABILITYOF BUNSEN-BURNER FLAMES FORTURBULENT FLOW, Lowell M. Bollinger and David T. Williams, 1948 TR THEEFFECTS OF AERODYNAMIC HEATING ANDHEAT TRANSFER ONTHE SURFACE TEMPERATURE OFA BODY OF REVOLUTION IN STEADY SUPERSONIC FLIGHT, Richard Scherrer, 1948 TR THEORETICAL MOTIONS OFHYDROFOIL SYSTEMS, Frederick H. Imlay, 1948 TR ACCURACY OF AIRSPEED MEASUREMENTS ANDFLIGHTCALIBRATION PRO- CEDURES, Wilber B. Huston, 1948 TR 920 THEDEVELOPMENT ANDAPPLICATION OF HIGH-CRITICAL-SPEED NOSE INLETS, Donald D. Baals, NormanF. Smith and John B. Wright, TR CHARACTERISTICS OF LOW-ASPECT-RATIO WINGS AT SUPER-CRITICAL MACH NUMBERS, John Stack and W. F. Lindsey, 1949 TR 932 EFFECT OFREYNOLDS NUMBER IN TURBULENT-FLOW RANGE ONFLAME SPEEDS OF BUNSEN-BURNER FLAMES, Lowell M. Bollinger and David T.

Williams, 1949 TR 938 SUMMARY OF SECTION DATAONTRAILING-EDGE HIGH-LIFTDEVICES,Jones F. Cahill, 1949 TR THEORETICAL CHARACTERISTICS IN SUPERSONIC FLOW OF TWO TYPES OF CONTROL SURFACES ONTRIANGULAR WINGS,Warren A. Tucker and Robert L. Nelson, 1949 TR 940 THEDESIGN OF LOW-TURBULENCE WINDTUNNELS, Hugh L. Dryden and Ira H. Abbott, 1949 TR 944 HEATTRANSFER TO BODIES TRAVELING AT HIGHSPEED IN THEUPPER ATMOSPHERE, Jackson R. Stalder and David Jukoff, 1949 TR TWO-DIMENSIONAL UNSTEADY LIFT PROBLEMS IN SUPERSONIC FLIGHT,Max A. Heaslet and Harvard Lomax, 1949 TR 947 THEDEVELOPMENT OF CAMBERED AIRFOIL SECTIONS HAVING FAVORABLE LIFT CHARACTERISTICS AT SUPERCRITICAL MACH NUMBERS, Donald J.

Graham, 1949 TR AN APPARATUS FORVARYING EFFECTIVE DIHEDRAL IN FLIGHTWITHAPPLICA- TION TO A STUDY OFTOLERABLE DIHEDRAL ONA CONVENTIONAL FIGHTER AIRPLANE, William M. Kauffman, Charles J. Liddell, Jr., Allan Smith, and Rudolph D. Van Dyke, Jr., 1949 TR 949 EFFECT OF SCREENS IN WIDE-ANGLE DIFFUSERS, G. B. Schubauer and W. G. Spangenberg, 1949 TR 951 USEOF SOURCE DISTRIBUTIONS FOREVALUATING THEORETICAL AERODYNAMICS OF THIN FINITE WINGS AT SUPERSONIC SPEEDS, John C. Evvard, 1950 TR 953 ATTAINABLE CIRCULATION ABOUT AIRFOILSIN CASCADE, Arthur W.

Goldstein and Artur Mager, 1950 TR 956 LINEARIZED COMPRESSIBLE-FLOW THEORY FORSONIC FLIGHTSPEEDS, Max A. Heaslet, Harvard Lomax, and John R. Spreiter, 1950 TR 957 THECALCULATION OF DOWNWASH BEHINDSUPERSONIC WINGS WITHAN APPLICATION TO TRIANGULAR PLANFORMS, Harvard Lomax, LomaSluder, and Max A. Heaslet, 1950 TR 958 LAMINAR MIXINGOF A COMPRESSIBLE FLUID, Dean R. Chapman,1950 TR 959 ONE-DIMENSIONAL FLOWS OFAN IMPERFECT DIATOMIC GAS,A. J. Eggers, Jr., 1950 THEAPPLICATION OF GREEN'S THEOREM TO THESOLUTION OF BOUNDARY- TR 961 VALUE PROBLEMS IN LINEARIZED SUPERSONIC WING THEORY, Max A. Heaslet and Harvard Lomax, 1950 TR 962 THEAERODYNAMIC FORCES ONSLENDER PLANE-AND CRUCIFORM-WING ANDBODY COMBINATIONS, John R. Spreiter, 1950 TR 963 INVESTIGATION WITHAN INTERFEROMETER OF THETURBULENT MIXINGOF A FREESUPERSONIC JET, Paul B. Gooderum,George P. Wood, and Maurice J. Brevoort, 1950 TR 964 THEEFFECTS OF VARIATIONS IN REYNOLDS NUMBER BETWEEN 3.0 x 106 AND 25.0 x 106 UPON THEAERODYNAMIC CHARACTERISTICS OFA NUMBER OF NACA 6-SERIESAIRFOIL SECTIONS, Laurence K. Loftin, Jr. and William J.

Bursnall, 1950 TR THEORETICAL LIFT ANDDAMPING IN ROLLAT SUPERSONIC SPEEDS OF THIN SWEPTBACK TAPERED WINGS WITHSTREAMWISE TIPS, SUBSONIC LEADING EDGES, ANDSUPERSONIC TRAILINGEDGES, Frank S. Malvestuto, Jr., Kenneth Margolis, and Herbert S. Ribner, 1956 TR 974 THESUPERSONIC AXIAL-FLOW COMPRESSOR, Arthur Kantrowitz, 1950 TR 976 LINEARTHEORY OF BOUNDARY EFFECTS IN OPEN WINDTUNNELS WITHFINITE JET LENGTHS, S. Katzoff, Clifford S. Gardner, Leo Diesendruck, and Bertram J. Eisenstadt, 1950 TR FREQUENCY RESPONSE OF LINEARSYSTEMS FROM TRANSIENT DATA,Melvin E. Leveine and Aaron S. Boksenbom,1950 TR 978 METHOD OF DESIGNING CASCADE BLADES WITH PRESCRIBED VELOCITY DISTRIBUTIONS IN COMPRESSIBLE POTENTIAL FLOWS, George R.

Costello, 1950 TR 979 ON STABILITY OF FREE LAMINAR BOUNDARY LAYER BETWEEN PARALLEL STREAMS, Martin Lessen, 1950 TR 983 LINE-VORTEX THEORY FOR CALCULATION OF SUPERSONIC DOWNWASH, Harold Mirels and Rudolph C. Haefeli, 1950 TR 985 A RADAR METHOD OF CALIBRATING AIRSPEED INSTALLATIONS ON AIR- PLANES IN MANEUVERS AT HIGH ALTITUDES AND AT TRANSONIC AND SUPERSONIC SPEEDS, John A. Zalovcik, 1950 TR 986 THE REVERSIBILITY THEOREM FOR THIN AIRFOILS IN SUBSONIC AND SUPERSONIC FLOW, Clinton E. Brown, 1950 TR 988 COMPARATIVE DRAG MEASUREMENTS AT TRANSONIC SPEEDS OF RECTANGULAR AND SWEPTBACK NACA 65-009 AIRFOILS MOUNTED ON A FREELY FALLING BODY, Charles W. Mathews and Jim Rogers Thompson, 1950 TR 990 AN ANALYSIS OF SUPERSONIC AERODYNAMIC HEATING WITH CONTINUOUS FLUID INJECTION, E. B. Klunker and H Reese Ivey, 1950 TR 995 BLOCKAGE CORRECTIONS FOR THREE-DIMENSIONAL-FLOW CLOSED-THROAT WIND TUNNELS, WITH CONSIDERATION OF THE EFFECT OF COMPRESSIBILITY, John G. Herriot, 1950 TR 998 FURTHER EXPERIMENTS ON THE FLOW AND HEAT TRANSFER IN A HEATED TURBULENT AIR JET, Stanley Corrsin and Mahnider S. Uberoi, 1950 TR 1002 ON THE THEORY OF OSCILLATING AIRFOILS OF FINITE SPAN IN SUBSONIC COMPRESSIBLE FLOW, Eric Reissner, 1950 TR 1004 A LIFT-CANCELLATION TECHNIQUE IN LINEARIZED SUPERSONIC-WING THEORY, Harold Mirels, 1951 TR 1015 ANALYSIS OF TURBULENT FREE-CONVECTION BOUNDARY LAYER ON FLAT PLATE, E. R. G. Eckert and Thomas W. Jackson, 1951 TR 1016 EFFECT OF TUNNEL CONFIGURATION AND TESTING TECHNIQUE ON CASCADE PERFORMANCE, John R. Erwin and James C. Emery, 1951 TR 1020 MEASUREMENTS OF AVERAGE HEAT-TRANSFER AND FRICTION COEFFICIENTS FOR SUBSONIC FLOW OF AIR IN SMOOTH TUBES AT HIGH SURFACE AND FLUID TEMPERATURES, Leroy V. Humble, Warren H. Lowdermilk, and Leland G. Desmon, 1951 TR 1022 TEMPERATURE DISTRIBUTION IN INTERNALLY HEATED WALLS OF HEAT EXCHANGERS COMPOSED OF NONCIRCULAR FLOW PASSAGES, E. R. G. Eckert and George M. Low, 1951 EXPERIMENTAL ANDTHEORETICAL STUDIES OFAREASUCTION FORTHE rR 1025 CONTROL OF THELAMINAR BOUNDARY LAYER ONAN NACA 64A010AIRFOIL, Albert L. Braslow, Dale L. Burrows, Neal Tetervin and Fioravante Visconti, 1951 EFFECT OF ASPECT RATIOONTHEAIR FORCES ANDMOMENTS OF HARMONI- TR 1028 CALLYOSCILLATING THIN RECTANGULAR WINGS IN SUPERSONIC POTENTIAL FLOW,Charles E. Watkins, 1951 INVESTIGATION OF SEPARATION OF THETURBULENT BOUNDARY LAYER, TR 1030 G. B. Schubauer and P. S. Klebanoff, 1951 TR 1032 A COMPARISON OFTHEORY ANDEXPERIMENT FORHIGH-SPEED FREE- MOLECULE FLOW,Jackson R. Stalder, Glen Goodwin, and Marcus O.

Creager, 1951 COMPARISON BETWEEN THEORY ANDEXPERIMENT FORWINGS AT SUPERSONIC TR 1033 SPEEDS, Walter G. Vincenti, 1951 TR 1036 EXPERIMENTAL INVESTIGATION OF THEEFFECTS OF VISCOSITY ONTHE DRAG ANDBASE PRESSURE OF BODIES OF REVOLUTION AT A MACH NUMBER OF 1.5, DeanR. Chapman and EdwardW. Perkins, 1951 TR 1038 WIND-TUNNEL INVESTIGATION OF AIR INLETANDOUTLET OPENINGS ONA STREAMLINE BODY,John V. Becker, 1951 1039 ONTHEPARTICULAR INTEGRALS OFTHEPRANDTL-BUSEMANN ITERATION TR EQUATIONS FORTHEFLOW OFA COMPRESSIBLE FLUID, Carl Kaplan, 1951 TR 1040 SPECTRA ANDDIFFUSION IN A ROUND TURBULENT JET, Stanley Corrsin and Mahinder S. Uberoi, 1951 THEMETHOD OF CHARACTERISTICS FORTHEDETERMINATION OF SUPERSONIC TR 1044 FLOW OVER BODIES OF REVOLUTION AT SMALL ANGLES OF ATTACK, Antonio Ferri, 1951 TR 1045 SUPERSONIC FLOW AROUND CIRCULAR CONES AT ANGLES OF ATTACK, Antonio Ferri, 1951 TR 1046 A GENERAL INTEGRAL FORM OF THEBOUNDARY-LAYER EQUATION FORIN- COMPRESSIBLE FLOW WITHAN APPLICATION TO THECALCULATION OF THE SEPARATION POINTOF TURBULENT BOUNDARY LAYERS, Neal Tetervin and Chia Chiao Lin, 1951 A STUDY OF EFFECTS OF VISCOSITY ONFLOW OVER SLENDER INCLINED TR 1048 BODIES OFREVOLUTION, H. Julian Allen and EdwardW. Perkins, FORMULAS FORTHESUPERSONIC LOADING, LIFT ANDDRAG OF FLAT TR 1050 SWEPT-BACK WINGS WITHLEADING EDGES BEHIND THEMACH LINES, Doris Cohen, 1951 TR 1051 AN ANALYSIS OF BASE PRESSURE AT SUPERSONIC VELOCITIES AND COMPARI- SON WITH EXPERIMENT, Dean R. Chapman, 1951 TR 1053 INVESTIGATION OF TURBULENT FLOW IN A TWO-DIMENSIONAL CHANNEL, John Laufer, 1951 TR 1054 INTEGRALS AND INTEGRAL EQUATIONS IN LINEARIZED WING THEORY, Harvard Lomax, Max A. Heaslet, and Franklyn B. Fuller, 1951 TR 1055 COMPARISON OF THEORETICAL AND EXPERIMENTAL HEAT-TRANSFER CHARACTERISTICS OF BODIES OF REVOLUTION AT SUPERSONIC SPEEDS, Richard Scherrer, 1951 TR ANALYSIS OF THE EFFECTS OF BOUNDARY-LAYER CONTROL ON THE TAKE- OFF AND POWER-OFF LANDING PERFORMANCE CHARACTERISTICS OF A LIAISON TYPE OF AIRPLANE, Elmer A. Horton, Laurence K. Loftin, Jr., Stanley F. Racisz, and John H. Quinn, Jr., 1951 TR 1060 DETAILED COMPUTATIONAL PROCEDURE FOR DESIGN OF CASCADE BLADES WITH PRESCRIBED VELOCITY DISTRIBUTIONS IN COMPRESSIBLE POTENTIAL FLOWS, George R. Costello, Robert L. Cummings, and John T.

Sinnette, Jr., 1952 TR 1063 AIRFOIL PROFILES FOR MINIMUM PRESSURE DRAG AT SUPERSONIC VELOCITIES --GENERAL ANALYSIS WITH APPLICATION TO LINEARIZED SUPERSONIC FLOW, Dear R. Chapman, 1952 TR 1065 CORRELATION OF PHYSICAL PROPERTIES WITH MOLECULAR STRUCTURE FOR SOME DICYCLIC HYDROCARBONS HAVING HIGH THERMAL-ENERGY RELEASE PER UNIT VOLUME--2-ALKYLBIPHENYL AND THE TWO ISOMERIC 2-ALKYLBICYCLO- HEXYL SERIES, Irving A. Goodman and Paul H. Wise, 1952 TR 1067 GENERALIZATION OF BOUNDARY-LAYER MOMENTUM-INGEGRAL EQUATIONS TO THREE-DIMENSIONAL FLOWS INCLUDING THOSE OF ROTATING SYSTEM, Artur Mager, 1952 TR 1069 ON A SOLUTION OF THE NONLINEAR DIFFERENTIAL EQUATION FOR TRANSONIC FLOW PAST A WAVE-SHAPED WALL, Carl Kaplan, 1952 TWO- AND THREE-DIMENSIONAL UNSTEADY LIFT PROBLEMS IN HIGH-SPEED TR 1077 FLIGHT, Harvard Lomax, Max A. Heaslet, Franklyn B. Fuller and Loma Sluder, 1952 TR 1078 EFFECTS OF COMPRESSIBILITY ON THE PERFORMANCE OF TWO FULL-SCALE HELICOPTER ROTORS, Paul J. Carpenter, 1952 TR 1081 A STUDY OF SECOND-ORDER SUPERSONIC FLOW THEORY, Milton D. Van Dyke, 1952 METHOD OF ANALYSIS FORCOMPRESSIBLE FLOW THROUGH MIXED-FLOW TR 1082 CENTRIFUGAL IMPELLERS OF ARBITRARY DESIGN,Joseph T. Hamrick, AmbroseGinsburg, and Walter M. Osborn, 1952 AXISYMMETRIC SUPERSONIC FLOW IN ROTATING IMPELLERS, Arthur TR 1083 W. Goldstein, 1952 DISCUSSION OF BOUNDARY-LAYER CHARACTERISTICS NEAR THEWALL OF TR ANAXIAL-FLOW COMPRESSOR, Artur Mager, John J. Mahoney, and Ray E. Budinger, 1952 INTERNAL-LIQUID-FILM-COOLING EXPERIMENTS WITHAIRSTREAM TR 1087 TEMPERATURES TO 2000°F IN 2-AND4-1NCH-DIAMETER HORIZONTAL TUBES,GeorgeR. Kinney, Andrew E. Abramsonand John L. Sloop, METHOD FORCALCULATING LIFT DISTRIBUTIONS FORUNSWEPT WINGS TR 1090 WITHFLAPSORAILERONS BYUSEOFNONLINEAR SECTION LIFT DATA, JamesC. Sivell and Gertrude C. Westrick, 1952 HEATTRANSFER TO BODIES IN A HIGH-SPEED RAREFIED-GAS STREAM, TR 1093 Jackson R. Stalder, Glen Goodwinand Marcus O. Creager, 1952 AN EXPERIMENTAL INVESTIGATION OF TRANSONIC FLOW PASTTWO- TR 1094 DIMENSIONAL WEDGE ANDCIRCULAR-ARC SECTIONS USING A MACH- ZEHNDER INTERFEROMETER, Arthur Earl Bryson, Jr., 1952 TRANSONIC FLOW PASTA WEDGE PROFILE WITHDETACHED BOW WAVE, TR 1095 Walter G. Vincenti and Cleo B. Wagoner, 1952 AIR FORCES ANDMOMENTS ONTRIANGULAR ANDRELATED WINGS WITH TR 1099 SUBSONIC LEADING EDGES OSCILLATING IN SUPERSONIC POTENTIAL FLOW, Charles E. Watkins and Julian H. Berman, 1952 ON REFLECTION OF SHOCK WAVES FROM BOUNDARY LAYERS, H. W.

TR ii00 Liepmann, A. Reshko and S. Dhawan, 1952 THE LINEARIZED CHARACTERISTICS METHOD AND ITS APPLICATION TO TR 1102 PRACTICAL NONLINEAR SUPERSONIC PROBLEMS, Antonio Ferri, 1952 PRELIMINARY INVESTIGATION OF A NEW TYPE OF SUPERSONIC INLET, TR 1104 Antonio Ferri and Louis M. Nucci, 1952 CHORDWISE AND COMPRESSIBILITY CORRECTIONS TO SLENDER-WING THEORY, TR 1105 Harvard Lomax and Loma Sluder, 1952 TR 1106 THE LANGLEY ANNULAR TRANSONIC TUNNEL, Louis W. Habel, James H.

Henderson, and Mason F. Miller, 1952 AN EMPIRICALLY DERIVED BASIS FOR CALCULATING THE AREA, RATE, AND TR 1107 DISTRIBUTION OF WATER-DROP IMPINGEMENT ON AIRFOILS, Norman F.

Bergrun, 1952 TR 1108 EXPERIMENTAL AERODYNAMIC DERIVATIVES OF A SINUSOIDALLY OSCILLATING AIRFOIL IN TWO-DIMENSIONAL FLOW, Robert L. Halfman, 1953 TR 1109 EXPERIMENTAL INVESTIGATION OF BASE PRESSURE ON BLUNT-TRAILING- EDGE WINGS AT SUPERSONIC VELOCITIES, Dean R. Chapman, William R.

Wimbrow, and Robert H. Kester, 1952 TR iii0 SOME FEATURES OF ARTIFICALLY THICKENED FULLY DEVELOPED TURBULENT BOUNDARY LAYERS WITH ZERO PRESSURE GRADIENT, P. S. Kelbanoff and Z. W. Diehl, 1952 TR 1111 AN ANALYSIS OF LAMINAR FREE-CONVECTION FLOW AND HEAT TRANSFER ABOUT A FLAT PLATE PARALLEL TO THE DIRECTION OFTHE GENERATING BODY FORCE, Simon Ostrach, 1953 TR SPECTRUM OF TURBULENCE IN A CONTRACTING STREAM, H. S. Ribner and M. Tucker, 1953 TR 1115 DESIGN OF TWO-DIMENSIONAL CHANNELS WITH PRESCRIBED VELOCITY DISTRIBUTIONS ALONG THE CHANNEL WALLS, John D. Stanitz, 1953 TR 1116 APPLICATION OF A CHANNEL DESIGN METHOD TO HIGH-SOLIDITY CASCADES AND TESTS OF AN IMPULSE CASCADE WITH 90 ° OF TURNING, John D.

Stanitz and Leonard J. Sheldrake, 1953 TR 1118 METHOD FOR CALCULATION OF LAMINAR HEAT TRANSFER IN AIR FLOW AROUND CYLINDERS OF ARBITRARY CROSS SECTION (INCLUDING LARGE TEMPERATURE DIFFERENCES AND TRANSPIRATION COOLING), E. R. G.

Eckert and John N. B. Livingood, 1953 TR 1119 RECIPROCITY RELATIONS IN AERODYNAMICS, Max A. Heaslet and John R. Spreiter, 1953 TR 1120 RELATIVE IMPORTANCE OF VARIOUS SOURCES OF DEFECT-PRODUCING HYDROGEN INTRODUCED INTO STEEL DURING APPLICATION OF VITREOUS COATINGS, Dwight G. Moore, Mary A. Mason, and William N. Harrison, TR 1121 DIRECT MEASUREMENTS OF SKIN FRICTION, Satish Dhawan, 1953 TR 1123 A STUDY OF INVISCID FLOW ABOUT AIRFOILS AT HIGH SUPERSONIC SPEEDS, A. J. Eggers, Jr., Clarence A. Syvertson, and Samuel Kraus, 1953 TR 1124 DISPLACEMENT EFFECT OF A THREE-DIMENSIONAL BOUNDARY LAYER, Franklin K. Moore, 1953 TR 1128 CALCULATIONS ON THE FORCES AND MOMENTS FOR AN OSCILLATING WING- AILERON COMBINATION IN TWO-DIMENSIONAL POTENTIAL FLOW AT SONIC SPEED, Herbert C. Nelson and Julian H. Berman, 1953 TR 1132 LAMINAR BOUNDARY LAYER ON CONE IN SUPERSONIC FLOW AT LARGE ANGLE OF ATTACK, Franklin K. Moore, 1953 DIFFUSION OF HEAT FROM A LINE SOURCE IN ISOTROPIC TURBULENCE, TR 1142 Mahinder S. Uberoi and Stanley Corrsin, 1953 A VECTOR STUDY OF LINEARIZED SUPERSONIC FLOW APPLICATIONS TO TR 1143 NONPLANAR PROBLEMS, John C. Martin, 1953 AERODYNAMIC CHARACTERISTICS OF A REFINED DEEP-STEP PLANING-TAIL TR 1144 FLYING-BOAT HULL WITH VARIOUS FOREBODY AND AFTERBODY SHAPES, John M. Riebe and Rodger L. Naeseth, 1953 A METHOD OF CALIBRATING AIRSPEED INSTALLATIONS ON AIRPLANES AT TR 1145 TRANSONIC AND SUPERSONIC SPEEDS BY THE USE OF ACCELEROMETER AND ATTITUDE-ANGLE MEASUREMENTS, John A. Zalovcik, Lindsay J. Lina, and James P. Trant, Jr., 1953 TR 1146 AERODYNAMIC FORCES AND LOADINGS ON SYMMETRICAL CIRCULAR-ARC AIRFOILS WITH PLAIN LEADING-EDGE AND PLAIN TRAILING-EDGE FLAPS, Jones F. Cahill, William J. Underwood, Robert J. Nuber, and Gall A. Cheesman, 1953 TR 1147 THE SIMILARITY LAW FOR HYPERSONIC FLOW AND REQUIREMENTS FOR DYNAMIC SIMILARITY OF RELATED BODIES IN FREE FLIGHT, Frank M.

Hamaker, Stanford E. Neice, and Thomas J. Wong, 1953 TR 1149 ON TRANSONIC FLOW PAST A WAVE-SHAPED WALL, Carl Kaplan, 1953 TR 1150 CONSIDERATIONS ON THE EFFECT OF WIND-TUNNEL WALLS ON OSCILLATING AIR FORCES FOR TWO-DIMENSIONAL SUBSONIC COMPRESSIBLE FLOW, Harry L. Runyan and Charles E. Watkins, 1953 1153 ON THE APPLICATION OF TRANSONIC SIMILARITY RULES TO WINGS OF TR FINITE SPAN, John R. Spreiter, 1953 A COMPARISON OF THE EXPERIMENTAL SUBSONIC PRESSURE DISTRIBUTIONS TR 1155 ABOUT SEVERAL BODIES OF REVOLUTION WITH PRESSURE DISTRIBUTIONS COMPUTED BY MEANS OF THE LINEARIZED THEORY, Clarence W. Matthews, TR 1159 IMPINGEMENT OF WATER DROPLETS ON WEDGES AND DOUBLE-WEDGE AIRFOILS AT SUPERSONIC SPEEDS, John S. Serafini, 1954 TR 1160 THE ZERO-LIFT DRAG OF A SLENDER BODY OF REVOLUTION (NACA RM -- i0 RESEARCH MODEL) AS DETERMINED FROM TESTS IN SEVERAL WIND TUNNELS AND IN FLIGHT AT SUPERSONIC SPEEDS, Albert J. Evans, 1954 TR 1161 AVERAGE SKIN-FRICTION DRAG COEFFICIENTS FROM TANK TESTS OF A PARA- BOLIC BODY OF REVOLUTION (NACA RM--IO), Elmo J. Mottard and J. Dan Loposer, 1954 TR 1164 CONVECTION OFA PATTERN OFVORTICITY THROUGH A SHOCK WAVE, H. S.

Ribner, 1954 TR 1165 UNSTEADY OBLIQUE INTERACTION OFA SHOCK WAVE WITHA PLANE DISTRUBANCE, Franklin K. Moore, 1954 TR EFFECT OF HORIZONTAL-TAIL SPAN ANDVERTICAL LOCATION ONTHE AERODYNAMIC CHARACTERISTICS OFAN UNSWEPT TAIL ASSEMBLY IN SIDESLIP, Donald R. Riley, 1954 TR THESTRUCTURE OFTURBULENCE IN FULLYDEVELOPED PIPE FLOW, John Lanfer, 1954 TR 1175 EFFECT OFVARIABLE VISCOSITY ANDTHERMAL CONDUCTIVITY ONHIGH- SPEED SLIP FLOW BETWEEN CONCENTRIC CYLINDERS, T. C. Lin and R. E. Street, 1954 TR A NOTE ONSECONDARY FLOW IN ROTATING RADIALCHANNELS, JamesJ.

Kramer and John D. Stanitz, 1954 TR 1180 THEORETICAL STUDY OF THETRANSONIC LIFT OF A DOUBLE-WEDGE PROFILE WITHDETACHED BOW WAVE, Walter G. Vincenti and Cleo B. Wagoner, TR 1182 COMPARISON OF EFFECTIVENESS OF CONVECTION-, TRANSPIRATION-, AND FILM-COOLING METHODS WITHAIR AS COOLANT, E. R. G. Eckert and John N. B. Livingood, 1954 TR SUPERSONIC FLOW PASTOSCILLATING AIRFOILSINCLUDING NONLINEAR THICKNESS EFFECTS, Milton D. Van Dyke, 1954 TR 1184 THENORMAL COMPONENT OF THEINDUCED VELOCITY IN THEVICINITY OF A LIFTING ROTOR ANDSOME EXAMPLES OF ITS APPLICATION, Walter Castles, Jr., and Jacob Henri De Leeuw, 1954 TR 1185 THECALCULATION OF PRESSURE ONSLENDER AIRPLANES IN SUBSONIC ANDSUPERSONIC FLOW, Max A. Heaslet and Harvard Lomax, 1954 TR FORMATION ANDCOMBUSTION OF SMOKE IN LAMINAR FLAMES, Rose L.

Schalla, ThomasP. Clark, and Glen E. McDonald, 1954 TR 1187 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OFADDITIVEDRAG, Nerwin Sibulkin, 1954 TR THEORETICAL ANDEXPERIMENTAL ANALYSIS OF LOW-DRAG SUPERSONIC INLETSHAVING A CIRCULAR CROSS SECTION ANDA CENTRAL BODY AT MACH NUMBERS OF 3.30, 2.75, AND2.45, Antonio Ferri and Louis M. Nucci, 1954 TR ONTHEDEVELOPMENT OF TURBULENT WAKES FROM VORTEX STREETS, Anatol Roshko, 1954 TR 1194 A STUDY OF HYPERSONIC SMALL-DISTURBANCE THEORY, Milton D. Van Dyke, 1954 TR 1196 AN ANALYTICAL STUDY OF THE EFFECT OF AIRPLANE WAKE ON THE LATERAL DISPERSION OF AERIAL SPRAYS, Wilmer H. Reed, III, 1954 TR 1201 PERFORMANCE AND BOUNDARY-LAYER DATA FROM 12 ° AND 23 ° CONICAL DIFFUSERS OF AREA RATIO 2.0 AT MACH NUMBERS UP TO CHOKING AND REYNOLDS NUMBERS UP TO 7.5 X 106 , B. H. Little, Jr. and Stafford W. Wilbur, 1954 TR 1202 CHARTS RELATING THE COMPRESSIVE BUCKLING STRESS OF LONGITUDI- NALLY SUPPORTED PLATES TO THE EFFECTIVE DEFLECTIONAL AND ROTA- TIONAL STIFFNESS OF THE SUPPORTS, Roger A. Anderson and Joseph W. Semonian, 1954 TR 1209 DEVELOPMENT OF TURBULENCE-MEASURING EQUIPMENT, Leslie S. G.

Kovasznay, 1954 TR 1210 ANALYSIS OF TURBULENT HEAT TRANSFER, MASS TRANSFER, AND FRICTION IN SMOOTH TUBES AT HIGH PRANDTL AND SCHMIDT NUMBERS, Robert G.

Deissler, 1955 TR 1211 EXPERIMENTAL INVESTIGATION OF FREE-CONVECTION HEAT TRANSFER IN VERTICAL TUBE AT LARGE GRASHOF NUMBERS, E. R. G. Eckert and A. J. Diaguila, 1955 TR 1213 MINIMUM-DRAG DUCTED AND POINTED BODIES OF REVOLUTION BASED ON LINEARIZED SUPERSONIC THEORY, Hermon M. Parker, 1955 TR 1215 IMPINGEMENT OF CLOUD DROPLETS ON A CYLINDER AND PROCEDURE FOR MEASURING LIQUID-WATER CONTENT AND DROPLET SIZES IN SUPERCOOLED CLOUDS BY ROTATING MULTICYLINDER METHOD, R. J. Brun, W. Lewis, P. J. Perkins, and J. S. Serafini, 1955 1216 CHARTS FOR ESTIMATING TAIL-ROTOR CONTRIBUTION TO HELICOPTER TR DIRECTIONAL STABILITY AND CONTROL IN LOW-SPEED FLIGHT, Kenneth B. Amer and Alfred Gessow, 1955 TR 1217 THEORETICAL PREDICTION OF PRESSURE DISTRIBUTIONS ON NONLIFTING AIRFOILS AT HIGH SUBSONIC SPEEDS, John R. Spreiter and Alberta Alksne, 1955 EFFECT OF GROUND INTERFERENCE ON THE AERODYNAMIC AND FLOW CHARAC- TR 1218 TERISTICS OF A 42 ° SWEPTBACK WING AT REYNOLDS NUMBERS UP TO 6.8 X 106 , G. Chester Furlong and Thomas V. Bollech, 1955 TR 1220 CALCULATIONS OF LAMINAR HEAT TRANSFER AROUND CYLINDERS OF ARBITRARY CROSS SECTION AND TRANSPIRATION-COOLED WALLS WITH APPLICATION TO TURBINE BLADE COOLING, E. R. G. Eckert and J. N. B. Livingood, 1955 TR 1221 THEORETICAL STUDY OFTHETUNNEL-BOUNDARY LIFT INTERFERENCE DUE TO SLOTTED WALLS IN THEPRESENCE OFTHETRAILING-VORTEX SYSTEM OFA LIFTINGMODEL, Clarence W. Matthews, 1955 TR A FREE-FLIGHT WIND TUNNEL FORAERODYNAMIC TESTING AT HYPERSONIC SPEEDS, Alvin Seiff, 1955 TR 1223 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OFHEATTRANSFER BY LAMINAR NATURAL CONVECTION BETWEEN PARALLEL PLATES,A. F.

Lietzke. lO55 TR 1226 A METHOD FORTHEDESIGN OF SWEPTBACK WINGS WARPED TO PRODUCE SPECIFIED FLIGHTCHARACTERISTICS AT SUPERSONIC SPEEDS, Warren A. Tucker, 1955 TR 1227 AN INVESTIGATION OF THEMAXIMUM LIFT OFWINGS AT SUPERSONIC SPEEDS, JamesJ. Gallagher and JamesN. Mueller, 1955 TR EXACT SOLUTIONS OF LAMINAR-BOUNDARY-LAYER EQUATIONS WITHCONSTANT PROPERTY VALUES FORPOROUS WALL WITHVARIABLE TEMPERATURE, Patrick L. Donougheand John N. B. Livingood, 1955 TR 1230 GENERALIZED IDICIAL FORCES ONDEFORMING RECTANGULAR WINGS IN SUPERSONIC FLIGHT,Harvard Lomax, Franklyn B. Fuller, and Loma Sluder, 1955 TR 1231 NACA TRANSONIC WIND-TUNNEL TESTSECTIONS, Ray H. Wright and Vernon G. Ward, 1955 TR 1232 A THEORETICAL ANDEXPERIMENTAL INVESTIGATION OF THELIFT AND DRAG CHARACTERISTICS OF HYDROFOILS AT SUBCRITICAL ANDSUPER- CRITICALSPEEDS, Kenneth L. Wadlin, Charles L. Shuford, Jr., and John R. McGehee,1955 TR SHOCK-TURBULENCE INTERACTION ANDTHEGENERATION OFNOISE, H. S.

Ribner, 1955 TR STANDARD ATMOSPHERE -- TABLES ANDDATAFORALTITUDES TO 65,800 FEET, International Civil Aviation Organization and NACA,1955 TR 1236 ARRANGEMENT OF FUSIFORM BODIES TO REDUCE THEWAVE DRAG AT SUPER- SONICSPEEDS, Morris D. Friedman and Doris Cohen, 1955 TR 1238 INVESTIGATION AT SUPERSONIC SPEEDS OF 22 TRIANGULAR WINGS REPRE- SENTING TWO AIRFOIL SECTIONS FOREACH OF ii APEXANGLES, Eugene S. Love, 1955 TR ERROR IN AIRSPEED MEASUREMENT DUETO THESTATIC-PRESSURE FIELD AHEAD OF ANAIRPLANE AT TRANSONIC SPEEDS, ThomasC. O'Bryan, EdwardC. B. Danforth, and J. Ford Johnston, 1955 AN INVESTIGATION OF THEEFFECTS OFHEATTRANSFER ONBOUNDARY- TR 1240 LAYER TRANSITION ONA PARABOLIC BODY OFREVOLUTION (NACA RM- i0) AT A MACH NUMBER OF 1.61, K. R. Czarnecki and Archibald R. Sinclair, 1955 TR 1242 TRANSONIC FLOW PASTCONE CYLINDERS, George E. Solomon, 1955 TR 1243 HIGH-RESOLUTION AUTORADIOGRAPHY, George C. Towe, Henry J.

Gomberg,and J. W. Freeman, 1955 TR 1244 FREE-STREAM BOUNDARIES OF TURBULENT FLOWS, Stanley Corrsin and Alan Lo Kistler, 1955 TR 1245 ANALYSIS ANDCALCULATION BY INTEGRAL METHODS OF LAMINAR COM- PRESSIBLE BOUNDARY LAYER WITHHEATTRANSFER ANDWITHANDWITHOUT PRESSURE GRADIENT, Morris Morduchow,1955 TR 1246 THEHYDRODYNAMIC CHARACTERISTICS OF MODIFIED RECTANGULAR FLAT PLATES HAVING ASPECT RATIOS OF 1.00, 0.25, AND0.125 ANDOPERAT- ING NEAR A FREE WATER SURFACE, Kenneth L. Wadlin, John A. Ramsen, and Victor L. Vaughan, Jr., 1955 CHARACTERISTICS OF TURBULENCE IN A BOIHFDARYLAYER WITHZERO TR 1247 PRESSURE GRADIENT, P. S. Klebanoff, 1955 TR 1249 A UNIFIEDTWO-DIMENSIONAL APPROACH TO THECALCULATION OF THREE- DIMENSIONAL HYPERSONIC FLOWS, WITHAPPLICATION TO BODIES OF REVOLUTION, A. J. Eggers, Jr., and Raymond C. Savin, 1955 TR 1252 QUASI-CYLINDRICAL THEORY OF WING-BODY INTERFERENCE AT SUPERSONIC SPEEDS ANDCOMPARISON WITHEXPERIMENT, Jack N. Nielsen, 1955 TR 1253 A CORRELATION BYMEANS OF TRANSONIC SIMILARITYRULES OF EXPERI- MENTALLY DETERMINED CHARACTERISTICS OF A SERIESOF SYMMETRICAL ANDCAMBERED WINGS OF RECTANGULAR PLANFORM, John B. McDevitt, TR 1256 AXIALLYSYMMETRIC SHAPES WITHMINIMUM WAVE DRAG, Max A. Heaslet and Franklyn B. Fuller, 1956 TR 1257 ONTHEKERNEL FUNCTION OF THEINTEGRAL EQUATION RELATING LIFT AND DOWNWASH DISTRIBUTIONS OF OSCILLATING WINGS IN _ITPERSONIC FLOW, Charles E. Watkins and Julian H. Berman, 1956 TR 1259 SOME POSSIBILITIESOF USINGGASMIXTURES OTHER THAN AIR IN AERO- DYNAMIC RESEARCH, Dear.R. Chapman,1956 TR 1261 THENEAR NOISEFIELD OF STATICJETSANDSOME MODEL STUDIES OF DEVICES FORNOISEREDUCTION, Leslie W. Lassiter and Harvey H.

Hubbard, 1956 TR 1262 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OFTHEEFFECT OF TUNNEL WALLS ONTHEFORCES ONAN OSCILLATING AIRFOIL IN TWO- DIMENSIONAL SUBSONIC COMPRESSIBLE FLOW,Harry L. Runyan, Donald S. Woolston, and A. Gerald Rainey, 1956 TR 1263 INVESTIGATION OFTHEAERODYNAMIC CHARACTERISTICS OF A MODEL WING-PROPELLER COMBINATION ANDOF THEWING ANDPROPELLER SEPARATELY AT ANGLES OFATTACK UP TO 90°, Richard E. Kuhn and John W. Draper, 1956 TR 1266 CHARTS FORESTIMATING PERFORMANCE OF HIGH-PERFORMANCE HELICOPTERS, Alfred Gessowand Robert J. Tapscott, 1956 TR 1270 REVIEW OF EXPERIMENTAL INVESTIGATIONS OFLIQUID-METAL HEAT TRANSFER, Bernard Lubarsky and Samuel J. Kaufman, 1956 TR 1271 ONBOATTAIL BODIES OFREVOLUTION HAVING MINIMUM WAVE DRAG, Keith C. Harder and Conrad Rennemann, Jr., 1956 TR A STUDY OFTHEZERO-LIFT DRAG-RISE CHARACTERISTICS OFWING- BODY COMBINATIONS NEAR THESPEED OF SOUND, Richard T. Whitcomb, TR 1274 SECOND-ORDER SUBSONIC AIRFOIL THEORY INCLUDING EDGE EFFECTS, Milton D. Van Dyke, 1956 TR 1276 WIND-TUNNEL ANDFLIGHTINVESTIGATIONS OF THEUSEOF LEADING- EDGE AREA SUCTION FORTHEPURPOSE OF INCREASING THEMAXIMUM LIFT COEFFICIENT OF A 35 ° SWEPT-WING AIRPLANE, Curt A.

Holzhauser and Richard S. Bray, 1956 TR 1277 INTERACTION OF A FREE FLAME FRONT WITH A TURBULENCE FIELD, Maurice Tucker, 1956 TR 1279 THEORETICAL ANALYSIS OF INCOMPRESSIBLE FLOW THROUGH A RADIAL- INLET CENTRIFUGAL IMPELLER AT VARIOUS WEIGHT FLOWS, James J.

Kramer, Vasily D. Prian, and Chung-Hua Wu, 1956 TR 1281 FLIGHT DETERMINATION OF DRAG OF NORMAL-SHOCK NOSE INLETS WITH VARIOUS COWLING PROFILES AT MACH NUMBERS FROM 0.9 TO 1.5, R. I.

Sears, C. F. Merlet, and L. W. Putland, 1956 TR 1282 A SPECIAL METHOD FOR FINDING BODY DISTORTIONS THAT REDUCE THE WAVE DRAG OF WING AND BODY COMBINATIONS AT SUPERSONIC SPEEDS, Harvard Lomax and Max A. Heaslet, 1956 TR 1283 EXTRAPOLATION TECHNIQUES APPLIED TO MATRIX METHODS IN NEUTRON DIFFUSION PROBLEMS, Robert R. McCready, 1956 TR 1284 THEORY OF WING-BODY DRAG AT SUPERSONIC SPEEDS, Robert T. Jones, TR 1289 CONTRIBUTIONS ON THE MECHANICS OF BOUNDARY-LAYER TRANSITION, G. B. Schubauer and P. S. Klebanoff, 1956 TR 1291 LIFT HYSTERESIS AT STALL AS AN UNSTEADY BOUNDARY-LAYER PHENOMENON, Franklin K. Moore, 1956 TR 1292 INTENSITY, SCALE, AND SPECTRA OF TURBULENCE IN MIXING REGION OF FREE SUBSONIC JET, James C. Laurence, 1956 TR 1293 SIMILAR SOLUTIONS FOR THE COMPRESSIBLE LAMINAR BOUNDARY LAYER WITH HEAT TRANSFER AND PRESSURE GRADIENT, Clarence B. Cohen and Eli Reshotko, 1956 TR THE COMPRESSIBLE LAMINAR BOUNDARY LAYER WITH HEAT TRANSFER AND ARBITRARY PRESSURE GRADIENT, Clarence B. Cohen and Eli Reshotko, TR 1296 A THEORETICAL STUDY OF THE AERODYNAMICS OF SLENDER CRUCIFORM- WING ARRANGEMENTS AND THEIR WAKES, John R. Spreiter and Alvin H.

Sacks, 1957 TR 1297 NONLIFTING WING-BODY COMBINATIONS WITH CERTAIN GEOMETRIC RESTRAINTS HAVING MINIMUM WAVE DRAG AT LOW SUPERSONIC SPEEDS, Harvard Lomax, TR 1301 LINEARIZED LIFTING-SURFACE AND LIFTING-LINE EVALUATIONS OF SIDE- WASH BEHIND ROLLING TRIANGULAR WINGS AT SUPERSONIC SPEEDS, Percy J. Bobbitt, 1957 TR WIND-TUNNEL INVESTIGATION OF A NUMBER OF TOTAL-PRESSURE TUBES AT HIGH ANGLES OF ATTACK -- SUBSONIC, TRANSONIC, AND SUPERSONIC SPEEDS, William Gracey, 1957 TR 1306 BODIES OF REVOLUTION HAVING MINIMUM DRAG AT HIGH SUPERSONIC AIR- SPEEDS, A. J. Eggers, Jr., Meyer M. Resnikoff, and David H. Dennis, TR 1307 LIFT AND CENTER OF PRESSURE OF WING-BODY-TAlL COMBINATIONS AT SUB- SONIC, TRANSONIC, AND SUPERSONIC SPEEDS, William C. Pitts, Jack N.

Nielsen, and George E. Kaattari, 1957 TR 1310 AN INVESTIGATION OF FOUR WINGS OF SQUARE PLAN FORM AT A MACH NUM- BER OF 6.9 IN THE LANGLEY II-INCH HYPERSONIC TUNNEL, Charles M.

McLellan, Mitchel H. Bertram, and John A. Moore, 1957 TR 1311 DETERMINATION OF VORTEX PATHS BY SERIES EXPANSION TECHNIQUE WITH APPLICATION TO CRUCIFORM WINGS, Alberta Y. Alksne, 1957 TR 1312 SOME EFFECTS OF BLUNTNESS ONBOUNDARY-LAYER TRANSITION ANDHEAT TRANSFER AT SUPERSONIC SPEEDS, W, E. Moeckel, 1957 TR 1313 EXPLORATORY INVESTIGATION OF BOUNDARY-LAYER TRANSITION ONA HOLLOW CYLINDER AT A MACH NUMBER OF 6.9, Mitchel H. Bertram, TR 1314 SUMMARY OF SCALE-MODEL THRUST-REVERSER INVESTIGATION, John H.

Povolny, Fred W. Steffen, and Jack G. McArdle, 1957 TR 1315 ONSLENDER-BODY THEORY AT TRANSONIC SPEEDS, Keith C. Harder and E. B. Klunker, 1957 TR 1318 THREE-DIMENSIONAL TRANSONIC FLOW THEORY APPLIED TO SLENDER WINGS ANDBODIES, Max A. Heaslet and John R. Spreiter, 1957 TR 1319 INDUCED VELOCITIES NEAR A LIFTING ROTOR WITHNON-UNIFORM DISK LOADING, Harry H. Heyson and S. Katzoff, 1957 TR 1320 AN EVALUATION OF FOUR EXPERIMENTAL METHODS FORMEASURING MEAN PROPERTIES OFA SUPERSONIC TURBULENT BOUNDARY LAYER,George J.

Nothwang, 1957 TR 1323 INVESTIGATION OFTHELAMINAR AERODYNAMIC HEAT TRANSFER CHARAC- TERISTICS OFA HEMISPHERE-CYLINDER IN THELANGLEY II-INCH HYPERSONIC TUNNEL AT A MACH NUMBER OF 6.8, Davis H. Crawford and William D. McCauley, 1957 TR 1325 AVERAGE PROPERTIES OF COMPRESSIBLE LAMINAR BOUNDARY LAYER ON FLATPLATE WITHUNSTEADY FLIGHTVELOCITY, Franklin K. Moore and Simon Ostrach, 1957 TR 1328 A SECOND ORDER SHOCK-EXPANSION METHOD APPLICABLE TO BODIES OF REVOLUTION NEAR ZERO LIFT, Clarence A. Syvertson and David H.

Dennis, 1957 TR FARNOISEFIELD OFAIR JET- ANDJET ENGINES, Edmund E.

Calingliammad and Willard D. Coles, 1957 TR 1333 ATTENUATION IN A SHOCK TUBE DUETO UNSTEADY-BOUNDARY-LAYER ACTION,Harold Mirels, 1957 TR 1334 RELATION OF TURBOJET ANDRAMJET COMBUSTION EFFICIENCY TO SECOND- ORDER REACTION KINETICSANDFUNDAMENTAL FLAME SPEED, J. Howard Childs, Thaine W. Reynolds, and Charles C. Graves, 1957 TR 1335 MINIMUM WAVE DRAG FORARBITRARY ARRANGEMENTS OFWINGS ANDBODIES, Robert T. Jones, 1957 TR 1338 NEAR NOISEFIELD OFA JET-ENGINE EXHAUST, Walton L. Howes,Edmund E. Callaghan, Willard D. Coles, and Harold R. Mull, 1957 TR 1340 INVESTIGATION OF DOWN-WASH, SIDEWASH, AND MACH NUMBER DISTRIBUTION BEHIND A RECTANGULAR WING AT A MACH NUMBER OF 2.41, David Adamson and William B. Boatright, 1957 TR 1346 DIFFERENTIAL EQUATIONS OF MOTION FOR COMBINED FLAPWISE BENDING, CHORDWISE BENDING, AND TORSION OF TWISTED NONUNIFORM ROTOR BLADES, John C. Houbolt and George W. Brooks, 1958 TR 1347 DITCHING INVESTIGATIONS OF DYNAMIC MODELS AND EFFECTS OF DESIGN PARAMETERS ON DITCHING CHARACTERISTICS, Lloyd J. Fisher and Edward L. Hoffman, 1958 TR 1349 A LOW-SPEED EXPERIMENTAL INVESTIGATION OF THE EFFECT OF A SAND- PAPER TYPE OF ROUGHNESS ON BOUNDARY-LAYER TRANSITION, Albert E.

yon Doenhoff and Elmer A. Horton, 1958 TR 1351 THEORY OF SELF-EXCITED MECHANICAL OSCILLATIONS OF HELICOPTER ROTORS WITH HINGED BLADES, Robert P. Coleman and Arnold M.

Feingold, 1958 TR 1353 AN EXPERIMENTAL INVESTIGATION OF STING-SUPPORT EFFECTS ON DRAG AND A COMPARISON WITH JET EFFECTS AT TRANSONIC SPEEDS, Maurice S. Cahn, 1958 TR 1355 A THEORETICAL AND EXPERIMENTAL STUDY OF PLANING SURFACES INCLUDING EFFECTS OF CROSS SECTION AND PLAN FORM, Charles L. Shuford, Jr., TR 1356 INVESTIGATION OF SEPARATED FLOWS IN SUPERSONIC AND SUBSONIC STREAMS WITH EMPHASIS ON THE EFFECT OF TRANSITION, Dean R. Chapman, Donald M. Huehn, and Howard K. Larson, 1958 TR 1358 ON FLOW OF ELECTRICALLY CONDUCTING FLUIDS OVER A FLAT PLATE IN THE PRESENCE OF A TRANSVERSE MAGNETIC FIELD, Vernon J. Rossow, 1958 TR 1359 THIN AIRFOIL THEORY BASED ON APPROXIMATE SOLUTION OF THE TRANSONIC FLOW EQUATION, John R. Spreiter and Alberta Y. Alksne, 1958 TR 1361 APPROXIMATE ANALYSIS OF EFFECTS OF LARGE DEFLECTIONS AND INITIAL TWIST ON TORSIONAL STIFFNESS OF A CANTILEVER PLATE SUBJECTED TO THERMAL STRESSES, Richard R. Heldenfels and Louis F. Vosteen, TR THE MECHANISM OF THERMAL-GRADIENT MASS TRANSFER IN THE SODIUM HYDROXIDE -- NICKEL SYSTEM, Charles E. May, 1958 TR 1371 INVESTIGATION OF SOME WAKE VORTEX CHARACTERISTICS OF AN INCLINED OGIVE-CYLINDER BODY AT MACH NUMBER 2, Leland H° Jorgensen and Edward W. Perkins, 1958 TR 1372 A METHOD OF COMPUTIN@ THE TRANSIENT TEMPERATURE OF THICK WALLS FROM ARBITRARY VARIATION OF ADIABATIC-WALL TEMPERATURE AND HEAT- TRANSFER COEFFICIENT, P. R. Hill, 1958 TR 1374 THE SIMILARITY RULES FOR SECOND-ORDER SUBSONIC AND SUPERSONIC FLOW, Milton D. Van Dyke, 1958 TR 1375 A WIND-TUNNEL INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF A FULL-SCALE SUPERSONIC-TYPE THREE-BLADE PROPELLER AT MACH NUMBERS TO 0.96, Albert J. Evans and George Liner, 1958 TR 1376 ELLIPTIC CONES ALONE AND WITH WINGS AT SUPERSONIC SPEEDS, Leland H. Jorgensen, 1958 TR 1377 MEASUREMENTS OF FREE-SPACE OSCILLATING PRESSURES NEAR PROPELLERS AT FLIGHT MACH NUMBERS TO 0.72, Max C. KurbJun and Arthur W.

Vogeley, 1958 TR 1378 A METHOD FOR SIMULATING THE ATMOSPHERIC ENTRY OF LONG-RANGE BALLISTIC MISSILES, A. J. Eggers, Jr., 1958 TR 1379 COMPRESSIBLE LAMINAR BOUNDARY LAYER OVER A YAWED INFINITE CYLINDER WITH HEAT TRANSFER AND ARBITRARY PRANDTL NUMBER, Eli Reshotko and Ivan E. Beckwith, 1958 TR 1380 AN ANALYSIS OF PRESSURE STUDIES AND EXPERIMENTAL AND THEORETICAL DOWNWASH AND SIDEWASH BEHIND FIVE POINTED-TIP WINGS AT SUPERSONIC SPEEDS, William B. Boatright, 1958 TR 1381 A STUDY OF THE MOTION AND AERODYNAMIC HEATING OF BALLISTIC MISSILES ENTERING THE EARTH'S ATMOSPHERE AT HIGH SUPERSONIC SPEEDS, H.

Julian Allen and A. J. Eggers, Jr., 1958 TR 1382 A COMPARATIVE ANALYSIS OF THE PERFORMANCE OF LONG-RANGE HYPER- VELOCITY VEHICLES, Alfred J. Eggers, Jr., H. Julian Allen, and Stanford E. Neice, 1958 TR 1383 SURVEY OF HYDROGEN COMBUSTION PROPERTIES, Isadore L. Drell and Frank E. Belles, 1958 TR 1385 DRAG MINIMIZATION FOR WINGS AND BODIES IN SUPERSONIC FLOW, Max A. Heaslet and Franklyn B. Fuller, 1958 TR 1386 INVESTIGATION OF THE DRAG OF VARIOUS AXIALLY SYMMETRIC NOSE SHAPES OF FINENESS RATIO 3 FOR MACH NUMBERS FROM 1.24 TO 7.4, Edward W. Perkins, Leland H. Jorgensen, and Simon C. Sommer, TR 1387 FULL-SCALE INVESTIGATION OF SEVERAL JET-ENGINE NOISE-REDUCTION NOZZLES, Willard D. Coles and Edmund E. Callaghan, 1958 TR 1389 CHARACTERISTICS OF THELANGLEY 8-FOOT TRANSONIC TUNNEL WITH SLOTTED TESTSECTION, Ray H. Wright, Virgil S. Ritchle, and Albln O. Pearson, 1958 Applicable NASA Technical Report THE THEORY OF INDUCED LIFT AND MINIMUM INDUCED DRAG OF NONPLANAR R 139 LIFTING SYSTEMS, Clarence D. Cone, Jr., 1962 The basic theory of the induced lift and drag of nonplanar, circulation lifting systems is developed, and methods are evolved for determining the span force loading intensity necessary for minimum induced drag. It is shown that the aerodynamic efficiency of such optimally loaded systems can be expressed in terms of an effective aspect ratio which depends in value upon the spatial distribution on the vorticity of the system. Methods for deter- mining the maximum effective aspect ratio of arbitrary lifting systems of given shape by use of conformal transformation and electrical potential-flow analog techniques are developed and illustrated. The value of the induced-drag efficiency factor is determined for the families of circular, semiellipse, and complete- ellipse arcs and for several more complex forms. The results of the theory are interpreted in terms of the physical airfoil re- quirements necessary for successful realization of the theoretical induced-drag reductions. The practical application aspects of nonplanar wing systems are briefly considered. The theoretical developments in this paper are based upon the assumption of in- viscid, incompressible fluid flow so that the results are directly applicable to subsonic flight in air. The paper had as its pri- mary objective, the development of the quantitative theoretical procedures by which the minimum induced drag of arbitrary non- planar lifting systems could be determined subject to the physical restraint imposed by limiting the allowable projected span of the system.

Not Applicable NASA Technical Reports TR R SUPERSONIC FLOW PAST A FAMILY OF BLUNT AXISYMMETRIC BODIES, Milton D. Van Dyke and Helen D. Gordon, 1959 TR R SLENDER-BODY THEORY BASED ON APPROXIMATE SOLUTION OF THE TRANSONIC FLOW EQUATION, John W. Spreiter and Alberta Y. Alksne, 1959 TRR NEARLY CIRCULAR TRANSFER TRAJECTORIES FOR DESCENDING SATELLITES, George M. Low, 1959 TR R STABILITY OF A HORIZONTAL FLUID LAYER WITH UNSTEADY HEATING FROM BELOW AND TIME-DEPENDENT BODY FORCE, Arthur W. Goldstein, 1959 TR R EXPERIMENTAL AND THEORETICAL STUDIES OF AXISYMMETRIC FREE JETS, Eugene S. Love, Carl E. Grigsby, Louise P. Lee and Mildred J.

Woodling, 1959 TR R TURBULENT BOUNDARY LAYER ON A YAWED CONE IN A SUPERSONIC STREAM, Willis H. Braun, 1959 TR R 8 MASS TRANSFER COOLING NEAR THE STAGNATION POINT, Leonard Roberts, TR R 9 A THEORETICAL STUDY OF STAGNATION-POINT ABLATION, Leonard Roberts, TR R i0 STAGNATION-POINT SHIELDING BY MELTING AND VAPORIZATION, Leonard Roberts, 1959 TR R ii AN APPROXIMATE ANALYTICAL METHOD FOR STUDYING ENTRY INTO PLANETARY ATMOSPHERES, Dean R. Chapman, 1959 TR R 14 A METHOD FOR CALCULATION OF HYDRODYNAMIC LIFT FOR SUBMERGED AND PLANING RECTANGULAR LIFTING SURFACES, Kenneth L. Wadlin and Kenneth W. Christopher, 1959 TR R 15 APPROXIMATE ANALYTICAL SOLUTIONS FOR HYPERSONIC FLOW OVER SLENDER POWER LAW BODIES, Harold Mirels, 1959 TR R 16 EFFECTS OF MACH NUMBER AND WALL-TEMPERATURE RATIO ON TURBULENT HEAT TRANSFER AT MACH NUMBERS FROM 3 TO 5, Thorval Tendeland, 1959 TR R 17 ANALYSIS OF TURBULENT FLOW AND HEAT TRANSFER ON A FLAT PLATE AT HIGH MACH NUMBERS WITH VARIABLE FLUID PROPERTIES, R° G. Deissler and A. L. Loeffler, Jr., 1959 TR R 18 SEVERAL METHODS FOR AERODYNAMIC REDUCTION OF STATIC-PRESSURE SENSING ERRORS FOR AIRCRAFT AT SUBSONIC, NEAR-SONIC, AND LOW SUPERSONIC SPEEDS, Virgil S. Ritchie, 1959 TR R 22 BOUNDARY-LAYER DISPLACEMENT EFFECTS IN AIR AT MACH NUMBERS OF 6.8 AND 9.6, Mitchel H. Bertram, 1959 TR R 23 EFFECT OF SURFACE ROUGHNESS ON CHARACTERISTICS OF SPHERICAL SHOCK WAVES, Paul W. Huber and Donald R. McFarland, 1959 TR R 26 SKIN-FRICTION MEASUREMENTS IN INCOMPRESSIBLE FLOW, Donald W. Smith and John H. Walker, 1959 TR R 27 THEORETICAL AND EXPERIMENTAL INVESTIGATION OF HEAT CONDUCTION IN AIR, INCLUDING EFFECTS OF OXYGEN DISSOCIATION, C. Frederick Hansen, Richard A. Early, Frederick E. Alzofon, and Fred C. Witteborn, 1959 TR R 31 ANALYSIS OF TURBULENT FLOW AND HEAT TRANSFER IN NONCIRCULAR PASSAGES, Robert G. Deissler and Maynard F. Taylor, 1959 TR R 32 TABLES OF THE BESSEL-KELVIN FUNCTIONS ber, bei, ker, kei, AND THEIR DERIVATIVES FOR THE ARGUMENT RANGE 0 (0.01) 107.50, Herman H. Lowell, TR R 36 TWO-DIMENSIONAL DIFFUSION THEORY ANALYSIS OF REACTIVITY EFFECTS OF A FUEL-PLATE-REMOVAL EXPERIMENT, Edward R. Gotsky, James P. Cusick, and Donald Bogart, 1959 TR R 37 BOUNDARY-LAYER STABILITY DIAGRAMS FOR ELECTRICALLY CONDUCTING FLUIDS IN THE PRESENCE OF A MAGNETIC FIELD, Vernon J. Rossow, 1959 TR R 38 THE THEORY OF DIFFUSION IN STRAINED SYSTEMS, Louis A. Girifalco and Hubert H. Grimes, 1959 SIMILAR SOLUTIONS FOR THE COMPRESSIBLE BOUNDARY LAYER ON A YAWED TR R 42 CYLINDER WITH TRANSPIRATION COOLING, Ivan E. Beckwith, 1959 EFFECT OF BODY PERTURBATIONS ON HYPERSONIC FLOW OVER SLENDER POWER TR R 45 LAW BODIES, Harold Mirels and Philip R. Thornton, 1959 TR R 46 PRESSURE AND FORCE CHARACTERISTICS OF NONCIRCULAR CYLINDERS AS AFFECTED BY REYNOLDS NUMBER WITH A METHOD INCLUDED FOR DETERMINING THE POTENTIAL FLOW ABOUT ARBITRARY SHAPES, Edward C. Polhamus, Edward W. Geller, and Kalman J. Grunwald, 1959 TR R 47 SECOND-ORDER SLENDER BODY THEORY - AXISYMMETRIC FLOW, Milton D. Van Dyke, 1959 TR R 48 A SYSTEMATIC KERNEL FUNCTION PROCEDURE FOR DETERMINING AERODYNAMIC FORCES ON OSCILLATING OR STEADY FINITE WINGS AT SUBSONIC SPEEDS, Charles E. Watkins, Donald S. Woolston, and Herbert J. Cunningham, APPROXIMATIONS FOR THE THERMODYNAMIC AND TRANSPORT PROPERTIES OF TR R 50 HIGH-TEMPERATURE AIR, C. Frederick Hansen, 1959 TRAJECTORIES WITH CONSTANT TANGENTIAL THRUST IN CENTRAL GRAVITA- TR R 53 TIONAL FIELDS, W. E. Moeckel, 1960 AN ANALYSIS OF THE CORRIDOR AND GUIDANCE REQUIREMENTS FOR SUPER- TR R 55 CIRCULAR ENTRY INTO PLANETARY ATMOSPHERES, Dean R. Chapman, 1960 TR R 56 GRAPHICAL PRESENTATION OF DIFFERENCE SOLUTIONS TRANSIENT RADIAL HEAT CONDUCTION IN HOLLOW CYLINDERS WITH HEAT TRANSFER AT THE INNER RADIUS AND FINITE SLABS WITH HEAT TRANSFER AT ONE BOUNDARY, James E. Hatch, Ralph L. Schacht, Lynn U. Albers, and Paul G.

Saper, 1959 TR R 62 AN ANALYSIS OF ABLATION-SHIELD REQUIREMENTS FOR MANNED REENTRY VEHICLES, Leonard Roberts, 1960 A METHOD OF SOLUTION WITH TABULATED RESULTS FOR THE ATTACHED TR R 63 OBLIQUE SHOCK-WAVE SYSTEM FOR SURFACES AT VARIOUS ANGLES OF ATTACK, SWEEP, AND DIHEDRAL IN AN EQUILIBRIUM REAL GAS INCLUDING THE ATMOSPHERE, Robert L. Trimpi and Robert A. Jones, 1960 TR R 66 A STUDY OF THE ASYMMETRIC TRANSONIC FLOW PAST A SHARP LEADING EDGE, Howard A. Stine, Cleo B. Wagoner, and Alvin L. Lugn, Jr., 1960 THE INTERACTIONS BETWEEN NITROGEN AND OXYGEN MOLECULES, Willard E.

TR R 68 Meador, Jr., 1960 JET-BOUNDARY CORRECTIONS FOR LIFTING ROTORS CENTERED IN RECTANGULAR TR R 71 WIND TUNNELS, Harry H. Heyson, 1960 TR R 72 A SUPERSONIC AREA RULE AND AN APPLICATION TO THE DESIGN OF A WING- BODY COMBINATION WITH HIGH LIFT-DRAG RATIOS, Richard T. Whitcomb and John R. Sevler, Jr., 1960 A STUDY OF THE SIMULATION OF FLOW WITH FREE-STREAM MACH NUMBER i TR R 73 IN A CHOKED WIND TUNNEL, John R. Spreiter, Donald W. Smith, and B. Jeanne Hyett, 1960 CALCULATED EFFECTS OF BODY SHAPE ON THE BOW-SHOCK OVERPRESSURES IN TR R 76 THE FAR FIELD OF BODIES IN SUPERSONIC FLOW, Donald L. Lansing, FLOW IN THE BASE REGION OF AXISYMMETRIC AND TWO-DIMENSIONAL CON- TR R 77 FIGURATIONS, Milton A. Beheim, 1961 TR R 78 ANALYTIC STUDY OF INDUCED PRESSURE ON LONG BODIES OF REVOLUTION WITH VARYING NOSE BLUNTNESS AT HYPERSONIC SPEEDS, Vernon Van Hise, TR R 80 THEEFFECT OF LIFT ONENTRY CORRIDOR DEPTH ANDGUIDANCE REQUIRE- MENTS FORTHERETURN LUNAR FLIGHT, ThomasJ. Wongand Robert E.

Slye, 1961 TR R 81 ALIGNMENT CHARTS FORTRANSPORT PROPERTIES VISCOSITY,THERMAL CONDUCTIVITY, ANDDIFFUSION COEFFICIENTS FORNONPOLAR GASES AND GASMIXTURES AT LOW DENSITY,Richard S. Brokaw, 1961 TRR 82 TURBULENT SKINFRICTION AT HIGHMACH NUMBERS ANDREYNOLDS NUMBERS IN AIR ANDHELIUM,Fred W. Matting, Dean R. Chapman,Jack R.

Nyholm, and Andrew G. Thomas, 1961 TR R 84 ORDINATES ANDTHEORETICAL PRESSURE-DISTRIBUTION DATAFORNACA6- AND6A-SERIES AIRFOIL SECTIONS WITHTHICKNESSES FROM 2 TO 21 AND FROM 2 TO 15 PERCENT CHORD, RESPECTIVELY, Elizabeth W. Patterson and Albert L. Braslow, 1961 TR R 86 THEDRAG COEFFICIENT OF PARABOLIC BODIES OF REVOLUTION OPERATING AT ZERO CAVITATION NUMBER ANDZERO ANGLE OF YAW,Virgil E.

Johnson, Jr. and ThomasA. Rasnick, 1961 TR R 88 THEORETICAL PRESSURE DISTRIBUTIONS ONWINGS OF FINITE SPAN AT ZEROINCIDENCE FOR MACH NUMBERS NEARi, Alberta Y. Alksne and John R. Spreiter, 1961 TRR 89 TRAJECTORY CONTROL FORVEHICLES ENTERING THEEARTH'S ATMOSPHERE AT SMALL FLIGHT-PATH ANGLES, John M. Eggleston and John W. Young, TR R 90 THEORY ANDAPPARATUS FORMEASUREMENT OF EMISSIVITYFORRADIATIVE COOLING OF HYPERSONIC AIRCRAFT WITHDATAFORINCONEL, INCONEL X, STAINLESS STEEL303, ANDTITANIUM ALLOY RS-120, William J.

O'Sullivan, Jr. and William R. Wade, 1961 TR R 92 AN INVESTIGATION OFTHEEFFECT OF HIGHTEMPERATURE ONTHESCHUMANN- RUNGE ULTRAVIOLET ABSORPTION CONTINUUM OFOXYGEN, John S. Evans and Charles J. Schexnayder, Jr., 1961 TR R 93 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OF SUPERCAVlTATING HYDROFOILS OPERATING NEAR THEFREEWATER SURFACE, Virgil E.

Johnson, Jr., 1961 TR R 94 SIMILARITYOF NEAR NOISEFIELDSOF SUBSONIC JETS, Walton L. Howes, TR R 95 SHIELDING OF PARTIALLY REFLECTING STAGNATION SURFACES AGAINST RADIATION BY TRANSPIRATION OF ANABSORBING GAS, John ThomasHowe, TRR 96 ANALYSIS OF MULTIPOINT-MULTITIME CORRELATIONS AND DIFFUSION IN DECAYING HOMOGENEOUS TURBULENCE, Robert G. Deissler, 1961 TR R 99 THEORY OF THE SECULAR VARIATIONS IN THE ORBIT OF A SATELLITE OF AN OBLATE PLANET, William A. Mersman, 1961 TR R I00 COLLECTION OF ZERO-LIFT DRAG DATA ON BODIES OF REVOLUTION FROM FREE-FLIGHT INVESTIGATIONS, William E. Stoney, Jr., 1961 TR R i01 THEORETICAL PREDICTION OF THE EFFECTS OF VORTEX FLOWS ON THE LOADING, FORCES, AND MOMENTS OF SLENDER AIRCRAFT, J. Richard Spahr, 1961 TR R 102 AN ANALYSIS OF ERRORS AND REQUIREMENTS OF AN OPTICAL GUIDANCE TECHNIQUE FOR APPROACHES TO ATMOSPHERIC ENTRY WITH INTERPLANETARY VEHICLES, David P. Harry, III and Alan L. Friedlander, 1961 TR R 104 LOCAL HEAT TRANSFER AND RECOVERY TEMPERATURES ON A YAWED CYLINDER AT A MACH NUMBER OF 4.15 AND HIGH REYNOLDS NUMBERS, Ivan E. Beckwith and James J. Gallagher, 1961 TR R 106 FUNCTIONS FOR ATMOSPHERE ENTRY ANALYSES, Dean R. Chapman and Arline K. Kapphahn, 1961 TR R 107 SIMILARITY SOLUTIONS FOR SMALL CROSS FLOWS IN LAMINAR COMPRESSIBLE BOUNDARY LAYERS, Ivan E. Beckwith, 1961 TR R 108 MEASUREMENTS OF THE DISSOCIATION RATE OF MOLECULAR OXYGEN, Charles J. Schexnayder, Jr. and John S. Evans, 1961 TR R 109 HYPERSONIC VISCOUS SHOCK LAYER OF NONEQUILIBRIUM DISSOCIATING GAS, Paul M. Chung, 1961 TR R 113 A STUDY OF STATISTICAL DATA-ADJUSTMENT AND LOGIC TECHNIQUES AS APPLIED TO THE INTERPLANETARY MIDCOURSE GUIDANCE PROBLEM, Alan L.

Friedlander and David P. Harry, III, 1961 TR R 117 TURBULENT BOUNDARY-LAYER SEPARATION INDUCED BY FLARES ON CYLINDERS AT ZERO ANGLE OF ATTACK, Donald M. Kuehn, 1961 TR R 118 BOUNDARY-LAYER SIMILAR SOLUTIONS AND CORRELATION EQUATIONS FOR LAMINAR HEAT-TRANSFER DISTRIBUTION IN EQUILIBRIUM AIR AT VELOCITIES UP TO 41,100 FEET PER SECOND, Nathaniel B. Cohen, 1961 TR R 119 LINEARIZED SUPERSONIC NONEQUILIBRIUM FLOW PAST AN ARBITRARY BOUNDARY, James J. Der, 1961 TR R 120 THEORETICAL DETERMINATION OF THE FORM OF THE HOLLOW PRODUCED IN THE SOLAR CORPUSCULAR STREAM BY INTERACTION WITH THE MAGNETIC DIPOLE FIELD OF THE EARTH, John R. Spreiter and Benjamin R. Briggs, 1961 TRR 122 PARAMETER STUDY OF INSERTION CONDITIONS FORLUNAR MISSIONS INCLUD- ING VARIOUS TRAJECTORY CONSIDERATIONS, Carl R. Huss, Harold A.

Hamer, and John P. Mayer, 1961 TR R 123 CALCULATIONS OF COMPRESSIBLE AVERAGE TURBULENT SKIN FRICTION, Mitchel H. Bertram, 1962 TR R 124 LINEARIZED THEORY OFWIND-TUNNEL JET-BOUNDARY CORRECTIONS AND GROUND EFFECT FORVTOL-STOL AIRCRAFT, Harry H. Heyson, 1962 TR R 125 JET EFFECTS ONANNULAR BASEPRESSURE ANDTEMPERATURE IN A SUPER- SONICSTREAM, Milton A. Beheim, John L. Klann, and Richard A.

Yeager, 1962 TR R 127 TABLES OF AERODYNAMIC COEFFICIENTS OBTAINED FROM DEVELOPED NEW- TONIAN EXPRESSIONS FORCOMPLETE ANDPARTIAL CONIC ANDSPHERIC BODIES AT COMBINED ANGLES OF ATTACK ANDSIDESLIPWITHSOME COMPARISONS WITHHYPERSONIC EXPERIMENTAL DATA,William R. Wells and William O. Armstrong, 1962 TR R 131 FINALREPORT ONTHETIROSI METEOROLOGICAL SATELLITE SYSTEM, Staffs of Goddard Space Flight Center and U. S. Weather Bureau, TR R 133 A PRELIMINARY THEORETICAL STUDY OFTHEEXPANSION TUBE,A NEW DEVICE FORPRODUCING HIGH-ENTHALPY SHORT-DURATION HYPERSONIC GASFLOWS, Robert L. Trimpi, 1962 TR R 134 AERODYNAMIC EVIDENCE PERTAINING TO THEENTRY OF TEKTITES INTO THEEARTH'S ATMOSPHERE, Dean R. Chapman,HowardK. Larson, and Lewis A. Anderson, 1962 TR R 135 APPLICATION OF STATISTICAL FILTERTHEORY TO THEOPTIMAL ESTIMA- TION OF POSITION ANDVELOCITY ONBOARD A CIRCUMLUNAR VEHICLE, Gerald L. Smith, Stanley F. Schmidt, and Leonard A. McGee,1962 TR R 136 A STUDY OF THEFREE OSCILLATIONS OF THEEARTH,Gordon J. F.

MacDonaldand NormanF. Ness, 1962 TR R 139 THETHEORY OF INDUCED LIFT ANDMINIMUM INDUCED DRAG OFNONPLANAR LIFTING SYSTEMS, Clarence D. Cone, Jr., 1962 TR R 141 ONTHEHEATING OF THEPOLAR UPPER ATMOSPHERE, Kaichi Maeda, 1962 TR R 142 EFFECT OF LARGE-AMPLITUDE OSCILLATIONS ONHEAT TRANSFER, Charles E. Feller and Ernest B. Yeager, 1962 TR R 143 SPECTRUM OF HYDROMAGNETIC WAVES IN THEEXOSPHERE, Gordon J. F.

MacDonald, 1962 TR R 144 THEEVOLUTION OFMASSIVE STARS,PARTIII - HYDROGEN EXHAUSTION THROUGH THEONSET OF CARBON BURNING, C° Hayashl and R. C. Cameron, TR R 146 LAMINAR BOUNDARY-LAYER SEPARATION INDUCED BY FLARES ONCYLINDERS AT ZERO ANGLE OF ATTACK, Donald M. Kuehn, 1962 TR R 147 COMPUTATION OF SATELLITE ORBITS BY THEHANSEN METHOD AS MODIFIED BYMUSEN, HowardT. Phelan, 1962 TR R 148 THECRITICALINCLINATION PROBLEM IN SATELLITE ORBITTHEORY, William A. Mersman,1962 Applicable NACA Wartime Reports WR A-5 EFFECT OF MACH AND REYNOLDS NUMBERS ON THE MAXIMUM LIFT COEFFI- CIENT OBTAINABLE IN GRADUAL AND ABRUPT STALLS OF A PURSUIT AIR- PLANE EQUIPPED WITH A LOW-DRAG WING, John R. Spreiter, George M. Galster and William K. Blair, July 1945 Flight tests were conducted on a pursuit airplane, which has an NACA low-@rag wing, to determine the effects of Mach (M) and Reynolds numbers (RN) on the maximum lift coefficient (CLmax) obtainable in gradual and abrupt stalls. Gradual stalls were made at Mach nunbers from 0.145 to 0.67 and Reynolds numbers from 5.0 x &06 to 19.3 x 106 . Stalls of varying degrees of abruptness were made at selected Mach numbers from 0.195 to 0.44 and Reynolds numbers from 6.37 x 106 to 11.3 x 106 . Com- parisons are made with a pursuit plane having conventional wings.

The following were measured: indicated airspeed, pressure altitude, normal acceleration, and pitching and rolling velo- cities.

In the low Mach number region, the maximum lift coefficient de- creases markedly with increases of altitude but at higher Mach numbers the altitude effect is very small.

_C L For all but two conditions _-M--max _ - 1.75 is caused by a thickening boundary layer which reduces circulation. As R N is increased with contant M the CLmax at first remains nearly constant but as critical R N is reached the CLmax increases rapidly to a higher value and then remains constant again with further increases in Reynolds number. As Mach number increases, the effects of R N on CLmax decreases.

The limiting value of CLmax in abrupt stalls is plotted as a function of M and altitude and is shown to decrease rapidly with increases in M but to be independent of altitude and therefore R N • The CLmax was affected by compressibility at Mach numbers as low as 0.15.

At low M numbers the liftma x of the conventional wing was greater than that of the test plan, but at moderately supercritical Mach numbers the minimum lift of the low drag wing was much greater than that of the conventional wing.

WIND-TUNNEL INVESTIGATION OF AILERONS ONA LOW-DRAG AIRFOIL. III - WR A-18 THEEFFECT OF TABS, Ralph W. Holtzclaw and Robert M. Crane, November1944 Airfoil section lift and momentcoefficients, aileron hinge momentsand tab hinge momentsare measured on a NACA 6612-216 (a = 0.6) airfoil equipped with a 0.20-airfoil-chord plain sealed aileron and a 0.20-aileron chord tab. Two aileron configurations are used, one in which the aileron airfoil contour conforms to the NACA 6612-216 (a = 0.6) airfoil contour and one where the aileron airfoil is straight sided. Data was obtained at Reynolds numbers of from 5,500,000 to 9,000,000 at angles of from - 20° to + 20° and with tab deflections of from - 25° to + 25°. Results are presented in graphical form in 15 sets of graphs. The coeffi- cient derivatives _c_ , etc. are presented in tabular _c_ 6 ' _6 a = _ = 0 _ = _ = 0 a t o t form.

WIND-TUNNEL INVESTIGATION OF AILERONS OF A LOW-DRAG AIRFOIL.

WR A-54 II - THE EFFECT OF THICKENED AND BEVELED TRAILING EDGES, Robert M. Crane and Ralph W. Holtzclaw, January 1944 An investigation was made in the Ames 7- by 10-foot wind tunnel of the effects of modifications to the trailing edge of a 0.20- chord plain sealed aileron on an NACA 6612-216 (a = 0.6) airfoil.

Aileron control characteristics were estimated with normal-profile ailerons and with the modified ailerons. (The modifications con- sisted of various amounts of symmetrical thickening and beveling of the aileron trailing edge.) The following conclusions were drawn: i. Beveling the aileron trailing edge causes a decrease in aileron effectiveness, a decrease in the slope of the wing section lift curve, a decrease in hinge-moment coefficients, and a reduction in the angular range of linear aileron characteristics.

2. The magnitude of these bevel effects decreases with increasing angle of attack.

3. The bevels cause an increase of 0.0001 in minimum profile-drag coefficient.

4. The beveled trailing edge causes a reduction of 50 percent in the high-speed control forces for large rates of roll.

5. Whenused in conjunction with internal nose balance, the trailing-edge bevel results in a 30-percent reduction in the nose balance required for a given control force at high speed.

WR A-55 WIND-TUNNEL INVESTIGATION OFAILERONS ONA LOW-DRAG AIRFOIL.

I - THEEFFECT OF AILERON PROFILE,Robert M. Crane and Ralph W.

Holtzclaw, January 1944 An investigation was madein the Ames 7- by 10-foot wind tunnel of the effects of various modifications to the profile of a 0.20- chord plain sealed aileron and a O.15-chord plain sealed aileron on an NACA 6612-216 airfoil. The results are as follows: i. Thickening of the aileron profile results in a decrease in the aileron effectiveness, a decrease in the slope of the wing section lift curve, and a decrease in the aileron hinge-moment coefficient. Thinning the profile has the opposite effect.

2. The effects of aileron profile are reduced as angle of attack is increased. At an angle of attack of 12°, aileron profile has no effect on the aileron characteristics.

3. Thickening the aileron profile causes an increase of 0.0004 in the minimumsection profile-drag coefficient. Thinning the pro- file had no effect on minimumdrag.

4. Whenthe ailerons of a typical pursuit plane are designed for a given control force for a large rate of roll at high speed, the aileron with thickened profiles have greater stick force for full deflection at low speeds than the normal or thinned profiles.

5. Whendesigned for the samehigh-speed stick force for a large rate of roll, ailerons of 0.20 chord are preferable to ailerons of 0.15 chord of the samespan.

WR A-80 WIND-TUNNEL INVESTIGATION OF THEEFFECTS OF SLOTSHAPE ANDFLAP LOCATION ONTHECHARACTERISTICS OFA LOW-DRAG AIRFOIL EQUIPPED WITH A 0.25-CHORD SLOTTED FLAP, Ralph W. Holtzclaw and Yale Weisman, December1944 An investigation was madeto determine the effects of slot shape and flap location on the characteristics of an NACA 6612-216 (a = 0.6) airfoil equipped with a 0.25 chord slotted flap to pro- vide a basis for the study of drooped ailerons. Two slots were investigated and practical flap paths were selected for each. One slot had a rounded entry; the other had an entry designed to re- duce the gap with the flap retracted to a practical minimum.

The dynamic pressure = 50 psf, R N = 5,100,00 and M = 0.19.

Lift, drag, and pitching-moment measurementswere madethroughout the useful angle-of-attack range for a constant flap deflection and position.

Results i. For a properly located flap, the slot shape had little effect on CLmax.

2. For intermediate lift coefficients with the flap deflected, the round-entry slot had lower profile drag.

3. The addition of a minimum gap slot to the plain airfoil caused an increase in the section profile-drag coefficient of 0.0002 (flap retracted), while the addition of the rounded-entry slot caused an increase of 0.0015.

4. Low drag was obtained for a larger range of CL'S with the minimum-gap slot (flap retracted) than with the rounded entry slot.

5. The pitching moment coefficients were slightly higher with the minimum-gap slot (flap retracted) than with the rounded-entry slot.

WR A-87 TESTS OF NACA 65(216)-420 AND 66(218)-420 AIRFOILS AT HIGH SPEEDS, Joseph L. Anderson, April 1944 The report covers 2 high speed low-drag airfoils. It found the 65-series to have lower drag than the 66-series; the 65-series has a larger low drag range. The 6-series is very sensitive to minute surface variations and has higher critical Mach number.

For both, Von Karman's relation for the rate of increase of pres- sure coefficients with Mach number overestimates critical Mach number. The report has graphs and tables on lift, drag, pitching moment characteristics, critical Mach numbers and pressure distri- butions.

WR A-92 WIND-TUNNEL INVESTIGATION OF THE EFFECTS OF SPOILERS ON THE CHARACTERISTICS OF A LOW-DRAG AIRFOIL EQUIPPED WITH A 0.25-CHORD SLOTTED FLAP, Ralph W. Holtzclaw, July 1945 The report covered an investigation of circular arc spoiler on NACA 6612-216 (a = 0.6) airfoil with 0.25 chord slotted flap.

Spoilers were mounted (i) upper surface at 0.725 chord, (2) lower surface at 0.6666 chord, (3) both I and 2.

The upper surface spoilers were unsatisfactory because: i. It produces rolling moments in wrong direction for small deflections when flap is deflected.

2. Nonlinear variation of effectiveness with deflection.

Sealing the flap slot eliminated reversal but reduced flap effec- tiveness and spoiler effectiveness with flaps deflected. The lower surface spoiler also suffered nonlinear variation of effec- tiveness with deflection. The linkage of lower surface deflection to upper surface deflection improved performance but it was neces- sary to makespoiler deflection nonlinear with control travel.

Vehicle control was satisfactory.

WIND-TUNNEL INVESTIGATION OFAN NACA23021 AIRFOIL WITHA 0.32- WRL AIRFOIL-CHORD DOUBLE SLOTTED FLAP_Jack Fischel and John M.

Riebe_ October 1944 An investigation was madeof an NACA23021 airfoil with a double slotted flap having a chord of 32%of the airfoil chord to deter- mine the aerodynamic section characteristics with the flaps deflected at various positions. The effects of moving the fore flap and rear flap as a unit and of deflecting or removing the lower lip of the slot were also determined. The Reynolds number was about 3.5xi06 for the tests.

The 0.32c double slotted flap on the NACA23021 airfoil gave a CLmax of 3.31_ which was larger than the value obtained with the 0.2566c or 0.40c single slotted flaps and 0.25 less than the value obtained with the 0.40c double slotted flap on the sameairfoil.

The values of the profile-drag coefficient obtained with the 0.32c double slotted flap were larger than those for the 0.2566c or 0.40c single slotted flaps CL between 1.0 and approximately 2.7.

At all values of the C L above 1.0_ the present arrangement had a higher profile drag than the 0.40c double slotted flap.

At a given value of the CLmaxproduced by various flap deflections_ the 0.32c double slotted flap gave negative section pitching- momentcoefficients that were higher than those of other slotted flaps on the sameairfoil.

The 0.32c double slotted flap gave approximately the sameCLmax as_ but higher profile-drag coefficient over the entire lift than_ a similar arrangement of a 0.30c double slotted flap on an NACA23012 airfoil.

Moving the flaps slightly from their optimumpositions sometimes proved critical and resulted in a large increase in drag and a reduction in lift. The position of the fore flap appears to be more critical than that of the rear flap.

Deflecting the lower lip of the airfoil 19° upward generally de- creased the CL and increased the profile C D over most of the angle-of-attack range; removing the lip at the extended fore-flap position reduced the profile drag slightly in the lower-lift range but was slightly unfavorable at high C L.

AERODYNAMIC TESTS OF A FULL SCALE TBF-I AILERON INSTALLATION IN WRL 31 THELANGLEY 16-FOOT HIGH-SPEED TUNNELj John V. Becker and Peter F. Korycinski_ December1944 This report was specifically for the TBF airplane and was about the failure of its wing panels from changes in aerodynamics of the ailerons at high speed.

The hinge-moment coefficients varied only slightly with airspeed in spite of large fabric deflections that occurred at high speeds for the large aileron angles.

Aerodynamic buffeting due to separation of the airflow from the lower surface of the aileron occurred at up aileron angles of -I0 ° or greater. The peak stresses set up in the aileron control linkages because of buffeting were as high as three times the meanstress indicated by conventional hinge-momentbalance meas- urements. This buffeting condition appeared to be the only aerodynamic characteristic that could possibly result in struc- tural failures at high speeds.

The hinge-moment coefficients were appreciably affected by lower- ing the aileron and hinge line 1/4 inch below their normal posi- tions.

An analysis of the hinge-moment data showedthat the resultant control momentof similar ailerons installed in the airplane would tend to restore the ailerons to their neutral position for all the test conditions.

Calculations showedthat elastic instability of the aileron control system resulting in snatch of the upgoing aileron would not occur at indicated airspeeds below 500 mph for an aileron with the characteristics measuredin the present tests. Wing-aileron flutter involving wing deflection components (both normal and parallel to the chord line) occurred in these tests when the principal natural vibration frequencies of the wing (both normal- to-the-chord componentand chordwise component)were of approxi- mately the samemagnitude as the natural bending frequency of the aileron system. The flutter condition was eliminated in the tests either by stiffening the aileron system until its natural bending frequency was at least 1.4 times the principal normal-to- the-chord wing bending frequency (the frequency ratio measured on a TBF-I airplane was approximately 1.4) or by greatly stiffening the wing mounting in the chordwise plane.

An analysis of the flutter motion as determined from photographs taken at intervals of 1/64 second indicated that the flutter con- dition could also have been eliminated by mass-balancing the aileron in the normal-to-the-chord plane. The center of gravity of the aileron as tested was 2.17 inches above the hinge line.

WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS OF WRL 41 PLAINANDBALANCED FLAPSONAN NACA 0009 ELLIPTICALSEMISPAN WING_ Vito Tamburello_ Bernard J. Smith_ and H. NormanSilvers_ February A series of force tests were madeon an NACA 0009 elliptical semi- span wing equipped with a flap either 50%of the wing area or 30% of the wing area. The 30%area flap was tested as a plain flap and with 35-percent-flap-chord and 50%-flap-chord elliptical-nose overhangs. Each model was tested with the gap open and sealed through an _ range of + 20° and a flap range of 0° to 30° . The dynamic pressure was 15 psf and an airspeed of 71 mphwas used.

The effective Reynolds numberwas 2.76xi0 6 based on a c = 25.81".

All data was corrected for tare effects and tunnel-wall correc- tions were also applied.

Results I. The slope of the lift curve generally increased at large angles of attack for small flap deflections. This was character- istic of low aspect ratio wings.

2. At large position angles of attack and flap deflections_ both flaps gave about the same maximum lift increment.

3. Sealing the gap generally increased the effectiveness _-_ whereas an elliptical overhang balance tended to decrease the effectiveness with gap sealed and increase it with gap open. The effect of the gap was nevertheless small.

4. The rate of change of hinge-moment coefficient with _ increased positively and the rate of change of hinge-moment coefficient with flap deflection increased negatively when the gap was sealed.

5. Calculated lift-curve slopes were always higher than measured slopes.

WRL46 THE EFFECTS OF ROUGHNESS AT HIGH REYNOLDS NUMBERS ON THE LIFT AND DRAG CHARACTERISTICS OF THREE THICK AIRFOILS_ Frank T. Abbott_ Jr._ and Harold R. Turner_ Jr._ August 1944 The effects of roughness on three 22-percent-thick airfoils were investigated. The Reynolds number range was from about 6x106 to 26xi06 for the airfoils smooth and with roughness strips applied_he surfaces. The tests were made in a wind-tunnel. A correction of about 2% was applied to the data for normal tunnel-wall- construction effects. Different grains of roughness were tested.

The three airfoils tested were an NACA 63(420)-422 airfoil_ an NACA 65(223)-422 (modified) airfoil_ and a 22-percent-thick Davis airfoil.

Results i. The airfoil with roughness strips showed favorable scale effects over the RN range from 6 to 26xi06.

2. At small and moderate lift coefficients_ the drag coeffi- cients for all the sections tested with leading edge rough were nearly the same for the same roughness conditions and Reynolds number.

3. Increasing the size of the roughness grains applied to the leading edge progressively decreased CLmax for the sizes tested_ but the greater part of the drag increment caused by the roughness occurred with the smallest roughness tested.

4. The order in permitting high CL'S to be obtained without ex- cessively high CD'S were: (i) The NACA 63(420)-422 (2) The NACA 65(223)-422 (3) The 22% thick Davis 5. The CLma x of the NACA airfoils tested were not affected to any great extent by roughness strips at 20 or 30% of the chord back of the leading edge.

WRL47 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

XXIII - A 0.25-AIRFOIL-CHORD FLAP WITH TAB HAVING A CHORD TWICE THE FLAP CHORD ON AN NACA 0009 AIRFOIL_ M. Leroy Spearman_ September 1945 Wind tunnel tests were made to determine the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap having a chord 25% of the airfoil chord and a balancing tab having a chord 50% of the airfoil chord so linked that the tab would deflect at a given rate with respect to the flap. Three linkage ratios were tested. The effective Reynolds number was 2.57xi06. The dynamic pressure was 13 psf.

Results i. A flap with a 2.00 cf balancing tab could produce hinge-moment balance with both angle of attack and flap deflection and yet have greater lift effectiveness than a flap of similar size equipped with a 0.20 cf conventional balancing tab linked to give hinge-moment balance with flap deflection only.

2. Deflecting the tab for trim was about 75% as effective as an adjustable stabilizer.

3. Sealing both gaps generally increased the slope of the lift curve as well as the lift effectiveness of the flap.

4. With the tab deflected negatively for trim_ the hinge moments were closely balanced at high positive angles of attack.

WRL56 WIND-TUNNEL INVESTIGATION OF A RECTANGULAR NACA 2212 AIRFOIL WITH SEMISPAN AILERONS ANDWITHNONPERFORATED_ BALANCED DOUBLE SPLIT FLAPSFORUSEASAERODYNAMIC BRAKES_ ThomasA. Toll and Margaret F. Ivey_ April 1945 Tests were madeto determine the applicability of nonperforated_ balanced double split flaps for use as aerodynamic brakes. The effectiveness and the stability of a conventional trailing-edge aileron located immediately behind the flaps were also tested. A rectangular I0- by 6-inch wing model of NACA2212 airfoil section was used for tests. Results were obtained for flat-plate flaps with no wing cut-outs and for flaps having Clark Y sections with cut-outs madein the wing to simulate the space left open by the deflected flaps. The flap deflections_ the chordwise location_ and the gaps between the flaps and the airfoil contour were varied over wide ranges in order to determine optimum configura- tion. An investigation was madeto determine any buffeting ten- dencies of the aileron.

Dynamicpressure = 16.37 psf_ V = 80 mph_ RNeff = 975_000 The jet boundary correction was applied.

Tests were also madeon the model without flaps.

Results i. The effectiveness of a conventional aileron behind balanced double split flaps was generally low but increased as the flaps were movedrearward.

2. The slope of the curve of lift coefficient against angle of attack generally decreased as the flaps were movedrearward and as the flap gaps were increased.

3. An aileron back of a balanced single split flap with a small flap gap may be as effective through a large part of the angle-of- attack range as an aileron on a wing having no flaps.

4. The effectiveness of the aileron on the model having airfoil- section flaps and wing cut-outs was generally slightly higher than the effectiveness of the aileron on the model having flat-plate flaps and no wing cut-outs.

5. From a consideration of lift_ drag_ aileron-effectiveness_ and aileron hinge-momentcharacteristics a satisfactory practical configuration probably could be obtained with balanced double split flaps located at 80%of the wing chord and with flap gaps of 20%of the wing chord.

6. The drag of this model was higher than the drag of an NACA 23012 airfoil with full-span_ 0.20-airfoil-chord_ perforated double split flaps at the samechordwise location.

WRL 60 WIND-TUNNEL INVESTIGATION OF ROUNDED HORNS ANDOF GUARDS ONA HORIZONTAL TAlL SURFACE_ Robert B. Liddell and Vernard E. Lock- wood_ October 1944 An investigation was madeto determine the aerodynamic effects of horn balances with various plan forms and of guards on a hori- zontal tail surface. The tail surface investigated was the Grumman TBF-I airplane.

4 guards were tested with differences in area.

Dynamicpressure = 16.37 psf and also 12.53 psf with V = 80 and 70 mph and RN = 1.97xi06 and 1.72xi06 Jet boundary corrections were applied.

Results I. Rounding the adjacent horn and stabilizer edges had a negligible effect on the aerodynamic characteristics of the tail surface except for that caused by the decrease in horn area moment.

2. A solid horn guard mounted at the end of the stabilizer increased the rate of change of lift with angle of attack and with elevator deflection.

3. The rate of change of hinge moment with angle of attack and with elevator deflection increased negatively as the guard area was increased.

WRL 82 EFFECTS OF REYNOLDS NUMBER AND LEADING EDGE ROUGHNESS ON LIFT AND DRAG CHARACTERISTICS OF THE NACA 653-418 _ a = 1.0 AIRFOIL SECTION_ J. H. Quinn 3 Jr. 3 November 1945 The present investigation was made to determine the effects of the Reynolds number (RN) on the lift and drag characteristics of a NACA 6-series section with roughened leading edge. Tests were made on the NACA 653-4183 a = 1.0 airfoil section over a range of RN from 0.23xi06 to 3.0x106. Lift and drag measurements were made at several RN's in this range with two degrees of roughness applied to the leading edge.

Tests were made both in the low-turbulence tunnel at atmospheric pressure and in the low turbulence pressure tunnel at pressures of 14.7, 30, 45, 63, and 87 psf. The Mach numberwas never greater than 0.2.

Corrections for tunnel-wall interference were applied.

Results I. Roughening the edges generally lowered the CLmax throughout the range of Reynolds numbers.

2. There was a critical Reynolds number_.7xl06 and 0.5xi06 for the 0.0003c and 0.0007c diameters roughening grains) at which the lift-curve slope decreases rapidly and the drag coefficient in- creases sharply depending upon the size of the roughness.

3. At Reynolds number greater than 1.0xl06 the changes in lift- curve slope and drag coefficient were nearly independent of the sizes of roughness used for the two sizes of roughness tested.

4. Large variations in the lift and drag characteristics of the airfoil were found in the range of RN's between 0.23xi06 and i. 0xl06.

WRL 86 FLIGHTINVESTIGATION OF BOUNDARY-LAYER ANDPROFILE-DRAG CHARAC- TERISTICS OF SMOOTH WING SECTIONS OF A P-47D AIRPLANE, J. A.

Zalovcik, October 1945 A flight investigation was madeof boundary-layer and profile- drag characteristics of smoothwing sections of a P-47D airplane.

Measurementswere madeat 3 stations on the wing: (I) On upper surface of left wing in slipstream at 25%semispan.

(2) On upper surface of left wing in slipstream at 63%semispan.

(3) Wakesurveys were madeat 63%semispan on right wing.

The tests were madein straight flight and in turns over a range of conditions in which airplane lift coefficients from 0.15 to 0.68, Reynolds numbers from 7.7xi06 to 19.7xi06, and Mach numbers from 0.25 to 0.69 were obtained.

Results I. Boundary-layer transition at least as far back as 20% was obtained on the upper surface of a section in the slipstream at low lift coefficient.

2. At the highest Mach number attained in the tests, the criti- cal Mach number was exceeded by at least 0.04 with no evidence of compressibility shock losses appearing in the form of in- creased width of the wake or increased profile-drag coefficient.

3. For flight conditions approaching the critical Mach number_ variations in Machnumber as large as 0.17 appeared to have no effect on profile-drag coefficient.

WRL 94 FLIGHTINVESTIGATION OF BOUNDARY-LAYER TRANSITION ANDPROFILE DRAG OFAN EXPERIMENTAL LOW-DRAG WINGINSTALLED ONA FIGHTER-TYPE AIR- PLANE_ J. A. Zalovcik and R. B. Skoog_April 1945 The test plane was the XP-47Fwith a wing airfoil section that varied from an NACA 66(215)-1(16.5) at the plane of symmetry to an NACA67(115)-215 at the tip. Boundary-layer-transition and profile drag measurementswere madeat a section outside the propeller slipstream with smooth and with standard camouflage surfaces and on the upper surface of a section in the propeller slipstream with the surface smoothed.

Tests were madein normal flight at indicated airspeeds ranging from about 150 to 300 mphand in steady turns.

The range of Reynolds number (RN) was from 9x106 to 18x106 and Machnumber range of 0.27 to 0.53.

Transition measurementswere madeon the upper wings as well as wake surveys being taken behind the wing.

Results I. The point of transition on the upper surface moved rearward with decreasing CL to about 50% of the chord and then moved for- ward again with a further decrease in C L.

2. The profile-drag coefficient decreased with decreasing lift- coefficient until a minimum of 0.0045 was obtained at a section C L of about 0.19 and RN = 15.9xi06.

3. No difference in the point of transition on the upper surface or in the profile-drag coefficient was observed when the airplane was flown with normal engine operation and with engine throttled.

Separate results are given for the standardright wing section with camouflage point and normal construction waviness as well as for the specially finished upper surface of the left wing section in the propeller slipstream.

WRL98 FLIGHT INVESTIGATION AT HIGH SPEEDS OF PROFILE DRAG OF WING OF A P-47D AIRPLANE HAVING PRODUCTION SURFACES COVERED WITH CAMOUFLAGE PAINT_ J. A. Zalovcik and F. L. Daum_ March 1946 A flight investigation was made at high speeds to determine the pro- file drag of a P.47D airplane wing having production surfaces covered with camouflage paint. The profile drag of a wing section somewhatoutboard of the flap was determined by meansof wake surveys in tests madeover a range of airplane lift coefficients from 0.06 to 0.69 and airplane Machnumbers from 0.25 to 0.78 and Reynolds numbers (RN) from 8.4xi06 to 23.1xi0 6.

=> i coat of zinc chromate primer Surface Preparation 1 coat of gray surfacer 2 coats of olive-drab camouflage paint Surface roughness measurementswere madeas were surface waviness.

The tests were madein level flight_ dives_ and turns at 20_000 ft and over a range of calibrated airspeeds from 150 to 415 mph.

Results I. A minimum profile-drag coefficient of 0.0097 was attained for airplane CL'S from 0.16 to 0.25 at Mach numbers below 0.67.

2. Below the Mach number at which compressibility shock was evi- dent_ as indicated by a rapid rise in profile drag_ variation in Mach number as much as 0.2 appeared to have no effect on the profile drag coefficient while the RN variatioh was appreciable.

3. Compressibility shock losses were not evident until the critical Mach number was exceeded by at least 0.025.

WRL 105 WIND-TUNNEL TESTS OF A BLUNT-NOSE AILERON WITH BEVELED TRAILING EDGE ON AN NACA 66(215)-216 AIRFOIL WITH SEVERAL MODIFICATIONS OF AILERON NOSE AND ADJACENT AIRFOIL CONTOUR_ J. D. Bird_ February Ailerons having a 0.35-aileron-chord blunt-nose overhang and a 26 ° beveled trailing edge have been tested in two-dimensional flow on an NACA 66(215)-216 airfoil with several modifications of the aileron nose and adjacent airfoil contour. Comparing with cusped_ intervally balanced and blunt-nose ailerons_ it was found that: Making the aileron nose more nearly elliptical decreased the balance of hinge moments at small aileron angles and increased the balance of hinge moments at large aileron angles. The CL'S at large angles were higher than those obtained with the more blunt nose.

Rounding the airfoil contour adjacent to the aileron nose generally increased the balance of hinge moments and_ for small aileron angles_ slightly increased the value of the slope of the curve of CL against aileron angle CLs. The increase in balance was most pronounced for a range of aileron angle of ± i0 °. This modifica- tion gave results similar to those that would be obtained when an aileron nose was made more blunt.

Flaring the airfoil contour in the region adjacent to the aileron nose decreased the balance of hinge momentsfor aileron angles up to approximately J 14° . The value of CL8over a large part of the aileron-angle range was decreased. These results were similar to those that would be obtained when an aileron nose was madeless blunt.

The effects of the airfoil-contour changes were small at large aileron angles.

Unsealing the gap at the aileron nose generally caused the effects resulting from the various modifications of the aileron nose and adjacent airfoil contour to be more pronounced.

The aileron with 0.60-aileron-chord internal balance and cusped trailing edge afforded a greater degree of balance of hinge moments and higher lift at large deflections than the cusped aileron with the 0.35-aileron-chord blunt-nose overhang or the aileron with 26° beveled trailing edge and 0.35-aileron-chord blunt-nose overhang.

Comparisonswith other data indicated that_ for small aileron angles_ the increments of hinge-moment coefficient resulting from a beveled trailing edge _nd a blunt-nose overhang were additive.

WRL 115 FULL-SCALE WIND-TUNNEL INVESTIGATION OFFORWARD UNDERSLUNG COOLING- AIR DUCTS_ W. J. Nelson_ K. R. Czarnecki and Robert D. Harrington_ October 1944 A general investigation of underslung cooling air ducts in various locations on a model of a typical single-engine tractor airplane has been conducted.

Pressure recoveries at the radiator greater than 90%of the free- stream dynamic pressure were obtained at the low lift coefficient of 0.i0_ with the propeller removed_for inlet velocity ratios ranging from 0.40 to 0.75. Beyond the inlet velocity ratio of 0.75 the pressure recoveries decreased rapidly.

The variation of pressure recovery with lift coefficient 3 with the propeller removed_was less than 5%of the free stream dynamic pressure at values of inlet-velocity ratio of 0.5_ for inlet- velocity ratios greater than 0.5 the pressure losses ahead of the radiator increased rapidly with C L. Vanes in the diffuser of the forward underslung duct had little effect on the pressure recovery at low CL'S but reduced the adverse effects of increasing C L.

Operation of the propeller_ equipped with large chord cuffs_ increased the total pressure at the radiator of the large duct approximately 7%of the free-stream dynamic pressure at the high- speed thrust coefficient of 0.02 and approximately 45%of the free-stream dynamic pressure at the climb thrust coefficient of 0.ii. The static pressure at the outlet with no exit flaps in- creased with both the CL and the propeller thrust.

With the propeller removed_the static pressure at the outlet was reduced approximately 50%of the free-stream dynamic pressure by installing 45° exit flaps; the effectiveness of the exit flaps increased considerably with power.

At equal values of the inlet-velocity ratio and pressure-drop coefficient for the orifice plate_ the internal drag of the small duct was somewhathigher in someinstances than that of the larger duct even though the air flow was considerably less. The higher drag was a result of the lower diffuser expansion ratio of the small duct_ which resulted in a higher dynamic pressure within the duct and hence greater pressure losses and a greater pressure drop across the radiator. No comparison was madeof the ducts on the basis of providing equal cooling.

Increases in the inlet-velocity ratio with the propeller removed increased the critical Mach numberof the duct lower lip and duct- fuselage fillets.

Increases in the C L of the airplane with propeller removed in- creased the critical speed of the fillets. Propeller operation had little effect on the critical speed of the lower lip. The critical speed of the left fillet was only slightly decreased by propeller operation; whereas a substantial increase was measured at the right fillet.

WRL 122 APPLICATION OF SPRING TABSTO ELEVATOR CONTROLS_ William H.

Phillips_ October 1944 Problems were investigated which were concerned with the character- istics of a spring-tab type of elevator. The main problems encountered are to provide stick forces in the desired range_ to maintain the force per G sufficiently constant throughout the speed range_ to avoid undesirable "feel" of the control in ground handling_ and to prevent flutter. The following conclusions were reached in this investigation: I. By use of spring tabs_ satisfactory elevator control-force characteristics may be obtained over a large center of gravity range on airplanes varying in weight from about 16_000to at least 300_000pounds.

2. The spring tab offers the possibility of greatly reducing the changes in stick forces that result from small variations in contours of the elevators on different airplanes of the sametype.

3. The elevator control-force characteristics resulting from the use of a spring tab should be more closely predictable than those with other types of aerodynamic balance_ in order to take advan- tage of this effect more complete information on the hinge-moment characteristics of tabs will be required.

4. Oneof the chief objectives to the use of spring tabs is the amountof weight required for mass balance to prevent flutter.

The change in elevator hinge momentcaused by any change in angle of attack_ elevator angle_ or tab angle is given by: _C H _C H _C H e 2 e e (i) H e = (_T _T + A6 e 6_--e + A6 t _-_t-) qTbeCe where: _T = angle of attack of tail CHe = hinge moment coefficient of elevator 6e : elevator deflection 6 t = tab deflection qT = dynamic pressure at tail b e = span of elevator c = chord of elevator e T = tail subscripts • t = tab e : elevator The corresponding change in tab hinge moment is DCh t DCh t DCht 2 (2) -- + A6 t _-Tt_) qTbTCt AHt : (A_T _T + A6e _6e The relationship between the stick force; F; the elevator hinge moment_ and the tab hinge moment_ when the spring tab system is in equilibrium is given by: AH t + A5 + K2K 3 (3) AF : K 2 K I and K 2 are the gearing ratios between the stick and elevator and between the stick and tab.

K 3 is defined by F = K36t where F is the stick force required at zero airspeed to deflect the tab with the elevator fixed.

By simultaneous solutions of equations (i)_ (2)_ and (3) the stick force required in any maneuver for an elevator equipped with an unpreloaded spring tab may be obtained.

SCALE-EFFECT TESTS IN A TURBULENT TUNNEL OF THENACA653-418_ WRL 128 a = 1.0 AIRFOIL SECTION WITH0.20-AIRFOIL-CHORD SPLIT FLAP, Warren A. Tucker and Arthur R. Wallac% September1944 Scale-effects tests of the NACA 653-418_ a = 1.0 airfoil section with a split flap having a chord 20%of the airfoil chord were made. The Reynolds numbers ranged from 0.19x106 to 2.99xi06_ the Machnumber attained was never greater than 0.i0.

The CLmax increased with Reynolds number. Deflecting the flap added an increment of CLmaxthat seemedto be almost constant at all Reynolds numbers.

The slope of the section lift curve with flap deflected showedno consistent variation with Reynolds number_although the slope of the section lift curve for the plain airfoil increased up to a Reynolds number of about 1.0xl06 and then remained nearly constant up to a Reynolds numberof about 3.0xI06_ the limit of the tests.

For flap deflections above 15_ the slope of the section lift curve decreased with an increase in flap deflection.

The section profile-drag coefficient with flap deflected remained almost constant with Reynolds number_although the section profile- drag coefficient for the plain airfoil decreased up to a Reynolds number of about 0.8xi06 and then remained nearly constant to a Reynolds number of about 3.0x106.

The slope of the pitching momentcoefficient curve of the plain airfoil becameslightly more negative with an increase in Reynolds number. The pitching-moment-coefficient slope for the airfoil with flap deflected varied with CL in such a way that presentation of the slopes was not practical.

WIND-TUNNEL INVESTIGATION OF ANNACA66-SERIES16-PERCENT-THICK WRL 134 LOW-DRAG TAPERED WING WITHFOWLER ANDSPLITFLAPS_ Robert H.

Neely and Gerald V. Foster_ January 1946 Tests of an NACA 66-series 16%-thick low-drag tapered wing of 12-foot span with .30-chord Fowler and 0.20_chord split flaps led to these conclusions: The CLmax'Sobtained with full-span and partial span Fowler flaps were 3.27 and 2.49 at an Re = 3.5xi06. For the sameconditions_ the CLmax'Sobtained with split flaps were 2.43 and 2.07. The values of CLmaxfor the wing with split flaps were somewhatlower (approximately 5%) than the values obtained for comparable wings with conventional airfoil sections.

Trimming the large pitching momentsdue to flaps would appreciably reduce the maximum lift available_ particularly for the Fowler flaps.

For all configurations investigated_ the wing stalled suddenly_ and in most cases completely_ for a very small increase in angle of attack beyond maximum lift. With flaps retracted or with partial span split flaps_ there was someindication of the approaching wing stall_ but with partial-span or full-span Fowler flaps there was no such indication.

WRL 138 SCALE ANDTURBULENCE EFFECTS ONTHELIFT ANDDRAG CHARACTERISTICS OFTHENACA 653_418 _ a = 1.0 AIRFOIL SECTION# John H. Quinn# Jr._ and Warren A. Tucker_ August 1944 An investigation in two NACA wind tunnels has determined the effect of Reynolds numberand stream turbulence on the lift and drag characteristics of a low-drag airfoil-NACA 653_418 _ a = 1.0.

Large increases in minimumdrag coefficient were found as the Reynolds number decreased particularly at Reynolds numbers below 1.5x106. At Reynolds numbersbelow 1.5xi06_ stream turbulence had little effect on the drag characteristics_ but at high Reynolds numbersstream turbulence had a detrimental effect on drag.

Large decreases in maximum lift coefficient were found with de- creasing Reynolds number; most of this decrease was encountered at Reynolds numbers above 2.0x106.

Considerable variation of lift-curve slope with Reynolds number was found. Results at high and low turbulence differed as muchas 6 percent but yielded the samevalue of lift-curve slope at a Reynolds number = 4.0x106. At Reynolds numbers higher than this value_ no scale effect on the lift-curve slope was observed over the range tested.

WRL 139 PROFILE-DRAG COEFFICIENTS OF CONVENTIONAL ANDLOW-DRAG AIRFOILSAS OBTAINED IN FLIGHT_John A. Zalovcik_ May 1944 The results of flight investigations of the profile drag of several carefully finished conventional and low-drag6airfoils were pre- sented. Reynolds numbersranged from 7.4xi0 all the way up to 31xlO6. The results (for the airfoils: NACA27-2125 NACA35-215; NACA 66_2-2(14.7); NACA 64_2-(1.4)(13.5); NACA2414.57 N-22_ Republic S-3_II_ Republic S-3_13) indicated that in all cases lower profile-drag coefficients were obtained with the low-drag airfoils than with the conventional airfoils over the range of lift coefficient tested and that_ for comparable conditions of lift coefficient and Reynolds number_ the low-drag airfoils may have profile-drag coefficients which are at least 27% lower than the profile-drag coefficients of the conventional airfoils.

WRL 140 WIND-TUNNEL INVESTIGATION OF NACA 66(215)-216_ 66_i-212_ AND 651-212 AIRFOILS WITH 0.20-AIRFOIL-CHORD SPLIT FLAPSj Felicien F. Fullmer_ Jr._ July 1944 This was a report of lift coefficients of three different airfoil sections with and without flaps. Results are available in any book of airfoil tables.

WRL 145 SUMMARY OF MEASUREMENTS IN LANGLEY FULL-SCALE TUNNEL OF MAXIMUM LIFT COEFFICIENTS AND STALLING CHARACTERISTICS OF AIRPLANES_ Harold H. Sweberg and Richard C. Dingeldein_ April 1945 The results of measurements of CLmax and stalling characteristics of some different airplanes were collected.

Wings having high taper ratios and large amounts of sweepback have been shown to be subject to poor stalling characteristics because they are susceptible to tip stalling. The proper com- binations of washout and changes in camber and wing thickness from root to tip with taper will usually produce satisfactory stalls on wings subject to tip stalling.

The addition of fuselages and nacelles to wings frequently in- troduces centers of local separation and may reduce the maximum CL if the wing-fuselage or wing-nacelles junctures are not adequately faired.

Deflection of the landing flaps generally tended to "clean up" the inboard sections of a wing and increased the upwash over the outer unflapped portions of the wing.

Propeller operation will generally increase the severity of the stall_ especially on single-engine airplanes_ by producing an asymmetrical stall pattern and by cleaning up the inboard sec- tions of the wings.

The CLmax of an airplane may be appreciably increased by the elimination of wing surface roughness and air leakage through the wings.

Wing-duct inlets with well-cambered upper lips properly aligned with the flow at the leading-edge of the wing will generally cause no reduction in the CLmaxof an airplane; whereas substan- tial decreases in the CLmax of an airplane may be caused by ducts with the inlet plane perpendicular to the chord line and by inlet lips with small leading-edge radii.

The increments of C L contributed by split flaps could be computed with sufficient accuracy by the use of two-dimensional test data; for slotted flaps_ however_ the measured increments of C L were_ on the average_ about 20%lower than those calculated from the available two-dimensional test data. These low values for the slotted flaps are attributed_ mainly_ to difficulties encountered by manufacturers in producing slot shapes of efficient aerodynamic design.

In a single instance where great care was taken to reproduce the test conditions of Reynolds number_propeller operation_ and the time rate of change of angle of attack_ satisfactory agreement Is of the CLmax determined from full-scale-tunnel and flight tests were obtained.

WRL 151 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF 0.20-AIRFOIL-CHORD PLAIN AILERONS OF DIFFERENT CONTOUR ON AN NACA 651-210 AIRFOIL SECTION_ William J. Underwood_ Albert L. Braslow_ and Jones F.

Cahill_ December 1945 A two-dimensional wind-tunnel investigation was made of an NACA 651-210 airfoil equipped with three interchangeable sealed-gap 0.20-airfoil-chord plain ailerons of different contour. The air- foil was tested with smooth surfaces and with standard leading edge roughness. Changing the aileron contour by thickening or beveling the trailing edge would cause: I. The aileron effectiveness parameter to decrease.

2. The rate of change of aileron section hinge-moment coefficient with both section angle of attack and aileron deflection to in- crease positively.

3. The rate of change of section lift coefficient with section angle of attack to decrease.

4. The maximum section lift coefficient to decrease.

5. The aerodynamic center to shift forward.

6. The increment of section pitching-moment coefficient induced by aileron deflection at constant lift to remain the same.

7. The section profile drag coefficient with the aileron neutral to remain substantially unaffected throughout the section angle- of-attack range.

The application of roughness to the leading edge would accentuate the balancing action of the aileron and the loss in aileron effectiveness caused by beveling the aileron trailing edge.

The effect of aileron contour on the hinge momentsof sealed internally balanced ailerons_ as computed from data on the hinge- momentand seal-pressure-difference coefficients of plain ailer- ons_ showedan appreciable effect of aileron contour on the hinge momentsat large aileron deflections even though all three ailerons were computed to have the samehinge-moment slope at small deflections.

WRL 156 AERODYNAMIC CHARACTERISTICS OF THENACA747A315AND747A415 AIRFOILSFROM TESTSIN THENACA TWO-DIMENSIONAL LOW-TURBULENCE PRESSURE TUNNEL_ Albert E. von Doenhoff and Louis S. Stivers_ Jr._ September1944 Data is presented which is contained in airfoil section manuals.

WRL 171 ANALYSIS OFAVAILABLE DATAONTHEEFFECTIVENESS OFAILERONS WITHOUT EXPOSED OVERHANG BALANCE_ Robert S. Swansonand Stewart M. Crandall_ May 1944 The trends indicated by the analysis of available data on the effectiveness of ailerons without exposed overhang balance have been sun_narizedin the form of a few approximate rules concerning the effectiveness of flap parameter (at constant lift): Thickening and beveling the trailing edge (as measured by the trailing edge angle 9) will generally reduce the effectiveness about 0.3% per degree of bevel for ailerons sealed at the hinge axis and about 0.6% per degree of bevel for unsealed ailerons.

A 0.005c gap at the hinge axis usually reduced the effectiveness about 17%for flap chord ratios of 0.2. This percentage in- creased as the flap chord ratio is reduced. The effectiveness was about 14%lower at aileron deflections of 20° than at aileron deflections of I0o. At large angles of attack (_ = I0o) and for chord ratios of about 0.2_ positively deflected ailerons were about 20%less effective than negatively deflected ailerons. The deflection of partial-span flaps had no consistent effect on the effectiveness. Increases in Mach number and forward movementof the transition point decreased the aileron effectiveness.

WRL 172 EFFECT OF LEAKAGE PASTAILERON NOSE ONAERODYNAMIC CHARACTERISTICS OFPLAIN ANDINTERNALLY BALANCED AILERONS ONNACA 66(215)-216_ a = 1.0 AIRFOIL_J. D. Bird_ July 1945 The effect of leakage past the aileron nose on the aerodynamic characteristics of plain and internally balanced ailerons on an NACA66(215)-216_ a = 1.0 airfoil was investigated in 2-D flow.

From the results of this investigation_ it was found that: A small amount of leakage area changed the pressure distribution over the plain and internally balanced ailerons markedly. This change generally resulted in negative increments in the lift and hinge-moment parameters. A further increase in the leakage area produced smaller changes in these parameters for the internally balanced aileron.

The sensitivity of the internally balanced aileron tested to small amounts of leakage area would makeclose aileron balance difficult without use of a complete nose seal.

The hinge-moment characteristics of the internally balanced aileron with leakage past the balance plate generally were not changedradically by the changing leakage area from a narrow slit spanning the aileron at the balance plate nose to a rectangu- lar hole of about the samearea located at the model midspan.

Reducing the amount of leakage area and vent area so as to hold constant the ratio of leakage area to vent area increased the degree of hinge-momentbalance at large aileron angles but caused no appreciable change in the degree of balance at small aileron angles.

The sealed and unsealed internally balanced ailerons had almost the samevariation of aileron deflection hinge-moment coefficient with Machnumber and Reynolds number.

WRL 175 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

XXI - MEDIUM ANDLARGE AERODYNAMIC BALANCES OF TWO NOSE SHAPES AND A PLAIN OVERHANG USED WITHA 0.40-AIRFOIL-CHORD FLAPONAN NACA 0009 AIRFOIL_John M. Riebe and Oleta Church_ March 1945 The results of tests of an NACA 0009 airfoil with a 40%-chord flap having various arrangements of overhang and nose shape indicated that: The slope of the lift-coefficient curve was approximately the samefor all sealed gap-conditions regardless of aerodynamic- balance shape or length_ except for the elliptical-nose overhang with a 50%-flap chord for which the slope was about 3%larger than the average. Unsealing the gap reduced the slope 4%for the flap with plain overhang and 13 to 17%for the flap with aerodynamic balances.

The change in lift with flap deflection increased with sealing of the flap gap and with changing of the nose shape from elliptical to blunt.

Unsealing the flap gap (except for the plain flap)_ increasing the balance length_ and changing the nose shape from elliptical to blunt madethe rate of change of flap hinge momentwith flap deflection (at small flap deflections) and with angle of attack more positive (or less negative).

With gap either sealed or unsealed_ someoverbalance was found on the 50%-chordblunt-nose overhang.

Whenthe lift was varied by changing the angle of attack at zero flap deflection_ the center of lift was at the 24%-chord-station for all overhangs tested with gap sealed.

The center of lift due to flap deflection and that due to angle of attack generally movedrearward as the gap was unsealed.

WRL 178 WIND-TUNNEL INVESTIGATION OF AILERON EFFECTIVENESS OF0.20-AIRFOIL- CHORD PLAINAILERONS OF TRUE AIRFOIL CONTOUR ONNACA652-415_ 653-418 AND654-421 AIRFOIL SECTIONS_ Albert L. Braslow_ August The aileron effectiveness parameter (change in section angle of attack with aileron deflection at constant lift coefficient) decreased very slightly with an increase in airfoil thickness from 15%to 21%for the NACA652-415_ 653-418_ and 654-421 airfoil sections. At higher deflections of the 0.20-airfoil-chord ailer- ons and higher section angles of attack_ the increment of section lift coefficient due to aileron deflection was more appreciably reduced with an increase of airfoil thickness than was the aileron effectiveness parameter. The slope of the airfoil section lift curve CLwas substantially the samefor the three airfoils tested.

WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS. XX - WRL 186 PLAIN ANDBALANCED FLAPS ONAN NACA 0009 RECTANGULAR SEMISPAN TAlL SURFACE_ I. Elizabeth Garner_ October 1944 Force-test measurementshave been madein the Langley 4- by 6_ foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 semispan tail surface of rectangular plan form equipped with flaps of various nose shapes and overhangs. The flap chord was 30 percent of the airfoil chord. A few tests were made to determine the effectiveness of a balancing tab on various flap arrangements.

dynamic pressure = 15 psf_ V = 76 mph_ effective RN = 2_760_000 jet boundary corrections were applied no gap corrections were applied no tunnel wall corrections applied The 0.35cf and 0.50cf overhangs were tested with blunt and ellip- tical nose shapes.

A linked balancing tab constructed of brass and having a gap of 0.001c was tested on the plain sealed flap and on the flap with 0.35cf elliptical overhang with open gap. The tab had a chord of 0.20 cf where cf = chord of the flap.

Results Sealing the gap at the flap nose increased the slope of the lift curve_ but the balance nose shape and the amount of overhang had little effect on the slope. The effectiveness of the flap was greatest for the unsealed blunt-nose overhangs_ but stalls occurred at lower flap deflections.

The 50_percent-flap-chord overhang was over-balanced over a part of the flap deflection range regardless of the nose shape and the gap at the flap nose.

At large flap deflections for positive angles of attack_ the drag coefficients generally increased with an increase in overhang and were higher for the blunt nose than for the elliptical nose_ at large flap deflections_ the elliptical nose gave more lift than the blunt nose with approximately the same amount of drag.

The calculations developed in 2-dimensional flow were slightly higher for the lift-curve slope and were more negative for hinge moment parameters than were the test results found in actual 3- dimensional flow.

WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

WRL 196 XXII - MEDIUM AND LARGE AERODYNAMIC BALANCES OF TWO NOSE SHAPES AND A PLAIN OVERHANG USED WITH A 0.20-AIRFOIL-CHORD FLAP ON AN NACA 0009 AIRFOIL_ John M. Riebe and Elizabeth G. McKinney_ June Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord were tested in two_dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an elliptical over- hang of 0.35 flap chord. The pressure difference across the flap seal was also determined for the plain sealed flap.

dynamic pressure = 14 psf_ RNef f = 2.76xI06_ Mach no. = 0. I0 An experimentally determined tunnel correction was applied to the CL.

Results I. The slope of the lift curve was largest for the plain sealed flap_ whereas the slopes for the 0.5cf overhangs were equal to or slightly larger than for the 0.35cf overhang.

2. The variation of C L with flap deflection generally increased when the gap was sealed and when the nose was changed from ellip- tical to blunt.

3. Sealing the gap made variation of flap hinge-moment coefficient with angle of attack more negative. Changing the nose shape from blunt to elliptical made this variation more negative for the sealed gap and more positive for unsealed gap.

4. The tab was slightly more effective in changing the lift and the flap hinge moment on the plain flap than on the flap with 0.35cf elliptical-nose overhang.

WR L 209 TESTS OF THE NACA 653-018 AIRFOIL SECTION WITH BOUNDARY-LAYER CONTROL BY SUCTION_ John H. Quinn_ Jr._ October 1944 An NACA 653-018 airfoil section equipped with slots for boundary layer control was tested in the Langley two-dimensional low turbulence tunnel at Reynolds numbers up to 6.0xlO 6. Slots were tested at 30% and 75% and at 45% and 75% of the chord. Approxi- mately twice as much air was removed through the rear slot as through the forward slot.

A CLmax of 1.85 was obtained at a Reynolds number = 6x106 with section using boundary layer control (BLC). This CL was obtained with suction slots at 45% and 75% of the chord. The low-drag characteristics of this airfoil section could be realized with this arrangement when the slots were not operating by covering them with flush doors. The total amount of air removed at this CL corresponded to flow having free-stream velocity through an area equal to approximately 1.2% of the wing area.

For maximum effectiveness_ the amount of air to be removed per unit span through each slot was approximately equal to the amount that would pass through the displacement boundary-layer thickness first ahead of the slot with a velocity equal to the local velocity just outside the boundary layer at that point.

The CLmax for the airfoil with the slots tested was attained at approximately the same angle of attack as for the plain airfoil.

Little or no scale effect on maximum lift with boundary layer condition at the highest flow rate was found for the test Reynolds number range.

The present results indicated that farther increases in maximum lift for this particular airfoil would depend on the prevention of separation near the leading edge. This separation might be prevented by a suction slot placed near the leading edge_ although further investigation is required to develop a slot design that permits the low-drag properties of this airfoil to be realized.

WRL 212 EXPERIMENTAL VERIFICATION OF A SIMPLIFIEDVEE-TAILTHEORY AND ANALYSIS OF AVAILABLE DATA ONCOMPLETE MODELS WITHVEETAILS_ Paul E. Purser and John P. Campbell_ January 1945 An analysis was madeof available data on vee-tail surfaces.

Methods for designing vee-tails were also given in the report.

The following results were observed: I. The use of vee-tails will probably provide no reduction in area unless the conventional vertical tail is in a bad canopy wake_ unless the usually higher location of the vee-tail places it in a region of greatly reduced downwash_ or unless the vee tail has a higher effective aspect ratio than the conventional horizontal and vertical tails.

2. A possible reduction in control forces was indicated by use of vee-tails_ provided that large deflections of the control surfaces do not cause a large decrease in the effectiveness and increase in hinge-moment coefficient per degree deflection of the control surface.

3. The following advantages can be obtained with the use of a vee-tail: (a) Less drag.

(b) Less tendency toward rudder lock.

(c) Higher location of tail surfaces_ which tends to reduce elevator deflection required for take-off and landing_ to keep the tail out of spray in flying boat take-off_ and to reduce possibilities of tail buffeting from the wing and canopy wakes in high-speed flight.

(d) Fewer tail surfaces to manufacture.

.

The following disadvantages were noted: (a) Possible interaction of elevator and rudder control forces.

(b) Possible interactions of elevator and rudder trimming when tabs are at fairly large deflections.

(c) More complicated operating mechanism.

(d) Greater loads on tail and fuselage_ which would tend to require increased weight.

5. Indications are that the vee-tail should be as good or better in regard to spin-recovery as the conventional tail.

WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

WRL 215 XIX - A DOUBLE FLAPWITHAN OVERHANG ANDAN INTERNAL AERODYNAMIC BALANCE_ Robert B. Liddell_ June 1944 Wind-tunnel tests have been made in two-dimensional flow to in- vestigate the aerodynamic characteristics of a double flap with an internal balance and an overhang balance.

The balanced double flap produced lifts about equal to a single plain flap of the samechord and at the sametime produced closely balanced hinge moments.

High lifts and low hinge momentswere obtained with a double flap arrangement if either an overhang or an internal balance having a chord 50%of the flap chord was incorporated on the forward flap.

The data also indicated that the forward and rearward flaps should deflect at about the samerelative rate.

The relative rate of deflection of the two flaps had a large effect on the hinge momentdue to flap deflection and a small effect on the hinge momentdue to angle of attack.

The flap having an overhang balance showeda lower value of the hinge momentgradient due to flap deflection than the internally balanced flap.

The rapid change in hinge-moment coefficient at large flap deflec- tions and angles of attack of opposite sign may cause reversal of control surface force_ however_ a relatively small force should be required to return the control surface to neutral.

A double flap arrangement incorporating an aerodynamic balance is a very promising arrangement. Inasmuchas this double flap is merely a large leading tab_ its incorporation on the tail of an airplane should not present any particularly difficult problem.

There are not enough data available to determine the optimum chord for a large leading tab.

WRL 228 WIND-TUNNEL INVESTIGATION OF A PLAINAILERON WITHVARIOUS TRAILING- EDGE MODIFICATIONS ONA TAPERED WING. II - AILERONS WITHTHICKENED ANDBEVELED TRAILINGEDGES_ F. M. Rogallo and Paul E. Purser_ October 1942 An investigation was madein the Langley 7- by 10-foot tunnel of various modifications to the trailing edge of a 0.155-chord plain aileron on a semispan model of the tapered wing of a fighter air- plane. The modifications considered were various amounts of thickening and beveling of the aileron trailing edge to reduce stick force.

The results of the tests indicated that the use of beveled ailerons would reduce the high-speed stick forces to 60 percent or less of those experienced in the use of plain sealed ailerons and would tend to increase the effective dihedral and the damping in roll with the stick free. The use of small amounts of thick- ening and beveling of the trailing edge also was found to be use- ful to supplement the action of other types of balance in a final adjustment of stick forces. The ill effects of a gap at the aileron nose increased as the thickness of the beveled aileron was increased and as the chord of the bevel was decreased.

WRL 229 HIGH-SPEED TESTS OF RADIAL-ENGINE NACELLES ONA THICKLOW-DRAG WING_ John V. Becker_ May 1942 Tests were madeto determine the drag characteristics of several conventional types of radial-engine nacelle on a low drag airfoil.

The minimumdrags of conventional nacelles of various types and sizes installed on a 20.7%-thick low-drag wing were of the same order of magnitude as the minimumnacelle drags obtained in a previous investigation employing an 18%-thick conventional thick low-drag wing.

The estimated effect of the disturbance of the laminar boundary layer on the wing by the slipstream of a tractor propeller is to increase the nacelle drag from 12%to 21%_depending on nacelle size.

The drag coefficients of nacelles that were unsatisfactory at low speeds increased very rapidly with increasing Machnumber. For the best arrangements tested_ no serious increases occurred up to Machnumber = 0.55.

Decreases in nacelle size resulted in large reductions of drag both through reduced frontal area and through decreased interference effects.

Nacelles in the low position with the top of the nacelle flush with the upper surface of the wing had about the samedrag as the nacelles whose center lines passed through the trailing-edge_ provided that the low afterbody was extended far enough beyond the trailing edge to prevent flow separation.

Low nacelles appeared to present less of a problem than central nacelles in designing for a high critical Machnumber at the wing- nacelle juncture because only the relatively low local velocities on the under surface of the wing were augmentedby the afterbody.

With either the low or the central location it appears that the critical Mach numberat the juncture can be madeto exceed that of the wing alone by the proper shaping of the nacelle afterbody.

The effect of air outlet through efficient openings resulted in reduced external drag in several cases. This effect was large enough to warrant further investigation.

DEVELOPMENT OF COWLING FORLONG-NOSE AIR-COOLED ENGINE IN THENACA WRL 241 FULL-SCALE WINDTUNNEL_ Abe Silverstein and EugeneR. Guryansky_ October 1941 An investigation of cowlings for long-nose radial engines was made on the Curtiss XP-42 airplane in the wind-tunnel. The XP-42 air- plane is provided with a Pratt and Whitney R-1830-31 engine_ which has a propeller shaft and bearing housing that is 20 inches longer than the standard short-nose engine of the sameseries.

The wind-tunnel program included an initial investigation of the original P-42 cowling_ which was followed by tests of several modified arrangements with improved scoops. The general un- satisfactory aerodynamic characteristics of all the cowlings with scoop inlets led to the development of the annular high-velocity inlet cowling.

The long.nose engine enables the design of an efficient annular inlet cowling owing to the length available for a diffusing passage. The ratio of the cooling-air velocity at the cowling inlet to the stream velocity is one of the most important design variables for the annular inlet cowling and this ratio should not be less than about 0.5. The critical compressibility speed for the long-nose engine cowling can be extended to above 500 miles per hour at 20_000 feet altitude. Important drag losses occur due to the flow of cooling air out of conventional cowling outlets with flap gear and exhaust collectors to disturb the flow.

WRL 242 A FLIGHTINVESTIGATION OF INTERNALLY BALANCED SEALED AILERONS IN THEPRESENCE OF A BALANCED SPLIT FLAP_W. C. Williams_ May 1942 Flight tests were madewith a modified Ryan ST airplane to deter- mine the effect on aileron characteristics of various arrange- ments of balanced split flaps covering that portion of the wing span occupied by the ailerons. In the full-span flap arrangement_ with which this paper is concerned_ balanced split flaps were located over that portion of the wing span covered by the ailerons_ the inboard portion of the span presumably being fitted with slotted or Fowler type flaps. The investigation consisted of flight tests in which the full-span-flap lateral control arrange- ment was simulated by locating a flap of the balanced split type under that portion of the wing span covered by the ailerons. The tests were confined to measurementsof the effectiveness of the lateral controls.

The airplane was tested with several arrangements of flap deflec- tion_ fore-and-aft positions_ and of the gap between the flap and the lower surface of the wing. Runswere madeat approximately 57 and 85 mph. The corresponding values of airplane lift coeffi- cients were 1.4 and 0.56_ respectively.

Results A region of low aileron effectiveness was found which seemed to agree with some unpublished wind-tunnel reports. It is possible_ however_ that this low aileron effectiveness at partial flap deflections is not_ in reality_ a serious drawbackj because a two- position flap arrangement may be used in which the flap passes quickly through the region of low aileron effectiveness. The balanced split flap was intended for use in the duplex arrangement wherein a Fowler or a slotted flap was used over the inboard portions of the wing_ therefore_ partial flap deflections might very well be confined to movement of these inboard portions.

WRL 243 FLIGHT INVESTIGATION OF NACA D S COWLINGS ON THE XP-42 AIRPLANE.

II - LOW-INLET-VELOCITY COWLING WITH AXIAL-FLOW FAN AND PROPELLER CUFFS_ J. Ford Johnston and T. J. Voglewede_ January 1943 The results are presented for a series of flight tests of the performance and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a short-nose low- inlet-velocity cowling and an axial-flow fan mounted on the spinner. The cowling is one of a series being tested in an effort to improve the performance and cooling characteristics of air- cooled engine installations.

Type of Cowling and Flight Condition Long-nose high-inlet-velocity cowling with small cowl flaps; high speed Long-nose high-inlet-velocity cowling with modified cowl flaps; climb Short-nose low-inlet-velocity cowling with small cowl flaps_ high speed Short-nose low-inlet-velocity cowling with fan_ cuffs_ and small cowl flaps_ high speed Short-nose low-inlet-velocity cowling with fan_ cuffs_ and modified cowl flaps_ climb Short-nose low-inlet-velocity cowling with fan 3 cuffs_ and modified cowl flaps_ high speed As in test 6_ but with baffle seal strips at base of cylinders removed; high speed The first of the climb tests was a sustained climb to 20_000 feet at approximately 155-miles-per-hour indicated airspeed_ an engine speed of 2550 rpm_ and 40 inches of mercury manifold pressure to full throttle_ with the carburetor setting at automatic rich.

The second climb was to the samealtitude at 140-miles-per-hour indicated airspeed and an engine speed of 2550 rpm in full rich.

After the climb tests_ the cowl flaps were fixed closed and addi- tional high-speed,runs were made to determine the effect of the added cowl flaps on the maximum speed of the airplane.

The maximum speed_ pressure_ and temperature were discussed.

Results i. The maximum speed of the XP-42 airplane obtained with the short-nose low-inlet-velocity cowling_ the axial-flow fan_ and propeller cuffs was about 2 mph less than that obtained with the short-nose high-inlet-velocity cowling_ and about 7 mph less than that obtained with the long-nose high-inlet-velocity cowling at the same power and altitude.

2. Cooling-air pressure recoveries on the front of the engine were 87 percent of airplane impact pressure in the high-speed condition_ 99 percent in the full-power climb at 155 mph indicated airspeed_ and 105 percent in the full-power climb at 140 mph.

3. Cylinder-head temperatures were satisfactory in all condi- tions_ but maximum cylinder-base temperatures exceeded the army limit in the high-speed condition and were marginal in climb. A more nearly standard baffle arrangement_ obtained by removing the sealing strips from the bottom of the cylinders_ reduced the cylinder-base temperature indications below the Army limit.

WR L 250 WIND-TUNNEL INVESTIGATION OF A TAPERED WING WITH A PLUG-TYPE SPOILER SLOT AILERON AND FULL-SPAN SLOTTED FLAPS_ John G. Lowry and Robert B. Liddell_ July 1942 An investigation was made on several arrangements of a plug-type spoiler-slot aileron on a tapered wing model of a typical fighter airplane having a full-span slotted flap. The plug-type aileron is essentially a tapered plug that fits into a slot through the wing to conform to the original external wing contour when in the neutral position. When the aileron is deflected_ the plug pro- jects from the upper surface of the wing as a spoiler and_ at the same time_ makes a slot through the wing behind the spoiler. The static rolling-_ yawing-_ and hinge-moment coefficients were deter- mined and were presented for several angles of attack and flap deflections. Estimates of the rolling effectiveness and the stick forces for a fighter airplane were also given.

All tests with the slotted flap retracted were made at a dynamic presSure of 16.37 psf_ or at a velocity of 80 mph. The test Reynolds number was 2_050_000. The tests with the flap deflected were_ in general_ run at a dynamic pressure of 9.21 psf_ or a velocity of 60 mph. The test Reynolds numberwas I_540_000.

The lift characteristics_ aileron characteristics_ and estimated rates of roll and stick forces were discussed.

Results The results of this investigation indicated that a plug aileron will provide satisfactory lateral control on a tapered-wing airplane equipped with full-span slotted flaps. For satisfactory results_ it is essential either to obtain the optimum amount of vent opening or to provide means for deflecting the plate relative to the aileron.

WR L 260 WIND-TUNNEL TESTS OF SPOILERS ON TAIL SURFACES_ Robert B. Liddell, August 1945 Wind-tunnel tests were made in two-dimensional and three- dimensional flow to investigate the aerodynamic characteristics of spoilers on tail surfaces for low-speed flight. The following conclusions were drawn: i. Spoilers showed little possibility of replacing conventional tail control surfaces but might be used as auxiliary control de- vices if a number of their serious disadvantages can be improved.

2. Spoilers should generally be located at the rear portion of the tail surface. It may be advantageous_ however_ to locate an auxiliary spoiler forward on the lower surface of the horizontal tail in order to aid in depressing the tail in the landing maneuver.

3. A forward spoiler alone or in conjunction with the convention- al control surface gave unsatisfactory results because of its erratic action throughout the angle of attack range.

4. A forward auxiliary spoiler should be located on the opposite side of the tail surface from the rear spoiler_ since the two spoilers on the same side of the tail surface tended to cancel the effects obtained by the use of either spoiler alone.

5. A gap between the spoiler and tail surface resulted in a loss of spoiler effectiveness.

WR L 261 WIND-TUNNEL INVESTIGATION OF AN NACA 23012 AIRFOIL WITH A HANDLEY PAGE SLAT AND TWO FLAP ARRANG_ENTS_ Marvin J. Schuldenfrei_ February 1942 An investigation was made of an NACA 23012 airfoil equipped with a Handley Page slat and a slotted and a split flap. The purpose of the investigation was to determine the aerodynamic section charac- teristics of this airfoil with and without flaps_ as affected by the location of the Handley Page slat. A range of slat-nose locations was investigated both with and without flaps at a constant slat gap_ and the effect of slat gap was investigated for the slotted flap deflected 40° . The slat position for maximum lift_ polars for slotted and split flaps for the most favorable slat arrangements for maximumlift_ and complete section data for the most favorable slat arrangements were included. Contours of slat-nose locationwere given for maximum lift coefficient_ for angle of attack for maximum lift coefficient_ and for drag and pitching momentsat selected lift coefficients.

dynamic pressure = 16.37_ RNeff = 3_500j000 The lift_ drag_ and pitching-moment coefficients were measured in all tests from an angle of attack of -6° to the stall.

Results I. The Handley Page slat extended the angle-of-attack range about 9 ° for the plain airfoil and about 14 ° with optimum deflection of either slotted or split flap.

2. The maximum section lift coefficient of the plain airfoil was increased 0.52 by use of the slat_ and the maximum lift coeffi- cient of the airfoil with either flap at optimum flap deflection was increased about 0.26 by the use of the slat. The high drag associated with the increased lift should allow a steeper glide angle.

3. The extension of the slat decreased the negative pitching moments at high lift coefficients with flaps deflected but had little effect in decreasing pitching moments at moderate lift coefficients.

WRL 262 WIND-_EL INVESTIGATION OF THE CHARACTERISTICS OF BLUNT-NOSE AILERONS ON A TAPERED WING_ Paul E. Purser and Thomas A. Toll_ February 1943 An investigation was made of various modifications of a 0.155- chord blunt nose aileron on a semispan model of a tapered wing of a fighter airplane. The modifications considered included various amounts of overhanging nose balance with various nose radii.

The use of blunt-nose ailerons with 40% balance and medium nose radii would reduce the high-speed stick forces to about 15% of those experiences in the use of plain sealed ailerons.

Increasing the balance chord increased the aileron effectiveness slightly and reduced the adverse effects of a gap at the aileron nose.

Increasing the nose radii decreased the aileron effectiveness for small deflections but increased the effectiveness at large deflec- tions and extended the deflection range over which the ailerons maintained their effectiveness.

Increasing the nose radii increased the negative slope of the curves of hinge-momentcoefficient plotted against aileron deflec- tion but_ at the sametim% extended the deflection range over which the slope was relatively small.

Changing the position of the hinge axis from the aileron mean line to a position near the lower surface of the aileron had comparatively little effect on the aileron characteristics.

The peak pressures over the noses of the blunt-nose ailerons were relatively high at moderate deflections.

WRL 271 ADDITIONAL DESIGN CHARTS RELATING TOTHESTALLING OF TAPERED WINGS_ Sidney M. Harmon_January 1943 Charts were presented to show the effects of taper rati% thickness rati% aspect ratio_ and Reynolds numberon the spanwise location of the initial wing stall and on the maximum lift coefficient of the wing. These stall charts supplement the charts given in NACA Report 703 by including additional taper ratios and a root thick- ness ratio of 0.24 tapering to 0.09 at the tip. For a root thickness ratio of 0.24_ the effect of increasing the aspect ratio to 18 was investigated.

The specific conclusions noted mainly for the NACA23024-09 air- foil were: i. Increasing the aspect ratio and Reynolds number tends to move the initial stall location toward the wing center_ while increas- ing the taper ratio moves the initial stall position in the out- board direction.

2. The calculated wing maximum lift coefficient for the NACA 23024-09 wing varies only slightly with aspect ratio for the usual tapers and_ in general_ increases slightly with increasing Reynolds number.

3. In general_ for a constant taper ratio_ a combined increase in thickness ratio and aspect ratio tends to reduce the maximum lift coefficient of the wing and to shift the initial stall location inboard. If the taper ratio is_ in addition_ increased_ the effect of the combined increase in aspect rati% taper ratio, and thickness ratio tends both to reduce the maximum lift coeffi- cient of the wing and to widen the spanwise initial stall region.

ErRL 275 A PRELIMINARY INVESTIGATION OFTHECHARACTERISTICS OF AIR SCOOPS 43O ONA FUSELAGE_ E. Barton Bell and Lucas J. DeKoster_ December1942 Tests were madeof six different air scoops in forward and middle positions on a streamline fuselage.

The air scoops tested in the forward position gave total pres- sures in the inlet almost equal to free-stream total pressure for inlet-velocity ratios of 0.3 or greater.

Whenthe scoops were in positions for which the boundary layer was appreciable_ it was necessary to resort to somemeansof separat- ing the boundary layer air from the inlet air to avoid low total pressure in the inlet. Even with the methods tried here_ there was a decrease in the inlet pressures next to the body.

The critical Mach number increased with inlet-velocity ratio.

For the forward position of the scoopj a critical Mach number of 0.55 was obtainable at an inlet-velocity ratio of 0.3. The high- est critical Mach number for a scoop in the midposition was 0.525 at an inlet velocity ratio of 0.3.

WR L 279 THE EFFECT OF STREAMLINING THE AFTERBODY OF AN NACA COWLING_ George W. Stickle_ John L. Crigler_ and Irven Naiman_ December An investigation was made of cowling shape.

The increase in drag of a conventional NACA open-nose cowling over that of a streamline nose is greatly affected by the shape of the afterbody. Of the two streamline afterbodies testedj the more streamlined afterbody showed the increment of drag associated with changing the nose to be about 1/4 of that with the other.

The results showed that the drag measurements obtained without the use of the propeller on a neutral aftezbody need not be corrected in applying them to the condition of the propeller operating.

WR L 285 FLIGHT INVESTIGATION OF NACA D S COWLINGS ON THE XP-42 AIRPLANE.

IV - HIGH-INLET-VELOCITY COWLING TESTED IN CLIMB WITH AND WITHOUT PROPELLER CUFFS AND IN HIGH-SPEED LEVEL FLIGHT WITHOUT PROPELLER CUFFS_ J. Ford Johnston and T. J. Voglewede_ January 1943 Results are presented of flight measurements of the performance and cooling characteristics of a short nose high-inlet-velocity cowling on the XP-42 for conditions of climb with and without propeller cuffs and for high speed without cuffs.

The maximum speed of the XP-42 airplane with the short-nose high- inlet-velocity cowling was about i mph greater without propeller cuffs than with propeller cuffs.

The cooling air pressure recoveries on the front of the engine in full-power climb at 140 mph indicated airspeed averaged aboutTO% airplane impact pressure with cuffs and 60%without cuffs. The corresponding pressure recoveries in high-speed level flight were 80%and 74%airplane impact pressure.

WRL 290 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS XIV - NACA 0009 AIRFOIL WITHA 20-PERCENT-CHORD DOUBLE PLAIN FLAP 3 Richard I. Sears and Paul E. Purser_ June 1943 Tests have been madeon the NACA 0009 airfoil with a double plain flap that consisted of a plain forward flap having a chord of 0.20 airfoil chord and a 0.15c plain rearward flap.

A 0.20c single or a 0.20c double plain flap deflected 60° posi- tively at zero and positive angles of attack was capable of producing lift as great or greater than a 0.50c plain flap de- flected 30o. At large negative angles of attack_ the small chord flaps were capable of producing as muchpositive lift as a 0.50c plain flap deflected 17° .

A 0°20c double plain flap was capable of producing adequate lift for use as a rudder or as an aileron. For use as an elevator_ however_ a double flap of slightly larger chord may be required if more than 30° deflection of a conventional 0.30c elevator or more than 17° deflection of a conventional 0.50c elevator is re- quired to land the airplane.

Whenadequately balanced_ small-chord double flaps of large lift effectiveness should be desirable for use as ailerons because the aileron span may be reduced and thereby may permit the use of larger-span high-lift devices.

With a 0.20c double plain flap_ a lift effectiveness per unit stick (or pedal) deflection equal to that of a 0.50c single plain flap can be obtained by adjusting the rate of flap deflection with stick (or pedal) deflection. Under these conditions_ the 0.20c double plain flap had a rate of change of stick hinge momentwith angle of attack that was about 1/16 that for the 0.50c flap and a rate of change of stick hinge momentwith stick (or pedal) deflec- tion that was less than 1/4 that for the 0.50c flap.

With controls free_ the slope of the lift curve for a control surface having a 0.20c single or a 0.20c double plain flap was more than twice that for a control surface having a 0.50c single plain flap. The control-free stability of the airplane will vary accordingly.

Although the stick hinge momentsof small-chord double plain flaps were much less than those of large-chord single flapsj they were not small enoughfor use as control surfaces on large high speed airplanes. In order to function efficiently_ a double flap control surface must have sealed gaps and the rearward flap must have a chord that is a large percentage of the chord of the forward flap.

WRL 300 WIND-TUNNEL TESTS OFAIR INLETANDOUTLET OPENINGS ONA STREAMLINE BODY_ John V. Becker_ November1940 Tests were madeto determine the effect on external drag and on the pressure distribution of air inlet openings located at the stagnation point of a streamline body. Air outlet openings located at the tail and at the 21-percent and 63-percent stations of the body were also investigated. Boundary-layer transition measurementswere madeand correlated with the force and pressure data. Individual openings were tested with the aid of a blower and then practicable combinations of inlet and outlet openings were tested. Various modifications to the internal duct shape near the inlet opening and the aerodynamic effects of a gun in the duct were also studied.

The speeds at which the tests were conducted were up to 450 mph or a speed range where compressibility must be considered.

WRL 301 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

III - A SMALL AERODYNAMIC BALANCE OFVARIOUS NOSE SHAPES USED WITH A 30-PERCENT-CHORD FLAPONAN NACA 0009 AIRFOIL_Milton B. Ames_ Jr._ August 1941 Tests were madein the NACA 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap having a small amount of aerodynamic balance. The effect of balance nose shape and gap at the nose of the flap was determined. A few tests were madeto determine the effectiveness of a tab on the balanced surface. The complete section aerodynamic characteristics of someof the arrangements tested were given. A partial analysis of the data was madeand the results were given. These results were comparedwith results of other tests presented in NACAreports.

The model completely spanned the tunnel test section. The gap between the tab and the flap was fixed at 0.I of I percent of the airfoil chord.

dynamic pressure = 15 psf_ v = 76 mph_effective RN = 2_760_000 6 flap nose shapes were tested first_ but only 3 were found to give sharp characteristics. The three used were called blunt_ medium_and sharp.

The angle of attack range was from negative to positive stall.

The pitching moment_flap hinge moment_balance effectiveness_ tab_ and drag characteristics were discussed.

Results i. For a given lift coefficient the reduction in flap section hinge-moment coefficient obtainable by the addition of a small aerodynamic overhanging balance will change with the variation of the flap nose shape and the size of the gap at the flap nose.

2. The blunt nose flap gave the greatest reduction in flap hinge- moment coefficient for moderate flap deflections_ but for flap deflections greater than 20°_ the medium nose flap was the most effective in this respect, 3. The lift effectiveness of the flap was the same as for a plain flap and was unaffected by the small amount of aerodynamic over- hanging balance.

4. The tab characteristics appeared to be unaffected by nose shape and overhang for unstalled condition.

5. The minimum profile-drag coefficient was obtained with the blunt nose flap neutral and with the gap sealed.

6. As taper of flap nose was increased_ so was the profile drag coefficient.

WR L 311 WIND-TUNNEL TESTS OF TWO TAPERED WINGS WITH STRAIGHT LEADING EDGES AND WITH CONSTANT-CHORD CENTER SECTIONS OF DIFFERENT SPANS_ Richard W. Fairbanks and Sidney R. Alexander_ October 1943 An investigation was conducted in the NACA 19-foot pressure tunnel of two-tapered wings with NACA 230-series airfoil sections_ straight leading edges_ and constant-chord center sections. The spans_ areas_ and root chords of both wings were equal. The center-section span of one wing was equal to the root chord; whereas the center-section span of the other was equal to twice the root chord. Both wings were equipped with partial- and full- span simple split flaps. Lift_ dragj and pitching-moment coeffi- cients were determined for the plain wing and for each flap arrangement through a test Reynolds number range of 2_600_000 to 4_700_000. Stalling characteristics were determined for the plain wings and with flaps deflected 60 ° .

The airfoil sections were NACA 23015 at the root and NACA 23009 at the tip. The flaps used were 20-percent-chord simple split flaps.

The flap spans were 53 percent of the wing span for the partial.

span condition and 90 percent of the wing span for the full-span condition.

absolute pressure = 35 psi angle of attack range was from -6 degrees to stall The wings were designated wings I and IV with wing IV having a greater sweepforward than wing I.

Results Wing I had greater maximumlift coefficients and greater incre- ments of maximum lift coefficient.

The increment of maximum lift coefficient due to split flaps is greater for the wings with straight leading edges than for similar wings with straight trailing edges.

No difference in drag is seen for the two wings at low lift.

The effect of increase in center-section span is to decrease the shift of the aerodynamic center of the wing in the direction of the wing sweep.

WRL 314 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

XIII - VARIOUS FLAPOVERHANGS USED WITHA 30-PERCENT-CHORD FLAP ONANNACA66-009 AIRFOIL_ Clarence L. Gillis and Vernard E.

Lockwood_July 1943 Force tests in 2-dimensional flow were madeon an NACA66-009 airfoil with a flap having a chord 30 percent of the airfoil chord and a tab having a chord 20 percent of the flap chord. A plain flap and flaps having overhangs of 35 and 50 percent of the flap chord were tested with two gap variations_ sealed and un- sealed. The results were presented as aerodynamic section char- acteristics.

Three flap arrangements were tested: (i) a plain flap_ (2) a flap having a 0.35cf overhang3 and (3) a flap having a 0.50cf overhang.

A blunt nose shape was used for each flap.

dynamic pressure = 15 psf_ v = 76 mph_effective RN = 2_760_000 The flap deflections used were 0°_ i°_ 2°_ 5o_ and in 5° incre- ments to 20o_ 25o_ or 30° . Wheneither stall position was approached 3 the increment was reduced to IO.

Tunnel corrections were applied only to the lift.

The lift_ flap hinge moments_pitching moments_drag_ and tab characteristics were discussed.

The results were comparedto the NACA 0009 and NACA 0015 airfoils.

Results The slope of the lift curve at small angles of attack was slightly greater for the NACA 66-009 airfoil than for the NACA 0009 and 0015 airfoils.

The hinge-moment-coefficient curves generally had greater negative slopes than those for the NACA 0009 and 0015 airfoils.

The pitching-moment-coefficient curves showedthat the aerodynamic center for an angle-of-attack change at a constant flap deflection remained near the quarter-chord point for all overhangs and gap conditions.

The tab was effective in producing increments of lift coefficient and flap hinge-moment coefficient for tab deflections throughout the range tested (from 20° to -20°) and was more effective when deflected opposite to the deflection of the flap.

The effect of the smaller included angle at the trailing edge in building up greater lift over the airfoil trailing edge was evident in the increased lift-curve slope_ the more negative hinge-moment coefficients_ and the further rearward position of the aerodynamic center on the NACA 66-009 as comparedwith the NACA 0009 and 0015 airfoils.

WRL 317 WIND-TUNNEL INVESTIGATION OF PLAINAILERONS FORA WING WITHA FULL-SPAN FLAPCONSISTING OF AN INBOARD FOWLER ANDAN OUTBOARD RETRACTABLE SPLITFLAP_ThomasA. Harris and Paul E. Purser_ March 1941 An investigation was madein the wind tunnel of three plain ailerons on an NACA 23012wing with full-span combinations of Fowler and split-type flaps. The static rolling_ yawing_ and hinge momentswere determined and were presented for several angles of attack and flap deflections. In addition_ the lateral-control characteristics were computedfor a typical pursuit airplane with two of the arrangements.

The tests were madeto determine the characteristics of a plain aileron on a wing with an outboard retractable split-type flap and an inboard flap of a type giving a higher lift and lower drag than the split flap.

v = 40 mph_ RN= i_440_000 Results Both the plain and the balanced ailerons gave about equal rolling-moment coefficients with the flap completely retracted.

The maximum stick force with full aileron deflection for the high- speed flight condition was about 25 percent less for the balanced aileron than for the plain aileron.

For the low angle of attack condition the yawing-momentcoeffi- cients were favorable or positive.

It is believed that the lateral control system will work equally well with any other type of inboard flap.

WRL 319 FORMULAS FORUSEIN BOUNDARY-LAYER CALCULATIONS ONLOW-DRAG WINGS_ E. N. Jacobs and A. E. von Doenhoff_ August 1941 This report was prepared in response to frequent requests received from aircraft companies for information concerning methods of computing on low-drag wings the: (i) Transition point (2) Velocity distribution in laminar and turbulent boundary layers (3) Thickness of the boundary layer_ both laminar and turbulent i. On the new low-drag sections the laminar separation point is so close behind the point of minimumpressure that transition is assumedto occur at the minimumpressure point if R6 is less than the previously mentioned value at the minimumpressure point_ where R 6 is the Reynolds number based on boundary layer thickness.

2. Boundary-layer velocity distribution measurementshave shown that in a favorable pressure gradient the shape of the laminar distribution is very closely approximated by the Blasius distribu- tion for a flat plate. An approximate relation for this distribu- tion_ due to Pohlhausen_ is given by the formula: = 0.8144(y/8) 0 1350(y/8) 3 + 0.0275(y/8) 4 V - " The outer limit of the boundary layer corresponds to: (y/8) = 2.4558 In a turbulent boundary layer_ the i/7-power law is a fair approx- imation to the shape of the velocity profile_ that is_ u ( 11/7 V when the pressure gradient is favorable.

3. The thickness of the laminar layer in a region of favorable pressure gradients is: c V 8,17 s 62 = 5"3 %_ (# fo (%o 8"17 d Sc where: c = chord s = distance along surface from leading edge V ° = reference velocity V = velocity outside boundary layer V I = velocity outside boundary layer at point for which boundary layer is being computed L = length r = distance of surface from axis of revolution The corresponding relation for bodies of revolution is: L V 8.17 s/L

v

o o The momentum thickness of the turbulent boundary layer where there is no danger of turbulent separation can be found from: 0,3914_ 6 = _ 0.2454 e where _ is related to a skin friction coefficient by: _2 = pV L T o and T o is shearing stress at surface and p is the density.

WR L 325 WIND-TUNNEL TESTS OF AILERONS AT VARIOUS SPEEDS. III - AILERONS OF 0.20 AIRFOIL CHORD AND TRUE CONTOUR WITH 0.35-AILERON-CHORD FRISE BALANCE ON THE NACA 23012 AIRFOIL_ W. Letko and W. B. Kemp_ September 1943 Hinge moment_ lift_ and pressure-distribution measurements were made on a Frise aileron on an NACA 23012 airfoil in the 2- dimensional LMAL stability tunnel. Speeds up to 360 mph_ Mach number = 0.470_ were used. The nose radius of the aileron was varied from 0.0012 to 0.0150 of the airfoil chord. Tests also were made with an increased vent gap and with the lower surface of the airfoil at the entrance of the slot rounded to a radius of 0.02 of the airfoil chord. The primary purpose of all tests was to determine the effects of speed on this type of aileron.

The variation in section hinge-moment and section lift coefficient with Mach number and angle of attack was shown in curves of hinge- moment_ and lift coefficient was plotted against aileron deflection for the various conditions tested. Slopes of these curves were determined and plotted against Mach number and aileron nose radius.

Frise ailerons of 0.20 airfoil chord and 0.35-aileron-chord balance was tested.

Section hinge moment and section lift were measured for a speed range of from 150 to 360 mph. The Reynolds number range was from 2_800,000 to 6_700_000.

The tests were made at angles of attack of -5o_ 0 o, 5o_ and I0 o and for each angle of attack readings were taken at aileron de- flections of 0°_ ± 2° , _ 5°_ ± 7°_ ! i0°_ ± 13°, _ 16°_ ± 18°, and + 20 °.

Corrections for tunnel-wall effects were not applied to the hinge- moment coefficients.

Hinge-moment_ and lift results were discussed.

Results I. The unstalled range of negative aileron deflections was de- creased by increasing the airspeed.

2. For small aileron deflections the aileron with the smallest .nose radius tested was most effective in reducing hinge moments_ but the effective range was limited.

3. Oscillations of the Frise ailerons occurred at the negative angle of stall of the ailerons, 4. A vibration or shudder different from the oscillation occurred at the high speed at large angles of attack and at small and even zero aileron deflections.

WR L 331 THE EFFECT OF EXTERNAL SHAPE UPON THE DRAG OF A SCOOP_ Irven Naiman and Paul R. Hill, July 1941 The principles of NACA cowling design may be applied to scoop fairing. Six scoops were built and tested to show the advantage of using these principles. Three of the scoops had a good nose contour with different afterbody lengths, and three were of inferior nose shape.

The scoop tests were made on a 0.4 scale model of the XP-41 air- plane with a revised fuselage 25 percent longer than the original one. The tests were run at a dynamic pressure of 50 psf and at a RN = 3_000_000 based on the mean wing chord. Six scoops_ designated A to F_ were tested on the bottom of the fuselage.

All scoop had an area of 47 square inches.

Results I. The most desirable place to take in cooling air for accessor- ies_ such as oil coolers_ intercoolers_ etc._ was at the nose of the fuselage or nacelle_ even if it was necessary to increase the cowling area.

2. If it is necessary to take air in through a scoop or under- slung duct_ low scoop drag may be secured by utilizing the design principles of the NACA cowling.

3. Scoopstested with a nose which used the principles of the NACA cowling gave not only a low drag increase but a critical speed of 400 mphwith no air flow.

4. Scoopdrag was found to be quite insensitive to changes in afterbody length in the range of four to eleven times the scoop depth.

5. Complete disregard of the principles of fairing resulted in a scoop which almost doubled the drag of the model.

An analysis of scoop design was given in the appendix.

WRL 332 WIND-TUNNEL TESTS OF TWO TAPERED WINGS WITHSTRAIGHT TRAILING EDGES ANDWITHCONSTANT-CHORD CENTER SECTIONS OF DIFFERENT SPANS_ Robert H. Neely_ March 1943 Tests were madeto determine the aerodynamic characteristics of two tapered wings having NACA230-series airfoil sections_ constant-chord center sections_ and straight trailing edges. The wing spans_ the areas_ and the root chords of the two wings were equal; the span of _he center section of one wing was equal to the root chord (III) and the span of the other was twice the root chord (IV). Lift_ drag_ and pitching-moment characteristics of the wings with partial-span and full-span flaps were given for a test Reynolds number of 4_600_000. Complete lift_ drag_ and pitching- momentcharacteristics were determined for each wing through a range of Reynolds numbers of 2_600_000to 4_600_000.

Lift and stalling characteristics_ drag characteristics_ and pitching-moment characteristics were presented.

Results i. The maximum lift Position of aerodynamic center coefficients of wing III back of leading edge (S/b) were greater than those Wing Experimental Calculated of wing IV for all condi- III 0.451 0.460 tions tested because of IV 0.442 0.442 the latter stalling.

2. The effect of increasing the span of the center section while keeping the wing span_ the root chord_ and the area constant and the trailing edge straight is to shift the aerodynamic center toward the leading edge.

3. The horizontal positions of the aerodynamic centers as determined by experiment and by calculation from section charac- teristics are in close agreement.

4. Increasing the span of the center section increased the drag coefficients for lift coefficients greater than 0. i.

AERODYNAMIC CHARACTERISTICS OF A SLOT-LIPAILERON ANDSLOTTED FLAP WRL 337 FORDIVE BRAKES_ F. M. Rogalloj April 1941 Section aerodynamic characteristics of an NACA23012 airfoil with a slot-lip aileron and slotted flap have been determined over a large range of flap and aileron deflections. The results_ which are presented in charts_ indicate that these devices may be com- bined so as to provide satisfactory dive control. Additional tests are recommended for determination of the buffeting effects.

The investigation was madefor the purpose of developing devices suitable for limiting the diving speeds of airplanes. The tests were run in a wind-tunnel at a speed of 80 mph corresponding to an average effective Reynolds numberof 3_500_000. The lift was corrected for tunnel effects_ but no drag corrections were made except for turbulence. The section lift_ drag_ and pitching- momentcoefficients of the complete wing and the section hinge- momentcoefficient of the slot-lip aileron_ over a wide range of deflection of the flap and the aileron_ were presented.

The data indicated that slot-lip ailerons and slotted flaps may be combined to provide satisfactory dive control. These data_ how- ever_ give no indication of the tendency of the arrangement to induce flutter or buffeting_ a tendency known to exist in many proposed dive-control devices.

WRL 345 PRELIMINARY REPORT ONLAMINAR-FLOW AIRFOILSANDNEW METHODS ADOPTED FORAIRFOIL ANDBOUNDARY-LAYER INVESTIGATIONSj EastmanN.

Jacobs_ June 1939 This report is an investigation of several low-drag airfoil and charts of their aerodynamic characteristics. They have low drag because they are designed to have laminar flow up to unusually large Reynolds numbers. Note that these airfoils can be tested only in tunnels which are exceptionably free of turbulence_ as this not only hastens transition_ but it also changes the nature of the transition.

Such properties as be neededcould be found in reference books such as Theory of Wing Sections by Abbott and Doenhoff.

WRL 355 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

IV - A MEDIUM AERODYNAMIC BALANCE OF VARIOUS NOSE SHAPES USED WITH A 30-PERCENT-CHORD FLAP ON AN NACA 0009 AIRFOIL_ Milton B. Ames_ Jr._ and Donald R. Eastman_ Jr._ September 1941 The results of the tests of a 0.30c flap having a 0.35 chord flap (cf) aerodynamic overhand indicated that the largest reduction in the flap section hinge-moment coefficient was obtained with blunt nose flaps. The lift effectiveness of the flap with either a blunt or medium nose shape and a 0.35cf overhang was slightly greater than that obtained with a plain flap or a flap having a small aerodynamic overhang. The adverse effect of a gap at the flap nose on the balance effectiveness of a flap having a 0.35cf overhang generally was less than for a plain flap or a flap having a small aerodynamic balance. When the angle of attack and the flap deflection were both positive_ the test data indicate that with a blunt or medium nose flap_ the largest gap gave the highest values of airfoil section lift coefficient and the most balance effectiveness at large flap deflections.

The effect of tab deflection on the hinge moment coefficient of a flap with 0.35cf aerodynamic overhang was less than for the same tab size on a plain flap_ but this reduction in balance effective- ness of the tab was very slight.

The minimum profile drag coefficient was obtained with the blunt nose flap neutral and with the gap sealed. The medium and sharp nose flaps gave increments in minimum profile-drag coefficients of 0.0014 and 0.0024_ respectively_ over that obtained with the blunt nose flap.

WRL 366 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

X - A 30-PERCENT-CHORD PLAIN FLAP WITH STRAIGHT CONTOUR ON THE NACA 0015 AIRFOIL_ H. Page Hoggard_ Jr._ September 1942 Force-test measurements in 2-dimensional flow were made in the NACA vertical wind tunnel to determine the characteristics of an NACA 0015 airfoil equipped with a straight-contour plain flap having a chord 30 percent of the airfoil chord. The straight- contour plain flap differs from an ordinary plain flap in that the surfaces behind the hinge axis are flat instead of conforming to the basic airfoil contour. The results are presented in the form of aerodynamic section characteristics for several flap deflec- tions and for a sealed and unsealed gap at the flap nose.

dynamic pressure = 15 psf_ v = 76 mph_ effective Reynolds number = 2_760_000 The flap was set_ in increments of 5o3 at deflections from 0o to 30° for tests with the gap both sealed and unsealed. For each flap setting 3 force tests were madethroughout the angle-of-attack range at 2° increments from negative stall to positive stall.

Wheneither stall position was approached the increment was re- duced to io angle of attack.

The lift 3 hinge momentof flap3 pitching moment 3 and drag were discussed.

Results i. The slope of the lift curve for the airfoil with the straight- contour plain flap was greater than for the same airfoil with the airfoil-contour plain flap.

2. The lift effectiveness of the straight-contour plain flap was slightly less with gap sealed and slightly larger with gap un- sealed than the lift effectiveness of the airfoil-contour flap with the same gap conditions.

3. For the straight-contour flap_ the variation of the flap hinge-moment coefficient with angle of attack and with flap de- flection was larger than for the airfoil-contour flap.

4. The location of the aerodynamic center for the straight- contour flap was in close agreement with the location of the aero- dynamic center for the airfoil-contour flap.

5. The airfoil had approximately the same drag characteristics for both flap contours.

WR L 374 WIND-TUNNEL INVESTIGATION OF 20-PERCENT-CHORD PLAIN AND FRISE AILERONS ON AN NACA 23012 AIRFOIL 3 F. M. Rogallo and Paul E.

Purser_ December 1941 An investigation of several modifications of 20-percent-chord plain and Frise ailerons on an NACA 23012 airfoil was made in the NACA 7- by 10-foot wind tunnel. The static rolling 3 yawing 3 and hinge moments were determined and presented for several angles of attack. The conditions under which aileron oscillation occurred were also determined. The aileron-control characteristics were computed for a pursuit airplane with several of the aileron arrangements and with three assumed aileron linkages.

The effective Reynolds number was i_4403000 for a v = 40 mph.

Some of the tests were repeated at v = 80 mph and RNef f = 23 8803000.

The results of the tests were presented as curves of rolling-_ yawing- 3 and hinge-moment coefficients plotted against aileron The flap was set at deflections from 0o to 30° in 5° increments.

The tab was set at 0°_ 15o_ and -15° for each of the flap settings and a few tests were madewith the tab deflected ! I0°_ ± 20o_ ± 30° . For each flap and tab setting_ force tests were made throughout the angle-of-attack range from negative stall to posi- tive stall at 2° increments of angle of attack.

Tunnel corrections were applied to lift only.

The lift_ hinge momentof flaps_ pitching moment_drag_ and hinge momentof tab were discussed.

Results i. An airfoil having a sealed gap at the flap nose required less stick force at a given lift and angle of attack than an airfoil having any size gap within the range tested.

2. Sealing the gap increased the control effectiveness_ delayed separation over the flap_ decreased the drag at most values of lift_ and slightly reduced the effectiveness of the tab.

3. Where maximum flap effectiveness and minimum stick forces are primary considerations in designing a plain flap control surface_ the gap at the flap nose should be sealed.

4. Too much reliance should not be placed in the use of param- eters to obtain characteristics of flapped airfoils with gaps be- cause the gap precipitates separation_ causing an early departure from the linear relationships assumed to exist between the varia- bles.

WRL 378 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS VIII - A LARGE AERODYNAMIC BALANCE OF TWO NOSE SHAPES USED WITH A 30-PERCENT-CHORD FLAP ON AN NACA 0015 AIRFOIL_ Richard I. Sears and Clarence L. Gillis_ July 1942 Force tests in 2_dimensional flow were made of the characteris- tics of an NACA 0015 airfoil with a balanced flap having a chord 30 percent of the airfoil chord_ a flap-nose overhang 50 percent of the flap chord_ and a tab having a chord 20 percent of the flap chord. The results were presented in the form of aerodynamic section characteristics for a sealed and an unsealed gap at the flap nose.

dynamic pressure = 15 psf_ v = 76 mph_ RNef f = 2_7603000 The flap was set at deflections from 0 ° to 25 ° in 5 ° increments.

The tab was set at deflections from 0 ° to 20 ° in 5o increments for both flap-nose shapes. For each flap and tab setting_ force tests were made throughout the angle-of-attack range at 2o increments from negative stall to positive stall. Wheneither stall position was approached_ the increment was reduced to i °.

The lift_ hinge momentof flap_ pitching moment_drag_ and tab characteristics were discussed.

Results i. The slope of the lift curve for the NACA 0015 airfoil was slightly less than that for the NACA 0009 airfoil and decreased when the gap at the flap nose was sealed.

2. The lift effectiveness of the flap with large balance on the NACA 0015 airfoil was practically the same as that of the plain flap on the same airfoil and as that of the similar flap on the NACA 0009 airfoil.

3. The blunt-nose balance was more effective in reducing flap hinge moments and caused greater overbalance than the medium-nose balance_ but the effectiveness of the blunt-nose balance was not maintained to so high a flap deflection when the flap was deflect- ed in conjunction with the angle of attack as that of the medium- nose balance.

4. The medium-nose flap caused an increase in minimum profile- drag coefficient of 0.0022 over that of the airfoil with plain flap_ whereas the blunt-nose flap gave no measurable increase.

5. The tab_ when deflected in conjunction with the angle of attack_ gave greater increments of lift and flap hinge-moment coefficients per unit tab deflection than when deflected in opposition to the angle of attack.

WR L 380 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

II - A LARGE AERODYNAMIC BALANCE OF VARIOUS NOSE SHAPES WITH A 30-PERCENT-CHORD FLAP ON AN NACA 0009 AIRFOIL_ Richard I. Sears and H. Page Hoggard_ Jr., August 1941 Tests were made of an NACA 0009 airfoil with a 30-percent-chord flap having a 49.5-percent flap-chord balance with various nose shapes and two gaps. The results were presented in the form of aerodynamic section characteristics. A method was proposed for reducing the control forces to any desired value while_ at the same time_ markedly increasing the lift effectiveness of the airfoil-flap combination over that of a plain flap of the same chord. Characteristics of a plain airfoil-flap combination with gaps sealed and unsealed were made in 5 of the references of this report for 2-dimensional flow. The tests reported in this report were made to provide section data for an airfoil having a flap with a large overhang and to determine the effects of the shape of the nose of this overhang. The terms "balance" and "overhang" are used synonymouslyto indicate the portion of the movable surface ahead of the hinge axis.

dynamic pressure = 15 psf_ v = 76 mph 3 RNef f = 23760_000 The flap deflections were set at 5° increments_ and with the blunt nose and sealed gap3 tests also were madeat lo 3 2o3 3° flap de- flections. With sealed gap the maximum flap deflection tested was limited to 15 or 20 degrees depending on the flap nose shape. The angle of attack range was from negative to positive stall.

The lift_ hinge momentof flap3 drag_ pitching moment 3 and effect of differential balancing tab were discussed.

Results i. The results of the tests showed that a flap with 49.5-percent overhang was aerodynamically overbalanced when deflected regard- less of nose shape. The large amount of overhang reduced the slope of the curve of hinge moment against angle of attack to practically zero.

2. The flap effectiveness in producing lift was about the same as for the unbalanced flap of the same chord.

3. The small gap tested had little effect on any of the charac- teristics.

4. The smallest increment in drag was obtained with the blunt- nose shape.

5. A tab deflected in the same direction as the flap in order to increase both the lift and the hinge moment of an overbalanced flap shows promise of being a very satisfactory arrangement for reducing stick forces and improving free-control stability.

WRL 383 FLIGHT INVESTIGATION OF NACA DS COWLINGS ON THE XP-42 AIRPLANE.

I - HIGH-INLET-VELOCITY COWLING WITH PROPELLER CUFFS TESTED IN HIGH-SPEED LEVEL FLIGHTj F. J. Bailey_ Jr._ and J. Ford Johnston_ January 1943 Only very generalized information was given which is surpassed by later publications dealing with this problem.

WRL 397 FLIGHT TESTS OF AN ALL-MOVABLE VERTICAL TAIL ON THE FAIRCHILD XR2K-I AIRPLANE_ Harold F. Kleckner_ June 1943 In this report an all movable rudder was investigated. The original rudder of the plane was replaced with an all movable rudder_ the report said this worked very well. This investigation was to learn the effect of size on the effectiveness of the rudder.

The rudder size was cut in half from 11.6 to 5.8_ but complete stalling was not obtained in steady sideslips as the sideslip angle obtained with full rudder was not large enough. The float- ing ratio_ partial of rudder deflection over a partial of angle of attack for the samerudder hinge-moment coefficients_ was lower at large angles of sideslip than at small angles; thus the in- crease in directional stability was not as great as expected. The floating ratio had to be closely controlled to prevent continuous yawing oscillations of small amplitude (snaking).

Although general conclusions were reached care should be taken in applying these conclusions to planes that differ much from the XR2K-I.

SOME EFFECTS OF REYNOLDS AND MACH NUMBERS ON THE LIFT OF AN NACA WR L 406 0012 RECTANGULAR WING IN THE NACE 19-FOOT PRESSURE TUNNEL_ Thomas C. Muse_ May 1943 A short investigation was made to determine the aerodynamic char- acteristics of a rectangular wing model constructed to NACA 0012 airfoil sections. Reynolds numbers ranged from 1.07xlO 6 to 8.24xi06.

Compressibility effects produce pronounced changes in the value of the maximum lift coefficient for Mach numbers exceeding approxi- mately 0.17. Below this value Reynolds number effects apparently predominate.

Determination of the maximum lift coefficient by wind-tunnel tests must therefore be done with due regard for the flight condition to which the results will be applied.

WR L 407 WIND-TUNNEL INVESTIGATION OF WING DUCTS ON A SINGLE-ENGINE PURSUIT AIRPLANE_ W. J. Nelson and K. R. Czarnecki_ October 1943 A study of several ducts installed in the wings of a model of a conventional single engine pursuit plane was made to determine the influence of inlet design and cooling-air flow on the pressure losses within the duct and on the aerodynamic charac- teristics of the plane.

The pressure recovery ahead of the radiator installed in a wing duct was determined principally by the inlet velocity ratio 3 the lift coefficient and the shape and location of the inlet lips and diffuser.

Highest pressure recoveries at the front force of the radiator were obtained at inlet-velocity ratios from 0.4 to 0.6.

A duct with the plane of the inlet opening perpendicular to the wing chord and with a diffuser parallel to the chord line gave highest pressure recoveries at low lift coefficients. At high lift coefficients_ best pressure recovery was obtained when the upper lip was extended ahead of the lower lip and the diffuser was inclined downward.

Becauseof rotation in the slipstream of a single propeller_ the pressure recovery in a duct located behind the upgoing blades was not the sameas that in a similar duct symmetrically located be- hind the downgoingblades. Best design practice would require different ducts on the right and left wings.

The use of outlet flaps reduced the static pressure in the exit as much as 60%of the free-stream dynamic pressure.

An inlet with a well-cambered upper lip properly aligned with the flow at the leading edge of the wing effected a small increase in the CLmax;whereas substantial decreases in the CLmax were effected by ducts with the inlet plane perpendicular to the chord line and by inlet lips with small leading edge radii.

The best compromisefixed inlet tested had an upper lip with a large leading edge radius conforming approximately to the contour of the original wing_ a lower lip cut back to turn the inlet plane downward70° to the chord lin% and a diffuser inclined approximately i0 o to the wing chord.

An inlet with an adjustable lower lip appeared feasible in cases in which fixed inlets were unsatisfactory because of an extreme range of inlet velocity ratio and lift coefficient.

WRL 415 AERODYNAMIC CHARACTERISTICS ANDFLAPLOADS OF PERFORATED DOUBLE SPLITFLAPSONA RECTANGULAR NACA 23012 AIRFOIL_Paul E. Purser and ThomasR. Turner_ January 1943 Tests madeon perforated double split flaps for flap loads and additional aerodynamic characteristics. Effects of flap deflec_ tio% flap span_ perforation shap% location and amountof perfora- tion, and presence of a fuselage on the flap loads at one spanwise station were also determined.

Aerodynamic characteristics of the airfoil are given in a ref- erance (Purser, Paul E., and Turner_ ThomasR.: Wind-tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes of a Rectangular NACA 23012 Airfoil_ NACA ACR 3 July 1941).

Application of the data to the design of dive brakes for fighter planes discussed in the above reference and Purser, Paul E., and Turner_ ThomasR.: Wind-tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes on a Tapered NACA23012 Airfoil_ 45O NACA ARRj November1941_ and Purser_ Paul E.: A Study of the Application of Data on Various Types of Flap to the Design of Fighter Brakes_ NACA ACR_June 1942.

Effects of the performances may be sunm_arized as follows: In general_ drag coefficient and the flap loads decreased as the amount of perforation was increased and as one row of perfora- tions was mo_edfrom the flap leading edge to the flap trailing edge. The variation of drag and flap loads with lift also de- creased as the amountof perforation was increased. The shape of the perforations had little effect on flap loads.

The presence of an elliptical fuselage reduced the loads on and the drag with 60-percent span perforated double split flaps. In the landing configuration (only lower flap deflected)_ presence of circular perforations that removed 33%of the flap area reduced the slope of the lift curve by about 5%and reduced the maximum lift coefficient about 10%.

WRL 420 WIND-TUNNEL DEVELOPMENT OF A PLUG-TYPE SPOILER-SLOT AILERON FORA WING WITHA FULL-SPAN SLOTTED FLAPANDA DISCUSSION OF ITS APPLI- CATION_ Francis M. Rogallo and Robert S. Swanson_ November1941 An investigation was madeof several arrangements of a plug-type spoiler-slot aileron on an NACA 23012 airfoil with a full-span slotted flap.

The results of this investigation indicate that a spoiler-slot aileron will provide satisfactory lateral control on airplanes equipped with full span slotted flaps. Because the aileron re- quires no large slots_ or openings in the wing when it is in the neutral position_ it should be acceptable for use on modern high_ performance airplanes. The spoiler slot aileron when located at 0.67 chord position was tested and considered unsatisfactory for use on a wing with a full-span split flap unless the aileron is uprigged when the flap is deflected_ but it may be satisfactory when located nearer the trailing edge.

WRL 421 WIND-TUNNEL INVESTIGATION OF A PLAIN ANDA SLOT-LIPAILERON ONA WING WITHA FULL-SPAN FLAPCONSISTING OF AN INBOARD FOWLER AND AN OUTBOARD SLOTTED FLAP_F. M. Rogallo and Marvin Schuldenfrei_ June 1941 An investigation was madeof a slot-lip aileron and a plain aileron_ singly and in combination_ on an NACA 23012 wing with a full-span flap. The flap consisted of a 0.30c Fowler flap over the inboard 63%of the wing span and a modified slotted flap over the remainder of the wing.

The characteristics of the plain and slot-lip ailerons on the wing with full span Fowler and modified slotted flaps were essentially the sameas the characteristics of similar devices on the wing with full-span NACA slotted flaps. An increase in maximumlift coefficient of approximately 14%was indicated by these flaps over other slotted flaps.

The 0.10c by 0.36 b/2 plain aileron tested was considered too small where c = chord and b = span; an increase of about 50%in its area was recommended. With this modification_ a combination of plain and slot-lip ailerons should provide acceptable lateral- control characteristics throughout the useful flight range.

WRL 428 DRAG ANDPROPULSIVE CHARACTERISTICS OFAIR-COOLED ENGINE-NACELLE INSTALLATIONS FORTWO-ENGINE AIRPLANES_ Herbert A. Wilsonj Jr._ and Robert R. Lehr_ June 1942 Research on wing-nacelle propeller arrangements was continued with tests on a model of a two-engine airplane provided with nacelles varying in diameter from 1.6 to 2.6 times the local wing thickness.

The overall efficiency of the two-engine model decreased linearly with an increase in the ratio of the nacelle diameter to the wing thickness.

The propulsive efficiencies were substantially the samefor all nacelle arrangements.

The static longitudinal stability was adversely affected by the addition of the nacelles to the wing and the operation of the propellers.

The addition of the two nacelles to the wing decreased the maximum lift by only 1%.

WRL 431 WIND-TUNNEL TESTS OFAILERONS AT VARIOUS SPEEDS.I - AILERONS OF 0.20 AIRFOIL CHORD ANDTRUE CONTOUR WITH0.35 AILERON-CHORD EXTREME BLUNT NOSE BALANCE ONTHENACA66_2-216 AIRFOIL_W. Letko_ H. G. Denaci_ and C. Freed_ June 1943 The results of the tests of ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt nose balance on the NACA66_2-216 airfoil indicate that: Increasing the Mach numberup to 0.470 generally caused a small increase of the hinge-moment and lift coefficients but increased the stalled range of the ailerons considerably.

An increase of the balance nose radii from 0 to 0.02 chord in- creased the range for which the aileron is effective by about 8° but results in increased hinge-momentcoefficients with little change in lift coefficients in the unstalled range.

An increase of the gap width increased the hinge-moment coeffi- cients slightly with little change in lift coefficient_ however_ a considerable increase in the stalled range of the aileron resulted. The magnitude of the increase varied with angle of attack.

The amountof balance tested_ 0.35 aileron chord_ gave no case of complete balance and in somecases the unbalance was relatively large.

WRL 432 WIND-TUNNEL TESTS OFAILERONS AT VARIOUS SPEEDS. II - AILERONS OF 0.20 AIRFOIL CHORD ANDTRUE CONTOUR WITH0.60 AILERON-CHORD SEALED INTERNAL BALANCE ONTHENACA66_2-216 AIRFOIL_H. G. Denaci and J. D. Bird_ June 1943 The results of the investigation of an internal-balance aileron of 0.20c and true contour 0.60 aileron chord balance tested on the NACA66_2-216_ a = 1.0 airfoil section indicated that: Increasing the airspeed up to Mach number of 0.475 noticeably increased the slope of the curves of the hinge-moment coefficient and of the airfoil CL but_ at the same time3 considerably decreased the unstalled range of the aileron.

Changesof the vent gap from 0.0025c to O.0100c had little effect on the aerodynamic characteristics_ best aerodynamics characteris- tics were obtained with a vent gap of 0.0050 chord or less.

A 0.60 aileron chord sealed internal balance on this aileron causes overbalance at zero of attack for low airspeeds_ moreover_ when the change in angle of attack due to rolling is considered_ the aileron may be overbalanced at all speeds for a large range of aileron deflections.

The internal-balance aileron tested had much better aerodynamic characteristics than the blunt nose ailerons tested on the same airfoil.

WRL 433 WIND-TUNNEL TESTS OFAILERONS AT VARIOUS SPEEDS. IV - AILERONS OF 0.20 AIRFOIL CHORD ANDTRUE CONTOUR WITH0.35 AILERON-CHORD EX- TREME BLUNT-NOSE BALANCE ONTHENACA23012 AIRFOIL_W. Letko_ T. A.

Hollingworth_ and R. A. Anderson_ August 1943 Tests were madeon an NACA23012 airfoil fitted with a 20%-chord_ true-contour aileron with 35%-chord_ extreme blunt-nose balance.

Increased airspeed increased the positive slope of the airfoil section lift curves and pitching-moment coefficient curves_ in- creased the slope of the section lift coefficient with aileron angle_ and had a negligible effect on the balance effectiveness at low angles of attack for small aileron angles. The unstalled range of aileron deflections decreased with increased speed.

Increased gap width increased the aileron balance effectiveness but decreased the slope of the curves of C L with aileron angles at low angles of attack for small aileron angles. An increase in gap width usually decreased the slope of the airfoil section lift curve but increased the positive slope of the airfoil section pitching momentcoefficient curve.

Increased balance-nose radii greatly increased the unstalled range of aileron angles and decreased the balance effectiveness for small angles.

WIND-TUNNEL INVESTIGATION OF TRIMMING TABSONA THICKENED AND WRL 435 BEVELED AILERON ONA TAPERED LOW-DRAG WING_ F. M. Rogallo and Stewart M. Crandall_ March 1943 The results of the tests of three different sized inset tabs and one attached tab on the beveled aileron of a low-drag wing indi- cated that: Of the inset tabs tested_ the tab with a chord of 50%of the aileron chord had the best characteristics for trimming. Its characteristics were the least affected by gaps and were thought to be satisfactory for trimming with any of the gap conditions tested.

The attached tab appeared to be satisfactory as a trimming device; its addition to a beveled aileron_ however_ it would increase the control operating force.

No appreciable change in aileron effectiveness resulted from deflection of the tabs as trimming devices.

Gapsat the leading edges of the tabs or ailerons were detrimental to tab characteristics for trimming_ especially for tabs of small chord.

The small-cord inset tabs showedpromise as linked balancing tabs.

Gaps did not appear to be so detrimental to the tabs for balancing as for trimming.

FULL-SCALE WIND-TUNNEL ANDFLIGHTTESTS OFA FAIRCHILD XR2K-I WRL 437 AIRPLANE WITHA ZAPFLAPANDUPPER-SURFACE AILERON-WING INSTALLA- TION_L. A. Clousing_ Robert R. Lehr_ and William J. O'Sullivan_ March 1942 A Fairchild XR2K-I airplane equipped with a wing having a full- span zap flap and upper surface ailerons was tested in a full- scale wind tunnel and in flight to determine the characteristics of the flap and the ailerons.

The zap flap_ when extended from 0° to 43.0o_ increased the CLmax of the airplane from 1.29 to 2.37.

The maximum lift and the pitching momentcoefficients were in- creased for all flap settings by an increase in the flap gap from O.Ol0c to 0.037c where c is the wing chord.

A reversal occurred in the resultant aileron hinge momentwhen the flap was deflected to the position that opened the flap gap.

Large aileron hinge-moments coefficients and excessive stick forces were measured at high aileron angles_ but these stick forces were probably_ in part_ a fault of this particular test installation.

The ailerons gave satisfactory rolling-moment coefficients.

The yawing-momentcoefficients of the upper surface ailerons were very small at all flap deflections and lift coefficients.

The flight tests showed: The ailerons produced the minimumsatisfactory rolling velocity with the flap retracted and more than the minimumsatisfactory rolling velocity with the flap extended despite excessive stretch of the control mechanismunder load.

The time lag in the response of the ailerons was so small as to be unnoticeable to the pilot.

The yawing characteristics_ although slightly irregular_ produced a small favorable yaw.

The aileron operating forces of this installation were excessive.

Because the aileron control system used in these tests had exces- sive friction and was very flexible under a load_ the results re- garding the aileron-control forces cannot be considered as con- clusive.

The results indicate the necessity for a considerable overlap in the starting and stopping of the upper-surface ailerons_ and that the control system must be designed with low friction and a small amountof stretch.

WRL 440 TESTS IN THE19-FOOT PRESSURE TUNNEL OF A 1/2.75-SCALEMODEL OF THEF4U-I AIRPLANE WITHSEVERAL BALANCED ELEVATORS_ FULL-SPAN FLAPS_ ANDDROPPABLE GASTANK_ Robert R. Grahamand C. Dixon Ashworth_ October 1942 A wind.tunnel investigation was madeto determine the aerodynamic effects of several elevators with varying amountsof balance and of outboard split flaps on a I/2.75-scale model of an F4U-I air- plane. Power-on runs were at i00 mph and power-off runs were at 260 mph.

The CLmaxfor the power-on landing approach was 6%higher with both inboard slotted flaps and outboard split flaps deflected than it was with inboard slotted flaps deflected and ailerons drooped.

The addition of the outboard split flaps had a negligible effect on the stalling characteristics and the longitudinal stability but noticeably reduced the aileron effectiveness.

WRL 441 WIND-TUNNEL INVESTIGATION OF AN NACA 23012 AIRFOIL WITHTWO SIZES OF BALANCED SPLIT FLAP, ThomasA. Harris and Paul E. Purser, November1940 An investigation was madein the NACA 7- by 10-foot wind tunnel of an NACA 23012 airfoil with a 15%chord and a 25%chord balanced split flap of the Clark Y profile.

The optimum arrangement of either of the balanced split flaps_ from consideration of maximum lift coefficient and minimumprofile- drag coefficient for take-off and climb, was a combination com- parable to the Fowler flap. The pitching-moment coefficients increased with flap deflection and with movementof the flap toward the trailing edge of the wing. Any leak between the nose of the flap and the lower surface of the wing was harmful from consideration of maximum lift coefficient, but if the gap was in- creased to form a suitable slot the maximumlift coefficient was increased. The data contained in this report is suitable for application to the design of any probable split-flap arrangement.

WRL 447 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

XI - VARIOUS LARGE OVERHANG ANDINTERNAL-TYPE AERODYNAMIC BALANCES FORA STRAIGHT-CONTOUR FLAPONTHENACA 0015 AIRFOIL, Richard I.

Sears and H. Page Hoggard_Jr._ January 1943 Force-test measurementsin two-dimensional flow were madein the NACA 4- by 6-foot vertical tunnel to determine the characteristics of several different shaped overhang-type aerodynamic balances applied to a straight-contour flap mounted on an NACA 0015 air- foil. The chord of the flap was 30%of the airfoil chord and the chord of the overhang was 50%of the flap chord. The results of tests are as follows: i. The addition of cover plates over the nose of a flap having a long overhang of sharp profile materially reduced the drag as comparedwith that of the uncovered overhang; the reduction in drag was greatest for the widest cover plates.

2. Whenthe gap at the nose of a long sharp overhang was not sealed_ the addition of wide cover plates increased the slope of the lift curve.

3. The addition of cover plates should decrease the control-free stability of an airplane with control surfaces having a long sharp-nose overhang.

4. The addition of cover plates restricted the maximum flap deflection.

5. The addition of cover plates over the nose of the flap with a long-sharp-nose overhang adversely affected the hinge-moment characteristics unless the air leak through the gap at the flap nose was sealed.

WRL 448 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

VII - A MEDIUM AERODYNAMIC BALANCE OF TWO NOSE SHAPES USED WITH A 30-PERCENT-CHORD FLAP ON AN NACA 0015 AIRFOIL, Richard I.

Sears and H. Page Hoggard_ Jr._ July 1942 Force-test measurements in two-dimensional flow were made in the NACA 4- by 6-foot vertical tunnel of the characteristics of an NACA 0015 airfoil with a balanced flap having a chord 30% of the airfoil chord and a flap-nose overhang 35% of the flap chord.

The following results were noted: i. The slope of the lift curve for the airfoil was found to be independent of the flap-nose shapes tested and decreased appre.

ciably when the gap at the flap nose was unsealed.

2. The lift effectiveness of the flap with a sealed gap was independent of the nose shapes tested.

3. When deflected in conjunction with the angle of attack_ the blunt-nose flap lost all lift effectiveness when deflected greater than 15°_ but the medium-nose flap was somewhat effective to 25 °.

When deflected in opposition to the angle of attack_ the flap with either nose shape was effective to 25 ° .

4. Unsealing the gap at the nose of the flap increased the balance effectiveness for flaps with both the blunt and the medium nose shapes.

5. The minimum profile drag of the airfoil with a blunt-nose balanced flap was the same as that for the plain flap_ but with the medium-nose balance the minimum profile-drag coefficient was increased by 0.0011.

WRL 449 WIND-TUNNEL INVESTIGATION OFAN NACA 23021 AIRFOIL WITHTWO SIZES OF BALANCED SPLIT FLAPS_ Robert S. Swansonand Marvin J. Schulden- frei_ February 1941 An investigation was madein the NACA7- by 10-foot tunnel of a large-chord NACA23021 airfoil with a 15%-chordand a 25%-chord balanced split flap of Clark Y profile. Section lift_ drag_ and pitching-moment characteristics were presented. The two balanced split flaps were comparedwith a slotted-flap arrangement developed in a previous investigation.

The results showedthat the basic airfoil had the lowest profile drag coefficients over the low lift range; the optimum arrangement of the 15%chord balanced split flap had the lowest profile-drag coefficient over the moderate lift range9 and the optimumarrange- ment of the 25%chord balanced split flap had the lowest profile- drag coefficient over the high lift range.

The Fowler arrangement of the 25%chord balanced split flap gave the highest increment of maximum lift coefficient_ about 1.82 as comparedto 1.47 for the slotted flap_ and 1.24 for the Fowler arrangement of the 15%chord balanced split flap. The optimum arrangement of the 15%chord balanced split flap from considera- tions of maximum lift coefficient was 5%ahead of the trailing edge and 3%below the chord line where the increment of maximum lift coefficient was 1.31. The slotted flap had lower pitching momentsthan either size of balanced split flaps.

WRL 450 NOTES ONTHEEFFECTS OF TRAILING-EDGE SHAPES OFLOW-DRAG AIRFOILS OF PROFILE DRAG ANDTHETRIMANDBALANCE OF CONTROL SURFACES_ W. J. Underwood_ March 1942 This report was concerned with the problem surrounding the value of adhering to the specified cusp trailing-edge shapes on low-drag airfoils as opposed to trailing edges with straight-line elements.

Comparative drag tests of a 0.20c straight faired aileron and a 0.20c cusp-type aileron were madeon a low drag airfoil (approx- imately NACA 66_2-I16). The model with the cusp-type aileron had the lower drag coefficient. The increment of change was equal to 0.0006. The data presented are not sufficiently complete for design purposes.

WRL 452 TESTS IN THENACA TWO-DIMENSIONAL LOW-TURBULENCE TUNNEL OF AIRFOIL SECTIONS DESIGNED TOHAVESMALL PITCHING MOMENTS ANDHIGHLIFT- DRAG RATIOS_ Neal Tetervin_ September 1943 Airfoil sections that have small or zero pitching-moment coeffi- cients and high lift-drag ratios were developed. The airfoil section ordinates were given in the report.

WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

WRL 454 VI - A 30-PERCENT-CHORD PLAIN FLAPONTHENACA 0015 AIRFOIL_ Richard I. Sears and Robert B. Liddell_ June 1942 Force-test measurementsin two_dimensional flow have been made in the NACA 4- by 6-foot vertical tunnel of the characteristics of a NACA 0015 airfoil equipped with a plain flap having a chord 30% of the airfo_l chord and a plain tab having a chord 20%of the flap chord. The results are as follows (the results are com- pared with those of a NACA 0009 airfoil already tested): i. The slope of the lift curve for the NACA 0015 was slightly less than that for the NACA 0009 and decreased when the gap at the flap nose was unsealed.

2. The lift effectiveness of the plain flap on the NACA 0015 was practically the sameas that of the similar flap on an NACA 0009.

3. Onboth the NACA 0009 and 0015 airfoils_ the plain flap gave a greater lift effectiveness with smaller hinge momentswith the flap gap sealed than with it unsealed. The effect was smaller for the thicker than for the thinner airfoil.

4. The flap with a sealed gap gave a smaller minimumprofile- drag coefficient than the flap with unsealed gap.

WIND-TUNNEL INVESTIGATION OFAN NACA23012 AIRFOIL WITH0.30- WRL 469 AIRFOIL-CHORD DOUBLE SLOTTED FLAP_Paul E. Purser_ Jack Fischel_ and John M. Riebe_ December1943 Tests to determine the effect of flap position and deflection on the aerodynamic characteristics of an NACA23012 airfoil with a double slotted flap having a chord 30%of the airfoil chord (0.30c) were conducted.

The use of a 0.30c double slotted flap on the NACA23012 airfoil gave a CLmaxof 3.30 which was larger than that of the 0.2566c and 0.40c single slotted flaps equal to that of the 0.30c Fowler flap_ but less than that of the 0.40c double slotted flap on the sameairfoil.

The 0.30c double slotted flap gave profile-drag coefficients that were larger than those of the 0.2566c and 0.40c single slotted flaps for CL'S between 1.2 and 2.7 and were less than those of the single slotted flaps at values of CL'S greater than 2.7; however_ over the entire lift range_ the present arrangement gave a higher profile drag than the 0.30c Fowler or 0.40c double slotted flaps.

The 0.30c double slotted flap gave negative section pitching-moment coefficients that were higher than those of the single and double slotted flaps but approximately equal to those of the Fowler flap at a given CLmax.

At high flap deflections and high CL'S _ a slight movementof the flaps from the optimumpositions sometimesresulted in relatively large decreases in lift and increases in drag.

Removingor deflecting the airfoil lower lip improved the aero- dynamic characteristics near maximumlift only slightly.

The use of a fore flap that was larger in both chord and thickness slightly increased the CLmax but also increased the section pro- file-drag and section pitching-moment coefficients.

WRL 470 WIND-TUNNEL INVESTIGATION OF A PLAINAILERON WITHVARIOUS TRAILING- EDGE MODIFICATIONS ONA TAPERED WING. III - AILERONS WITHSIMPLE ANDSPRING-LINKED BALANCING TABS_ F. M. Rogallo and Paul E. Purser_ January 1943 The results of the computations and the tests of 0.155-chord ailerons on an NACA 230-series airfoil indicated that_ for this test_ the use of ailerons with simple or spring-linked balancing tabs would reduce the high-speed stick forces to considerably less than those experienced in the use of plain scaled ailerons if the systems were designed for low maximum aileron deflections.

The use of spring-linked tabs designed to give the desired char- acteristics at high speed would reduce the variation of stick force with speed and would also cause an increase in rolling effectiveness for a given stick deflection as the speed was reduced_ relative to plain ailerons or ailerons with simple tabs.

WRL 480 A FLIGHTINVESTIGATION OF INTERNALLY BALANCED SEALED AILERONS_ W. C. Williams and H. F. Kleckner_ December1941 Flight tests were madeof a set of internally balanced sealed ailerons installed on a Ryan ST airplane. The flight tests indicated that internal aerodynamic balance in conjunction with a positive seal may be used to reduce hinge moments.

For this case an internal balance projecting of the hinge line 32.5%of the aileron chord reduced the hinge momentsby an average of 45%. The aileron effectiveness was comparable with that of other sealed ailerons that have been flight tested.

WRL 481 WIND-TUNNEL INVESTIGATION OFA PLAINAILERON ANDA BALANCED AILERON ONA TAPERED WING WITHFULL-SPAN DUPLEX FLAPS_ F. M. Rogallo and John G. Lowry_ July 1942 Duplex flaps consisted of an inboard NACA slotted flap and an outboard balanced split flap. Results indicate that the 0.58-span slotted flap provided an increment of 0.82 in maximum lift coeffi- cient_ and the 0.40-span retractable flaps over the aileron portion of the wing provided an additional increment of maximum lift coefficient of 0.22_ that is_ a total increment of 1.04 was given by the duplex-flap combination. Flap deflection over the aileron portion of the wing reduced the effectiveness of the aileron at intermediate positions of the flap but not necessarily at the final position. Estimated rates of roll and stick forces indicated that the wing arrangement tested would provide satis- factory lateral control on the assumedfighter airplane. It gives aerodynamic characteristics of flaps and aileron tested.

WRL 489 DRAG ANALYSIS OF SINGLE-ENGINE MILITARYAIRPLANES TESTED IN THE NACA FULL-SCALE WINDTUNNEL_ C. H. Dearborn and Abe Silverstein_ October 1940 Tests madeon full size models to determine what changes can be madeon existing planes to increase their top speed. The report analyzes each componentin turn and gives recommendations.

Somerules for ducts are: (I) Avoid bends in high speed sections.

(2) Use guide vanes in all the duct bends_ with rounded noses.

(3) Avoid sudden changes in duct size. Report gives allowable angles of bend. (4) Design the duct entry so that the air flow does not create pressure peaks on the external on internal lines of the duct entrance. (5) Locate duct inlets at a stagnation point if possible or design them to recover full stagnation pres- sure. (6) Do not use internal duct shutters_ use outlet shutters.

(7) Ducts should have a smooth internal surface and circular cross section when possible. (8) Duct outlets should be designed to discharge air on streamlines.

Proper design of exhaust stacks and cooling ducts can lead to full recovery of the drag loss that they produce. Air induction systems should always have ducts located at stagnation points to get maximum engine power. Intercoolers are necessary as long as blowers are inefficient. Use of intercoolers necessitates much attention to good design of the cooler because of space limita- tions and drag.

Drag considerations favor small-diameter engine installations.

Canopies and nacelles should be designed to minimize pressure peaks. Leaks on fuselage or wings or nacelles should be avoided_ as these lead to increased drag. Exhaust stacks and superchargers should be streamlined to reduce drag. Stacks should be designed to get maximum jet thrust out of the exhaust gases.

Wings should be constructed very carefully to avoid protuberances_ such as rivets and spanwise irregularities_ which will fix the transition from laminar to turbulent flow at the point of roughness and add considerably to drag. Sandedwalkways add a large drag increment_ as do aileron gaps. Canopies and all protuberances from the fuselage should have smooth curving contours_ to avoid turbulence and separation. Landing gear should be streamlined_ well faired_ or_ if retractable_ sealed to avoid leaks_ which cause a great increase in drag. Aerials should be streamlined and wires should be parallel to the flow if possible.

WRL 493 CHARACTERISTICS OF NACA 4400RSERIESRECTANGULAR ANDTAPERED AIRFOILS_INCLUDING THEEFFECT OF SPLITFLAPS_ Harry Greenberg_ January 1941 Tests were madein the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400Rseries sections which were tested in a reference. The wing was also tested with 0.2 chord split flaps_ deflected 60o_ in the center of the wing and having flap span to wing span ratios of 0.3_ 0.5_ 0.7 and 1.0_ respectively.

The numbers in the designation of the tapered wing (3-10-18) refer to taper ratio_ aspect ratio_ and root section percent thickness_ respectively. The tests were madeof the four rec- tangular airfoils of the NACA 4400Rseries (4409R_4412R_4415R_ and 4418R) with full-span 0.2 chord_ trailing-edge split flaps deflected 60° .

Measurementsof lift_ drag_ and pitching momentwere madein the variable-density wind tunnel according to standard procedure where the Reynolds numberwas 8_000_000.

Standard plots showing the characteristics of the rectangular airfoils with 0.2 chord split flaps deflected 60° were shown as figures. The section characteristics after the stall were not shown. The principal characteristics were summarizedin a table.

WRL 506 WIND-TUNNEL INVESTIGATION OFA FULL-SPAN RETRACTABLE FLAPIN COMBINATION WITHFULL-SPAN PLAINANDINTERNALLY BALANCED AILERONS ONA TAPERED WING_ R. M. Rogallo_ John G. Lowry_ and Jack Fischel_ August 1943 An investigation was madeof a 20%chord full-span retractable flap in combination with 8%chord full-span plain and internally balanced ailerons on a semispanmodel of the tapered wing of a typical fighter plane.

The results of this investigation indicated that an increment of CLmax of 1.3 may be obtained by deflecting the full span flap 30° with the flap nose about 3%below the trailing edge of the wing.

This increment was increased to 1.5 by increasing the flap deflec- tion and drooping the aileron. The pitching momentcoefficient obtained at any given C L with the flap extended was approximately the sameas that of other partial and full_span flap arrangements tested on the samewing.

The estimated aileron effectiveness was adequate in the flap- retracted condition and was increased by about 50%when the flap was extended. A reduction of aileron effectiveness of approxi- mately 40%relative to the flap-retracted condition appears un- avoidable at someintermediate flap positions. An internal balance reduced the estimated stick forces to acceptable values for all flap positions and deflections along a selected path.

It is indicated by the estimated rate of roll and the stick forces that the wing arrangement tested would provide satisfactory lat- eral control on the assumedfighter airplane.

WRL 507 INVESTIGATION OF THEBOUNDARY LAYER ABOUT A SYMMETRICAL AIRFOIL IN A WINDTUNNEL OF LOW TURBULENCE_ Albert E. yon Doenhoff_ August An extensive series of boundary-layer surveys was madeover the surface of an NACA 0012 airfoil at zero lift. The surveys were madeat Reynolds numbers of 2.675xi06_ 3.78xI06_ 5.35xi06 and 7.56x106 .

The calculated and the experimental laminar boundary_layer pro- files for an NACA 0012 airfoil were in good agreement.

Although comparative measurements of transition in flight indicate that the turbulence of the air stream of the low-turbulence tunnel was large enough to produce marked effects on transition_ the turbulence of this air stream was less than that of other NACA tunnels previously supposed to have low turbulence.

The critical Reynolds number of a sphere cannot be used as a measure of the effects of small amounts of turbulence on the flow about an airfoil.

The calculated turbulent skin-friction distribution for an NACA 0012 airfoil was in fair agreement with that found from boundary- layer surveys.

For the NACA 0012 airfoil 3 the Squire-and-Young method of cal- culating profile drag gave results in good agreement with the value determined from wake surveys.

Approximately 80% of the profile drag of the NACA 0012 airfoil was direct skin-friction drag.

WRL 509 WING-FUSELAGE INTERFERENCE - COMPARISON OF CONVENTIONAL AND AIRFOIL-TYPE-FUSELAGE COMBINATIONS_ Eastman N. Jacobs and Albert Sherman_ March 1937 Tests of wing-fuselage combinations employing an airfoil-type fuselage were made. The models were designed to simulate an existing moderate-size transport airplane of that type. The test results showed that for such sizes the airfoil-type-fuselage combination should be well faired in such a way as to eliminate the discontinuity at the ends of the fuselage, and even then will probably have to rely largely on other than basic aerodynamic considerations for its justification.

WRL 511 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

XII - VARIOUS COVER-PLATE ALIGNMENTS ONTHENACA 0015 AIRFOILWITH A 30-PERCENT-CHORD FLAPANDLARGE SEALED INTERNAL BALANCE_ H. Page Hoggard, Jr., January 1943 Force-test measurementsin two-dimensional flow were madeto determine the aerodynamic effects of changing the alignment of the cover plates on a sealed internally balanced flap. Manufac- turing imperfections in the aligmnent of the cover plates for internally balanced flaps with the airfoil contour, if large_ may have serious effects on the resultant hinge momentof a flap with a sealed internal balance.

In general, bending the cover plates in or out increased the negative slope of curves of flap hinge momentplotted against angle of attack and against flap deflection. A rudder with internal balance with the cover plates bent out an appreciable amount should have a tendency toward rudder lock in a sideslip.

Similarly_ an elevator should have a tendency toward overbalance when used in the landing attitude when the cover plates are bent out. Bending the plates in should have no serious effect other than a slight increase in hinge moment.

Bending the cover plates in or out had practically no effect on the slope of the lift curve for the airfoil.

The lift effectiveness of the flap with flap deflection and angle of attack of like sign was reduced when the cover plates were bent out at either bend location. Bending the plates in did not affect the lift effectiveness.

The increment of minimumprofile drag due to bending the plates out was appreciable and was larger when the bend location was near the cover-plate trailing edge. Within the experimental accuracy of the tests_ bending the cover plates in had no appreciable effect on the minimumprofile-drag coefficient.

WRL 513 WIND-TUNNEL INVESTIGATION OF A PLAINAILERON WITHVARIOUS TRAILING- EDGE MODIFICATIONS ONA TAPERED WING. I - AILERON WITHFIXEDINSET TABS,F. M. Rogallo and Paul E. Purser, September 1942 The results of the tests of 0.155c ailerons on an NACA230 series airfoil and the computations indicated that_ for this study_ the use of ailerons with fixed inset tabs combinedwith a suitable differential aileron linkage can reduce the maximum stick forces to about 40%or less of the forces experienced in the use of plain ailerons with an equal up and down likage. The decreases in stick forces were greater and the changes in aileron effective- ness were less for the ailerons with positive tabs than for the ailerons with negative tabs.

The results indicated that the presence of a gap at the aileron nose and also the use of initial aileron deflection to counteract the lift increment due to the deflection were detrimental to the aileron effectiveness and to the stick-force characteristics.

WRL 516 WIND-TUNNEL INVESTIGATION OF SHIELDED HORN BALANCES ANDTABSONA 0.7-SCALEMODEL OF XF6FVERTICAL TAlL SURFACE_ John G. Lowry_ JamesA. Maloney_ and I. Elizabeth Garner_ March 1944 An investigation was madeof a 0.7-scale model of the vertical tail surface of the Grumman XF6Fairplane. Tests to determine the effect on the hinge-moment characteristics of an unshielded horn_ of shielded horns of different chords_ spans_ and nose shapes_ and of trin_ning tabs of two nose shapes indicated that: The addition of the shielded horns gave a change in hinge-moment variation with angle of attack about 60%as great as unshielded horns for the samebalance coefficient. (The balance coefficient is the square root of the ratio of the product of the horn area and meanchord of the horn to the product of the rudder area and meanchord of the rudder.) For the shielded horns_ the change in hinge-momentvariation with rudder deflection was less than for the unshielded horn for horns of small balance coefficient and greater for horns of large balance coefficient. The ratio of the change in hinge-moment variation with angle of attack to change with rudder deflection was about 0.7 for the shielded horns.

For the XF6Fvertical tail surface the rate of change of hinge- momentcoefficient with rudder deflection could be reduced with shielded horns to about 50% of the unbalanced value without obtaining a positive value of the rate of change with angle of attack large enough to give steady oscillations of the airplane with free rudder.

For most tail surfaces it will be impossible to obtain a closely balanced surface by means of shielded horns and keep the rate of change of hinge moment coefficient with angle of attack near zero without the addition of some other balancing device of which the main function is to reduce the negative hinge moment due to de- flection.

The pressure-distribution tests showed that_ in general_ the medium-nosehorn gave lower peak pressures and consequently higher critical speeds than the blunt-nose horn.

The two tabs gave approximately the sameresults.

WRL 521 FLIGHTINVESTIGATION OF BOUNDARY-LAYER CONTROL BY SUCTION SLOTS ON AN NACA35-215 LOW-DRAG AIRFOILAT HIGHREYNOLDS NUMBERS_ John A.

Zalovcik_ J. W. Wetmore_and Albert E. von Doenhoffj February 1944 The results of the flight investigation of suction slots on the upper surface of the airfoil showedthat 3 with a slot spacing of about 5%of the chord_ the laminar boundary layer could be main- tained to or slightly beyond 45%of the chord_ or just about to the minimum_pressurepoint_ over a range of airplane lift coeffi- cient from 0.19 to about 0.35 with a corresponding range of Reynolds number from 30.8 to 23 million. Comparisonwith the results obtained from tests of the unslotted airfoil indicated that laminar flow at 45%of the chord represented an increase_ attributable to the effect of slots_ of at least 5%of the chord at a lift coefficient of 0.21 and a Reynolds number of 26.5 million. The corresponding reduction in the external profile-drag coefficient of the upper surface appeared to be 0.00031 and 0.00065_ respectively. These effects were obtained with an expenditure of blower power equivalent to a profile drag co- efficient of 0.00008.

In the tests with the slot spacing reduced to about 2½percent of the chord_ the maximum extent of the laminar layer was not definitely determined_ however_ it was apparently less for all test conditions than with either the 9 slot arrangement or no slots.

WIND-TUNNEL INVESTIGATION OF A PLAINAILERON WITHTHICKENED AND WRL 526 BEVELED TRAILINGEDGES ONA TAPERED LOW-DRAG WING_ Paul E. Purser and John W. McKee_May 1943 Tested 0.20 chord aileron on a tapered low-drag wing: i. Thickening and beveling the aileron trailing edge would sub- stantially reduce the high speed control forces.

2. Air leakage across the aileron nose tended to cause over- balance of the beveled ailerons at small deflections and to reduce their rolling momenteffectiveness. This loss in effectiveness was greater with the beveled aileron than with the original cusp aileron.

3. The characteristics of beveled ailerons were in general agree- ment with the characteristics obtained in previous wind tunnel and flights.

4. Thickening and beveling only one surface of the aileron gave less aerodynamic balance than thickening and beveling both surfaces and produced a large floating tendency that would allow advan- tageous use of a differential aileron linkage.

5. Tab effectiveness varied with aileron profile and in some cases was unsatisfactory.

WRL 532 A FLIGHTINVESTIGATION OF THEBOUNDARY-LAYER CHARACTERISTICS AND PROFILEDRAG OFTHENACA35-215 LAMINAR-FLOW AIRFOILAT HIGH REYNOLDS NUMBERS_ J. W. Wetmore 3 J. A. Zalovcik_ and Robert C.

Platt_ May 1941 Comparisonof the results of the present flight tests on the air- foil section with data obtained on generally similar airfoils in the original NACAlow-turbulence wind tunnel showedthat in flight the laminar boundary layer was maintained to values of Reynolds number considerably greater than the highest values that were attained in the tunnel. This result indicated that even in tunnel air streams of extremely low turbulence the effect of the residual turbulence might be appreciabl% and thereby demonstrated the necessity of continued flight research on airfoils of large scale to supplement the development work of the tunnels.

WRL 534 INVESTIGATION OF SURFACE IRREGULARITIES ONAN NACA 63(420)-416_ a = 1.0 AIRFOIL SECTION FORTHEGLENN L. MARTIN COMPANY DESIGN 195_ Albert L. Braslow_ October 1943 An investigation was madeto determine effects of riveted and piano-hinge-type skin joints.

It was found that: Any type of surface irregularities at the front spar_ however treated_ caused a substantial increase in drag.

Leakage of air through the airfoil from one surface to the other caused an additional increase in drag which may be prevented by sealing the skin joints.

Surface irregularities at the rear spar caused no significant increase in drag so long as no leakage of air through the airfoil was present.

The lowest drags at flight values of the Reynolds number for either the riveted or piano-hinge skin joints at the front spar were obtained with the riveted joints with the skin gaps filled.

The lowest drags for the piano hinges at the front spar were obtained with the hinges sealed with fabric faired to the surface of the airfoil.

No significant increase in drag resulted from the addition of an aileron slot.

WRL 544 AERODYNAMIC DATAFORA WINGSECTION OF THEREPUBLIC XF-12 AIRPLANE EQUIPPED WITHA DOUBLE SLOTTED FLAPj Jones F. Cahill_ January 1946 An investigation was carried out in the Langley 2-dimensional low- turbulence tunnels for the purpose of developing an optimum flap configuration for maximum lift on an airfoil section for the Republic XF-12 airplane equipped with a double slotted flap. Lift and flap loads were obtained at several flap deflections for two flap paths. Drag characteristics of the section with flaps re- tracted were also determined. Tests included an investigation of flap and fore flap configurations for maximum lift_ lift charac- teristics at several flap deflections for two flap paths_ and flap and fore-flap loads. The effect of Reynolds number and standard leading-edge roughness on the lift and drag characteristics were determined for several configurations.

The flap had a length of 0.238c while the fore flap had a length of 0.092c. The lift_ drag_ and flap loads were discussed.

A flap configuration was developed which was believed to be very near the optimum for maximum lift and which provided a maximum lift coefficient of 3.43 at a Reynolds number of 14 million. The maximum lift for all deflections except the best maximum lift configuration was shown to increase with Reynolds number. The maximum lift coefficient for the optimumconfiguration was shown to be approximately 0. i0 higher at 3.5 million than at 14 million.

WRL 560 SUMMARY OF AIRFOILDATA_Ira H. Abbott_ Albert E. von Doenhoff_ and Louis S. Stivers_ Jr._ March 1945 This report is a summaryof the NACAairfoil shapes through 747A415. It presents lift_ drag_ and momentcurves for each air- foil.

WRL 573 WIND-TUNNEL INVESTIGATION OF A SECTION OF THEHORIZONTAL TAIL SURFACE FORTHEBELLXP-63 AIRPLANE_ Milton B. Ames_Jr._ and H.

Page Hoggard_Jr._ August 1941 Data on the NACA 0009 airfoil and the NACA66_2X-009airfoil is given. This can be found in Theory of Wing Sections by Abbott and Doenhoff.

WR L 574 WIND-TUNNEL INVESTIGATION OF ANNACA23012AIRFOIL WITHAN 18.05- PERCENT-CHORDMAXWELL SLATANDWITHTRAILING-EDGE FLAPS_ Clarence L. Gillis and John W. McKee_October 1941 Tests were madeon an airfoil with an 18.05%chord Maxwell lead- ing edge slat and with a slotted and a split flap. The purpose was to determine the optimum slot gap of the Maxwell slat for and the aerodynamic section characteristics of the airfoil with sev- eral deflections of both types of flap. Curves of lift_ drag_ and pitching-moment characteristics for selected optimum arrangements were presented.

Effect of slot gap: Slat tested gave muchmore gradual stall than the 0.30% chord slat previously tested_ with higher _cI max but lower Clmax. Pitching momentsbecameincreasingly negative as the slot gap was increased_ indicating that the center of pressure movedrearward. The 0.1805%chord slat lost effective- ness muchmore rapidly with flap deflection than the 0.30% slat.

Whenthe slat was set at the optimum slot gap increased the pitching-moment coefficients in the high-lift range negatively for all flap deflections.

Comparisonof the profile drag characteristics: Below a lift coefficient of 0.8 the plain airfoil had the lowest profile drag.

Above a lift coefficient of 0.8 the airfoil with a slotted flap had a lower profile drag coefficient than any of the combinations with the Maxwell slat. With the optimum slot opening_ the airfoil with the slotted flap had the lowest profile drag_ the airfoil with the split flap had higher profile drag_ and the airfoil with no flap had the highest profile drag. The sameorder of the pro- file drag coefficients was noticed for the airfoil with the 0.30c slat.

Increasing the radius of the rear edge of the slot entry caused no appreciable change in the characteristics_ and a sharp corner at this point either had no effect or was detrimental. Deflecting the trailing edge of the slat increased the Clmax and decreased the profile drag and pitching moment.

WRL 613 REVIEW OFFLIGHTTESTS OF NACA C ANDD COWLINGS ONTHEXP-42 AIRPLANE_ J. Ford Johnston_ April 1943 Review of flight tests of the performance and cooling character- istics of three NACA D cowlings and of a conventional NACAC cowling on the XP-42 airplane are summarizedand compared.

The maximum speed of the XP-42 was increased by a change from a C-cowling to a D-cowling by an amount corresponding to an airplane drag coefficient reduction of 7%with the long-nose high-inlet_ velocity cowling_ 6%with the short-nose low-inlet-velocity cowling_ and 4%with the short-nose high-inlet-velocity cowling.

The engine cooling-air pressure recovery was also increased by the change so long as the inlet velocity was not too high for the diffuser used.

The use of wide-chord propeller cuffs with the D-cowling increased the pressure recovery in full-power climb by about i inch of water and improved the ground cooling_ but decreased the top speed by from I to 4 mph.

The use of a fan with the low-inlet velocity cowling raised the pressure recovery in climb by about 2½ inches of water but de- creased the top speed by from i to 4 mph.

WIND-TUNNEL INVESTIGATION OF PROFILE DRAG ANDLIFT OF AN INTER- WRL 615 MEDIATE WINGSECTION OF THEXP-51 AIRPLANE WITHBEVELED TRAILING- EDGE ANDCONTOUR AILERONS_ Frank T. Abbott_ Jr._ and William J.

Underwood_January 1943 Flight tests were madewhich tended to show that a beveled trail- ing edge aileron gave a lower profile drag than a contour aileron.

This was viewed with such suspicion that wind tunnel tests were run on scale models of the XP-51 with beveled trailing-edge aileron and contour aileron. The test justified the suspicions_ the test showedthat the profile drag of the beveled trailing edge aileron was higher than that of the contour aileron and that the beveled trailing-edge aileron was less effective per degree of deflection than the contour aileron. The report makes no mention of why the results cameout different in the flight test and the wind-tunnel test.

WRL 629 AERODYNAMIC TESTS OFAN NACA 66(215)-I16_ a = 0.6 AIRFOILWITHA 0.25c SLOTTED FLAPFORTHEFLEETWINGS XA-39 AIRPLANE_ Jones F.

Cahill_ November1944 Tests were conducted in the Langley 2_dimensional low_turbulence tunnels on a 24-inch-chord model of the NACA 66(215)-i16_ a = 0.6 airfoil with a 0.25-chord slotted flap. It was desired to obtain optimum flap pivot positions for the following conditions: (i) a high maximum lift coefficient at a high flap deflection; (2) high lift coefficients with reasonably low drags at a flap deflection of 30°_ and (3) a positive lift coefficient with low drags at a negative angle of attack for a flap deflection of 15° . These conditions were determined from a consideration of the landing_ take-off_ and strafing requirements of the airplane. Two slot entry lips were tested to find the effect of a door which closed the slot on the lower surface when the flap was retracted. Flap loads were obtained at certain configurations and the effects of external flap hinges and of the removal of the internal slot fairing skin were investigated.

Lift_ drag_ and pitching-moment as well as pressure_distribution data were obtained. All force and momentdata were corrected for tunnel-wall effect. The highest Mach numberwas 0.140.

Tests were conducted at Reynolds numbers of approximately 2.5xi06 in the 2-dimensional low-turbulence tunnel and 6x106 in the 2- dimensional low-turbulence pressure tunnel.

Tuft tests showedthat when the long slot entry lip (the slot entry lip which closed the slot on the lower surface) was in place_ the flow over the flap was stalled at deflections greater than 20o. Whenshort lip was used stalling did not occur.

Results I, Covering the slot entry with a flush door gave minimum drag coefficients lower than the no-door configuration by 0.0006 at a Reynolds number of 6_000_000 with the flap retracted.

2. The highest maximum lift coefficient measured was 2.70 and was obtained with a flap deflection of 55 ° .

3. The results indicated that the lowest drag at high lift co- efficients for the 30 ° flap deflection would be obtained at the third pivot point of the 6 investigated and shown in the report.

4. Few adverse effects were incurred as a result of removing the interior slot fairing skin provided the slot is covered by a door on the lower surface when the flap is retracted.

WR L 644 TWO DIMENSIONAL WIND-TUNNEL INVESTIGATION OF SPOILER AILERON FLAP MODEL FOR THE HUGHES XF-II AIRPLANE_ William J. Underwood and Felicien F. Fullmer_ Jr._ April 1945 The results of this investigation of a retractable spoiler aileron used as a lateral control device on an NACA 66(215)-216 (approxi- mate) airfoil section with 0.25c slotted flap indicated the follow- ing conclusions.

i. The hinge moment characteristics of the retractable spoiler aileron were greatly affected by spoiler thickness_ rear-gap size_ and bevel angle of the upper face of the spoiler. The best hinge-moment characteristics of the configurations tested were obtained with the thinnest (0,0028c) spoiler which had a 17 ° bevel angle on the upper and lower faces of the spoiler and roughness on the upper face_ the largest (0.0100c) spoiler rear gap_ and the 0.0013c spoiler forward gap.

2. The spoiler aileron was effective in producing a substantial decrease in the section lift coefficient for all negative spoilers deflections larger than -3 ° .

3. The spoiler effectiveness parameter for deflections above -i0 ° was practically unaffected by increasing the test Reynolds number from 2.5 to 6 million.

4. With the spoiler in the retracted position_ air flow through the cut-outs for the spoiler in the upper surface of the airfoil caused an increase of approximately 12% in the minimum profile- drag coefficient.

5. The increments of section pitching-moment coefficient of the airfoil produced by the spoiler aileron were less positive than those produced by a plain sealed flap of equal effectiveness.

The advantage of the smaller increments of section pitching momentassociated with spoiler ailerons with respect to the lateral-control reversal speed of an airplane_ however_may be offset by the relatively larger span required for spoiler ailer- ons.

WRL 651 WIND-TUNNEL INVESTIGATION OFA BEVELED AILERON SHAPE DESIGNED TO INCREASE THEUSEFUL DEFLECTION RANGE_ R. T. Jones and W. J.

Underwood_Apri ! 1944 The purpose of this investigation in a two-dimensional low- turbulence tunnel was to determine the general aerodynamic char- acteristics of an aileron on the XP-51 airplane and to determine its useful range.

The following three configurations were tested: --f _ (A) --( -_ (B) Aileron Shapes __ (c) Type (A) ailerons are the unmodified. Type (_ showed a somewhat greater useful range of deflections and gave slightly better control at low speed than the unmodified aileron. Likewise Type (C) improved on Type (B) in regard to range of deflection and controlability.

WR L 659 INVESTIGATION OF EXTR_E LEADING-EDGE ROUGHNESS ON THICK LOW-DRAG AIRFOILS TO INDICATE THOSE CRITICAL TO SEPARATION_ Eastman N.

Jacobs_ Ira H. Abbott_ and Milton Davidson_ June 1942 Several airfoils_ including a conventional NACA23021 and some low drag airfoils for which the thickness was increased to the point that they were considered doubtfully conservative with respect to separation_ were investigated as smooth airfoils and after the application of a standard roughness. The results showedsomeof of the airfoils to be critical to separation resulting from such flow disturbances. It is concluded_ pending further investiga- tion of separation difficulties_ that airfoil sections falling definitely within the conservative range should be used.

INVESTIGATION OF THEVARIATION OF LIFT COEFFICIENT WITHREYNOLDS WRL 661 NUMBER AT A MODERATE ANGLE OFATTACK ONA LOW-DRAG AIRFOIL_Albert E. von Doenhoff and Neal Tetervin_ November1942 An investigation of the boundary layer about the NACA66_2-216_ a = 0.6_ airfoil section was madein the NACA2_dimensional low- turbulence tunnel_ in an attempt to find an explanation for the decreased slope of the lift curve observed for someof the low- drag sections outside the low-drag range at low Reynolds numbers.

The tests consisted of boundary-layer and lift measurements through a range of Reynolds numbers from 0.9xi06 to 2.6xi06.

Changesin lift and boundary-layer characteristics were observed at an angle of attack = I0.I°_ which was chosen in order that a fairly large change of lift coefficient with Reynolds numberwould occur. This angle of attack_ however_was definitely below that for maximum lift. The velocity distributions in the boundary layer were obtained by measuring the static pressure at a point outside the boundary layer and the total pressure at several positions within the boundary layer.

The slope of the lift curve decreased with increasing Reynolds number_an indication that the effect under investigation became less pronounced as the Reynolds number increases. It is to be noted that the pressure in the separated region remains constant independent of the Reynolds number; whereas the pressures over the remainder of the upper surface decrease with increasing Reynolds number.

In order to obtain more information regarding the separated region near the leading edge_ a suspension of lampblack in kerosene was painted on the wing in each case before the tunnel was started.

It was found that the extent of the separated region decreased as the Reynolds number increased. In the case under consideration_ the turbulent boundary layer was affected by the Reynolds number in two ways. The first effect was the normal decrease in thickness of the turbulent boundary layer associated with an increase in Reynolds number. The second and more important effect in the present case was the large decrease in the initial thickness of the turbulent boundary layer where it forms just at the end of the region of laminar separation.

At higher Reynolds numbers it seems likely that the region of local separation near the leading edge will become insignificant or will completely disappear. It is to be expected then that the lift may continue to increase somewhat with increase in Reynolds number_ owing to the normal decrease in boundary-layer thickness with increasing Reynolds number_ but at a considerably lower rate.

WR L 665 ANALYSIS OF AVAILABLE DATA ON CONTROL SURFACES HAVING PLAIN- OVERHANG AND FRISE BALANCES_ Paul E. Purser and Thomas A. Toll_ May 1944 The available data on control surfaces having plain-overhang and Frise balances have been analyzed and some empirical factors that will facilitate the prediction of the characteristics of balanced control surfaces from the geometric constants have been deter- mined.

The results of the preceding correlation and analysis indicated the following general conclusions regarding control surfaces hav- ing plain-overhang or Frise balances: The effects of balance variation in changing the slope of the curve of hinge-moment coefficient plotted against control-surface deflection and in changing the lift effectiveness of the control surfaces were correlated for various models at low Mach numbers by the use of a balance factor that accounted for the size and shape of the overhang.

No correlation factor was obtained that would adequately account for all the variables which affect the slope of the curve of hinge-moment coefficient plotted against angle of attack or which affect the deflection range over which the balance is effective in reducing the slope of the hinge-moment curve.

The presence of a small gap at the nose of a plain-overhang balanced flap and of the corresponding unbalanced did not appreciably alter the differences in the slopes of the curves of hinge moment plotted against control deflection. The shape of the balance nose varied the effect of a gap at the control leading edge on the slope of the curve of hinge-moment plotted against angle of attack for plain-overhang balances. The presence of a gap at the control leading edge consistently increased the effect of overhang in increasing the control lift-effectiveness parameter.

With the open gap_ the increase in the lift-effectiveness param- eter with increase in overhang was caused by an increase in the slope of the curve of lift plotted against control-surface deflec- tion and a decrease in the slope of the curve of lift plotted against the angle of attack.

Increases in the Mach number consistently decreased the deflection range over which the balance was effective in reducing the slope of the hinge-moment curve.

WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

WRL 666 XVII - BEVELED-TRAILING-EDGE FLAPSOF0.20_ 0.30_ AND0.40 AIRFOIL CHORD ONA NACA 0009 AIRFOIL_ Vernard E. Lockwood_April 1944 Force tests in two_dimensional flow of flaps having chords 20_ 30_ and 40%of the airfoil chord and 20o_ 30o_ and 40° beveled trailing edges on an NACA 0009 airfoil were made. A com- parison of the results of the tests of models having a smooth leading edge and a sealed flap with the results for plain flaps having chords 20 and 30%of the airfoil chord on an NACA 0009 air- foil indicated that: The increased trailing-edge angle and the increased thickness near the trailing edge reduced the slope of the control-fixed lift curve.

The flap lift effectiveness was reduced by the increase of the trailing-edge angle and hence was less than that for the corres- ponding plain flaps.

An increase in the trailing edge angle generally gave a more positive slope to the rate of change of hinge-moment coefficient with angle of attack and with flap deflection. The hinge-moment characteristics also showedthat_ as the flap chord was increased_ the bevel angle that gave the greatest reduction of hinge moments was increased.

Aerodynamic centers of lift that result from varying the angle of attack and varying the flap deflection were generally shifted forward by an increase of the trailing-edge angle.

Opening the gaps at the nose of the flaps with a 30o beveled trailing edge decreased the slope of the control-fixed lift curve and decreased the flap effectiveness. The slopes of the curves of hinge-moment coefficient against angle of attack and flap deflection were more positive for the flap with open gap than with the sealed gap. The drag was generally higher for flaps with open gaps than with sealed gaps.

Fixing the transition at the leading edge of the airfoil by the addition of roughness had an effect on the lift and hinge moment similar to that caused by opening the gap. The maximum lift was reduced by addition of the rough leading edge.

The asymmetric flap with 20° bevel on the upper surface and I0 ° bevel on the lower surface gave negative hinge momentsat zero angle of attack and zero flap deflection. The hinge-moment- coefficient curve as a function of angle of attack at zero flap deflection had a positive slope at negative _'s and a positive slope at positive _'s greater than 3o.

WRL 668 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS XV - VARIOUS CONTOUR MODIFICATIONS OFA 0.30-AIRFOIL-CHORD PLAIN FLAPONAN NACA 66(215)-014 AIRFOIL_Paul E. Purser and John M.

Riebe_ December1943 Tests were madeof the NACA 66(215)-014 airfoil equipped with true-contour 3 straight contour_ and beveled-trailing-edge flaps having chords equal to 30%of the airfoil chord. The effects that increasing the trailing_edge angle had in decreasing the lift over the airfoil trailing edge were not significantly different from the effects previously noted on conventional airfoils.

The slope of the airfoil lift curve was largest with the sealed true-contour flap and decreased as the gap at the flap nose was opened_ as the trailing_edge angle was increased, and as roughness was added to the airfoil leading edge.

The slope of the lift curve with controls free (zero flap hinge moment) generally increased as the trailing edge angle increased and as roughness was added to the airfoil leading edge. The effect of the gap at the hinge line varied with trailing-edge angle and with the addition of roughness to the airfoil leading edge.

The effectiveness of the flap in producing lift was greatest with the true-contour flap and generally decreased as the gap at the flap nose was openedj as the trailing-edge angle was increased_ and as roughness was added to the airfoil leading edge.

The slope of the curves of the hinge momentplotted against angle of attack at 0° flap deflection and small angles of attack was approximately zero for the straight-contour flap_ negative for the true-contour flap_ and positive for the beveled-trailing- edge flap. The negative slopes of the hinge momentsplotted against flap deflection for all three flap contours decreased as the trailing-edge angle increased, as roughness was added to the leading edge_and_ for the straight-contour and beveled-trailing edge flaps_ as the gap at the flap nose was unsealed.

Whenthe lift was varied by changing the angle of attack at zero flap deflection_ the aerodynamic center of the airfoil with a sealed gap movedforward as the trailing edge angle was increased.

Unsealing the gap had little effect on the aerodynamic center; whereas the addition of leading-edge roughness movedthe aero- dynamic center forward I to 2%of the airfoil chord. At constant angle of attack the aerodynamic center of lift caused by flap deflection also tended to move forward as the trailing-edge angle was increased. Unsealing the gap or adding roughness at the air- foil leading edge tended to move the aerodynamic center rearward for the true-contour flap and forward for the beveled trailing edge flap.

LIFT ANDDRAG TESTS OF THREE AIRFOILMODELS WITHFOWLER FLAPS WRL 677 SUI_IITTED BYCONSOLIDATED AIRCRAFT CORPORATION_ Ira H. Abbott and Harold R. Turner_ Jr._ December1941 Lift and drag tests were madein the Langley two-dimensional tunnel of three airfoil models. The models represented intermediate sections on alternative wings of the XB-32 airplane and were equipped with 0.3c Fowler flaps.

The three alternative wings were: i. A Davis wing.

2. A wing obtained by adding a glove to the Davis wing with a forward extension of the leading edge.

3. A wing with the NACA65_2-221_ a = i section at the root and the NACA66_2X-416_a = 0.6 section at the tip.

The models were tested with various flap deflections up to 40° .

The Reynolds numberwas about 6x106. Lift curves and profile drag curves were plotted.

TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF SIX AIRFOIL SECTIONS WRL 681 FORTHEWING OF THEVEGA XP2V-I AIRPLANE_ Felicien F. Fullmer_ Jr._ October 1945 No one airfoil was superior in all respects to any other. Addi- tion of roughness to leading edge of plain airfoils produced marked separation effects and resultant increases in drag coeffi- cients of sufficient magnitude that the airfoils were considered to be unconservative sections_ with the exception of the NACA2418 and the Lockheed D-12A. The maximum lift coefficient for flap deflection could be appreciably increased by removing the flap gap seal.

dc I Range of lift Airfoil a_rg- Clmax Cdmin for low drag Cma. c.

o NACA 652-515 (modified) a=l.0 0.108 1.655 0.0043 0.250 to 0.740 -0.086 Lockheed D-12A 0. 109 1.555 0.0047 0.500 to 0.840 -0.059 1.460 0.0046 -.160 to 0.650 -0.47 NACA 65(318 ) -419 0.112 a=l.0_ cli=0.5 a=0.8_ Cli=-0.5 a=O. 5_ cti--0.4 Lockheed D-20B 0. 103 1.330 0.0048 -0.060 NACA 2418 0. I03 1.475 0.0068 ............... 0.044 Vega (modified) 0.098 1.440 0.0053 -0.051 WR L 693 WIND-TITNNEL INVESTIGATION OF AN NACA 23012 AIRFOIL WITH A 30- PERCENT-CHORDMAXWELL SLAT AND WITH TRAILING-EDGE FLAPS_ John G.

Lowry and John W. McKee_ June 1941 An investigation was made in the NACA 7- by 10-foot wind tunnel of an NACA 23012 airfoil with a 30-percent-chord Maxwell leading_ edge slat and with a slotted and a split flap. The purpose of the investigation was to determine the optimum slot gap of the Maxwell slat for_ and the aerodynamic section characteristics of_ the airfoil with several deflections of both types of flap. Curves of lift_ drag_ and pitching-moment characteristics for selected optimum arrangements were presented. The leading-edge-slots were disadvantageous because they increased the drag_ but they were advantageous where ruggedness and simplicity are essential.

Test conditions: Dynamic pressure = 16.37 psf v = 80 mph RNef f = 3.5xi06 Sufficient slot gaps of the Maxwell slat were tested with most flap deflections to determine the trend of the characteristics and the optimum slot gap for maximum angle of attack at the stall and for maximum lift. When the slotted flap was fully retracted the flap slot gap was sealed and faired to the basic airfoil con- tour as recon_nended in one of the references.

Effects of Slot Gap on Plain Airfoil: The maximum section lift coefficient increased from 1.55 at _c = 15.3 ° for the plain imax airfoil to 2.20 at _c = 25.2 ° for the airfoil with a 0.30c Maxwell slat. imax The pitching-moment coefficient becameincreasingly negative as the slot was opened_ indicating that the center of pressure moved rearward. The slope of the lift curve over the positive lift range remained practically constant_ and the drag coefficient increased slowly in the range above cl = 0.6 as the slot was opened.

Effect of Slot Gap with Various Configurations: In every case the optimum slot gap increased the angle of attack for maximum lift coefficient approximately I0 °. Opening the slot to the optimum gap increased the pitching-moment coefficient negatively an average of about 0.04 over the high lift range for all flap de- flections.

Comparison of Profile Drag: The plain airfoil had the lowest profile drag for lift coetficients below 0.9. Opening the gap to 0.40c gave slightly higher profile drag over the entire range.

The 0.20c split flap with the 0.035c slot gap had considerably higher profile drag than the corresponding slotted flap combina- tion above c I = 1.2.

For the arrangements tested a slot gap of 3.5 to 4 percent of the wing chord gave the greatest increase in maximum lift coefficient and angle of attack at the stall.

SOME LIFT AND DRAG MEASUR_ENTS OF A REPRESENTATIVE BOMBER NACELLE WR L 695 ON A LOW-DRAG WING_ Macon C. Ellis_ Jr._ May 1942 Tests of a representative bomber nacelle on a low-drag wing were made in the NACA 2_dimensional tunnel. A 1/10-full-scale model was used of a proposed two-engine bomber. Drag measurements were obtained by making wake surveys at a series of spanwise stations.

It was concluded that unless the lift disturbance due to the nacelle on an NACA 66_2-216 airfoil was sufficient to cause marked adverse effects on the induced drag_ the drag and interference of the nacelle tested may be considered small.

SOME LIFT AND DRAG MEASUR_ENTS OF A REPRESENTATIVE BOMBER NACELLE WR L 696 ON A LOW-DRAG WING - II_ Macon C. Ellis_ Jr._ September 1942 This report is the same kind of report as L-695 except that this report tests a different bomber nacelle with the same low-drag wing. Results showed the drag and interference of the nacelle on the low-drag wing to be small.

WIND-TUNNEL INVESTIGATION OF A LOW-DRAG AIRFOIL SECTION WITH A WR L 697 DOUBLE SLOTTED FLAP_ Seymour M. Bogdonoff_ September 1943 Tests of a 0.309-chord double-slotted flap on an NACA 65_3-I18_ a = 1.0 airfoil section have been made in the NACA 2-dimensional low-turbulence tunnel and the NACA 2-dimensional low-turbulence pressure tunnel. The purpose of the investigation was to deter- mine the lift, drag, and pitching-moment characteristics for a range of flap deflections. The results of tests of low-drag airfoils equipped with plain, split, or slotted flaps were pre- sented in reference I. The results of references 2 and 3 show that, on conventional airfoils, the highest lifts have been obtained with large-chord venetian-blind and double-slotted flaps. The present investigation uses double slotted flaps.

Section lift coefficients were obtained by measurementsof the lift reaction on the floor and ceiling of the tunnel, and section drag coefficients were obtained by the wake-survey method.

It was found that the double-slotted flap tested gave lift coeffi- cients higher than those that have been obtained on NACAlow-drag airfoils with plain, split, or slotted flaps and did not affect the low-drag characteristics of the wing with the flap retracted.

The combination tested also offered low drag and moderate lift for the cruising condition and fairly low drag and high lift for take-off and climb conditions. The lift coefficients obtained with the 0.309-chord double-slotted flap were almost as high as those obtained with larger-chord venetian-blind and double-slotted flaps on conventional airfoils of approximately the samethick_ ness as the low-drag airfoil tested. The high lift coefficients obtained with the 0.309-chord double-slotted flap were accompanied by high pitching moments, which were comparable to those obtained with other high lift devices giving similar maximum lift coeffi- cients.

WRL 698 EFFECTS OFA TYPICALNACELLE ONTHECHARACTERISTICS OF A THICK LOW-DRAG AIRFOIL CRITICALLY AFFECTED BYLEADING-EDGE ROUGHNESS_ MaconC. Ellis, Jr., April 1943 Tests were made to study the effects of a typical nacelle on the characteristics of a thick low-drag airfoil which was shown from previous tests to be subject to separation difficulties resulting from leading edge roughness_ that is, the airfoil with roughness had been shown to have sharp drag increases at moderate angles of attack. This report is a follow-up to reports L-695 and L-696 where bomber nacelles were tested on a low-drag wing to test their lift and drag characteristics. The present investigation was madeto study the effects of a typical nacelle on one of the airfoils that had been shown to be unconservative with respect to leading-edge roughness. Tests of the smooth wing and of the wing with leading-edge roughness were madeboth with and without the nacelle and the results were presented for comparison. For the tests, the nacelle was mounted on an NACA65_2-422, a = 1.0 airfoil.

It was found that unconservative airfoil sections of the type tested appeared to show less serious drag increases with nacelle 48O interference than with leading-edge roughness; the standard leading-edge roughness may consequently be considered the more satisfactory meansof judging such airfoils.

WRL 701 TESTOF NACA 66_2-I16_ a = 0.6 AIRFOIL SECTION FITTEDWITHPRES- SURE BALANCE ANDSLOTTED FLAPSFORTHEWINGOF THEXP-63 AIRPLANE_ William J. Underwoodand Frank T. Abbott_ Jr._ May 1942 Tests were madein the Langley 2-dimensional low_turbulence pressure tunnel of a model of the NACA66_2-I16_ a = 0.6 airfoil section representing the root section of the wing for the XP-63 airplane. Three things were investigated: (a) Lift_ drag_ and flap hinge-moment characteristics for the internal balanced flap.

(b) Lift_ drag_ and flap hinge-moment characteristics for the modified internal balance flap.

(c) Lift and drag characteristics for the slotted flap.

Lift and drag measurementswere madeby methods described in reference I. The flap hinge momentswere obtained from pressure- distribution measurementsby integrating the normal and chordwise pressure-distribution diagrams_ the pressures being plotted against the orifice projections on the flap chord line and a line perpendicular to the chord line.

Internal Balance Flap: It was found that for a flap deflection of 15°_ the hinge moments for the 0.0052c w gaps were larger than for the original gaps (cw = chord of the wing); however_ for a flap deflection of 45 ° there was very little change in the hinge moments. Results also showed the hinge moment for the flap at an angle of attack of 3° to be larger for the sealed condition than for the no-seal condition. The maximum lift was little affected either by small changes in the gap between the slot covers and flap_ or by removing the sealing curtain. With the original con- figuration for the internal balance flap_ results show that at a flap deflection of 15 degrees in the low-drag range_ a small de- crease in profile drag resulted from increasing the gap on the upper surface to 0.0052c w.

Modified Internal Balance Flap: The lift characteristics of the model with either the internal balance flap or the modified flap were about the same. The profile drag at a flap deflection of i0° with the modified flap was slightly higher than for the internal balance flap in the low drag range.

Slotted Flap: It was apparent for good flap characteristics that the slotted flap be designed to include a door to cover the slot in the retracted position for low drag and to deflect about the bottom hinge location with the slot open for maximum lift.

Although higher maximum lift coefficients were obtainable with the slotted flap tested than with the plain flap_ comparatively little gain was shownby the slotted flap unless a low flap hinge point was used.

WRL 702 WIND-TUNNEL INVESTIGATION OF A REVISED HORIZONTAL TAIL SURFACE FORTHEGRUMMAN TBF-I AIRPLANE_ John W. McKeeand Robert B.

Liddell_ February 1943 This report dealt with reducing hinge momentsof control surfaces.

An investigation was undertaken to determine if a horizontal tail surface with a large overhang would reduce the high stick forces in maneuvers that the airplane had with the original horn-balance elevator_ without appreciably affecting the longitudinal stability characteristics of the airplane. Results showedthat such a modification of the tail leads to reduced hinge moments and longitudinal stability was unaffected. The tab-elevator deflection ratio had a large effect on the hinge momentdue to elevator deflection and a small effect on the hinge momentdue to angle of attack.

WRL 704 TESTS OF FOUR MODELS REPRESENTING INTERMEDIATE SECTIONS OF THE SB-33 AIRPLANE INCLUDING SECTIONS WITHSLOTTED FLAPANDAILERONS_ Ira H. Abbott_ June 1942 Data presented is only general and is now conTnon knowledge.

WRL 708 ADDITIONAL POWER-ON WIND-TUNNEL TESTS OF THEI/8-SCALE MODEL OF THEBREWSTER F2A AIRPLANE WITHFULL-SPAN SLOTTED FLAPS_ John G.

Lowry_ October 1941 Tests were conducted in the wind tunnel on the i/8-scale model of the Brewster F2A airplane to determine the angle of attack of horizontal tail and the elevator angles required for trim with flaps down. The i/8-scale model of the Brewster F2A airplane with the modified wing and full-span slotted flaps was the sameas was used for the tests reported in reference i.

The effect of changing from the three-blade propeller (D = 1.36 ft) used in reference I with _ = 30° to the two-blade propeller (D = 1.54 ft) used in the subject tests with _ = 20° increased the slope of the pitching-moment-coefficient curve a small amount.

There was an increase in lift largely due to a small variation in flap setting and angle of attack. The variation in resultant drag was probably caused by a slight variation in propeller rpm. There was a decrease in longitudinal stability with up-elevator deflec_ tions. The elevator angles for trim were given in the figure on the back for the model with 1/2 rated power_ the flaps deflected_ and the landing gear extended. The angles for trim were 1½ ° to 2° more positive than the values given in reference I (Power-On Wind-Tunnel Tests of the I/8-Scale Model of the Brewster F2A Airplane with Full-Span Slotted Flaps_ NACA MR_8/21/41). The angle of attack of the horizontal tail was shown in a figure also for the model with flaps deflected and landing gear extended for both ½ rated power and windmilling propeller.

An analysis of the subject data indicated that a larger horizontal tail is desirable for the airplane with full-span slotted flaps.

0 0 U -4 -8, _I_ ' I I I I L ' 0 .4 .8 I_ 1.6zo z.

For Trim with / 0 Windmil ling / m J f -4 -8 .____ Power J , I t J. J ,8 1.6 2.4 C L Landing Gear is Extended WRL 736 AERODYNAMIC CHARACTERISTICS OF SEVERAL MODIFICATIONS OF A 0.45- SCALE MODEL OFTHEVERTICAL TAlL OF THECURTISS XP-62 AIRPLANE_ John G. Lowry_ ThomasR. Turner_ and Robert B. Liddell, July 1946 A 0.45-scale model of the Curtiss XP-62 vertical tail surface mounted on a stub fuselage was tested in the Langley 7- by lO- foot tunnel. The aerodynamic characteristics of the vertical tail with a plain rudder_ two amountsof overhang and an internal balance were presented. Tab characteristics on the plain rudder were also presented. The balance arrangements tested consisted of a plain rudder_ a mediumoverhang_ a large overhang_ and an in- ternal balance.

The plain rudder and overhang balances were tested both sealed and unsealed. The hinges_ however_were not completely sealed.

For one series of tests_ 0.013-inch-diameter transition wires were placed at the 10-percent-chord point along the vertical surface for the plain rudder VI4R14 (rudder designation number) and around the fuselage just back of the leading-edge radius.

Dynamicpressure = 16.37 psf_ V = 80 mph_ RNef f = 2_464_000 Jet-boundary corrections were applied.

The lift characteristics_ hinge moments_tab characteristics_ and effects of transition were discussed.

Results I. The internally balanced and overhang balanced rudders that have about the samebalance area had about the samehinge-moment characteristics throughout the angle-of-yaw and rudder-angle range.

2. Sealing the nose of the overhang balance increased the rudder effectiveness in producing lift_ the greater increase being ob- tained for intermediate balance size.

3. Completely sealing the balance of the internally balanced rudder resulted in lower hinge momentsand higher lift effective- ness than were obtained with the hinges unsealed.

4. The results of the tab tests indicated that the tab was effec- tive at least to tab angles of ± 20° over the rudder-deflection range_ except for the case of large positive angles of attack combinedwith large negative rudder deflections.

5. Fixing transition shifted all of the curves slightly and reduced the value of Ch6 r over the small rudder-deflection range and,in general_ reduced the hinge momentsover mose of the angle _Ch r of attack and rudder-deflection range where Ch8 r = (_-_--r)o_=_St=0 • TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF TWO NACA LOW-DRAG WRL 746 AIRFOIL SECTIONS EQUIPPED WITHSLOTTED FLAPSANDA PLAIN NACA LOW-DRAG AIRFOIL SECTION FORXF6U-I AIRPLANE_ LawrenceK. Loftin_ and Fred J. Ric% Jr._ January 1946 The results of a two-dimensional wind-tunnel investigation of two NACA 65-series airfoil sections of approximately 14%and 13% thickness and equipped with 25.92%airfoil chord and 33.62% air- foil chord slotted flaps_ respectively_ and a plain airfoil section indicate: The optimum flap deflection for maximum section C L was 40° for both of the airfoils equipped with slotted flaps.

The highest values of the CLmaxobtained were 2.63 for the 14% thick section with the 25.92%airfoil chord slotted flap_ and 2.80 for the 13%thick airfoil section with the 33.62% airfoil chord slotted flap.

At a Reynolds number of 9xlO6 the use of a 4° cruising flap de- flection caused the lift coefficient corresponding to the upper limit of the low drag range to increase from 0.3 to 0.4 for the root section and from 0.35 to 0.5 for the intermediate section.

On both airfoils the increment in minimumdrag coefficient caused by the 4° flap d_flection was approximately 0.001 at a Reynolds numberof 9.0x10v.

AN EXPERIMENTAL INVESTIGATION OFFLOW CONDITIONS IN THEVICINITY WRL 747 OF AN NACA Ds-TYPECOWLING_ Robert W. Boswinkle_ Jr._ and Rosemary P. Bryant_ August 1946 An investigation was conducted to determine the flow conditions in the vicinity of an NACA Ds-type cowling. Data was obtained for inlet velocity ratios ranging from 0.23 to 1.02 and for angles of attack from 0° to I0°.

The local airspeeds and flow directions had appreciably gradients in the region of the propeller shanks.

The propeller with thin airfoil type shanks caused higher total pressures and larger angles of flow rotation at the cowling inlet for the high-speed and climb flight conditions than the propeller with thick oval shanks.

At a constant blade-shank angl% the changes of flow rotation and total pressure rise caused by changes in advance-diameter ratio were smaller for the propeller with thick oval shanks than for the 48_ propeller with thin airfoil-type shanks for the complete operating range of inlet-velocity ratio.

The magnitude of the change of flow rotation in the inlet was such that contravanes would be required upstream of a fan in- stalled in the inlet of this cowling.

WR L 752 DRAG MEASUREMENTS AT HIGH REYNOLDS NUMBERS OF A 100-1NCH-CHORD NACA 23016 PRACTICAL CONSTRUCTION WING SECTION SUBMITTED BY CHANCE VOUGHT AIRCRAFT COMPANY_ Albert E. von Doenhoff and Robert J.

Nuber_ June 1944 Drag measurements were made over range of Reynolds numbers from approximately 4 to 68 million: I. Above a Reynolds number of about 25 million_ the changes in surface condition of the model had more effect on the drag co- efficient than changes in the Reynolds number.

2. Extrapolation formulas based on the turbulent skin friction drag of smooth flat plates tend to give too low values of the drag coefficient at high Reynolds numbers when applied to airfoils having surfaces comparable to those of the model investigated in this test.

WR L 777 TESTS OF A 0.1475c AILERON WITH A TAB ON LOW-DRAG SECTION FOR CURTISS XP-60 AIRPLANE IN THE LOW-TURBULENCE TUNNEL_ A. E. von Doenhoff and W. J. Underwood_ November 1941 Preliminary 2-dimensional tests of the hinge-moment characteris- tics of a 0.1725c internally balanced aileron on the XP-60 wing section indicated that more internal balance would be required if light stick forces were to be obtained at high speeds.

The simple leading tab had some advantages over the plain aileron and was suitable for use when extreme aileron travel at high speed was not necessary. If low hinge moments are required with large aileron deflections_ a geared arrangement such that the tab changes as the aileron is deflected to lighten the load appeared to be satisfactory from the aerodynamic point of view.

WR L 779 WIND-TUNNEL TESTS OF THE I/9-SCALE MODEL OF THE CURTISS XP-62 AIRPLANE WITH VARIOUS VERTICAL TAlL ARRANGEMENTS_ I. G. Recant and Arthur R. Wallace_ July 1943 Tests were made on a 1/9 scale model of an XP-62 to determine the directional stability and rudder control characteristics.

With take-off power and flaps deflected_ the modelj with rudder freej showed reversal of yawing moments at large angles of yaw for all the vertical tails tested. The addition of a proper dorsal fin improved this condition so that all vertical tails were satisfactory in this respect at least to 40° yaw.

Directional stability_ with flaps neutral and rudder fixed_ at small angles of yaw was obtained for all tails tested except the original tail (no balance horn) (also next-to-largest rudder area) which had very low or zero stability. This tail was con- sidered unsatfsfactory. Whenflaps were deflected and with power onj all tails gave satisfactory stability. The smallest tail had the least rudder area and largest aspect ratio and gave satisfactory weathercock stability.

All of the vertical tails tested had satisfactory rudder effectiveness for the flight conditions for which they were tested_ and it was believed the tails tested would have satis- factory rudder effectiveness for all normal flight conditions.

This situation results partly from the fact that_ because of the dual rotation propeller_ there are no asymmetric yawing moments at zero yaw which necessitate larger rudder deflections for trim.

Sufficient rudder control to overcome the adverse aileron yawing momentswas applied by all the vertical tails. Probably the most severe rudder requirement in the present case is the spin recovery requirement and any requirement which may be madeas to cross-wind take-offs and landings.

Pedal forces in sideslips were undesirably large for someof the tails but may be easily reduced. The rudder with the bevel trail- ing edge gave a reversal in pedal forces at small angles of yaw.

EFFECTS OFPROPELLERS ANDOF VIBRATION ONTHEEXTENT OF LAMINAR WRL 784 FLOW ONTHENACA27-212 AIRFOIL_Manley J. Hood and M. Edward Gaydos, October 1939 The effects of propellers and vibration on the extent of laminar flow on the NACA27-212 airfoil were investigated by testing the airfoil in conjunction with a tractor and a pusher propeller and with a mechanical vibrator. 6The Reynol_s numbers of the investigation rangedrfrom 3.5xi0 to 7.6xI0 v for the propeller tests and to 10.3x10b for the vibration tests.

The tractor propeller caused transition on the NACA27-212 airfoil to move from approximately midchord to a position near the leading edge_ the accompanyingincrease in drag probably exceeded i00% for this airfoil. The corresponding drag increase for the NACA 0012 airfoil would be approximately 25%because this airfoil normally has a less extensive boundary layer.

The effect of the location of the transition point of a pusher propeller at 0.20% chord behind the airfoil were inconsequential.

The largest vibration amplitude of the airfoil as a whole_ 0.094 inch at a frequency of 1650 cycles per minut% had no measurable effect on the laminar flow over the airfoil.

Not Applicable NACA Wartime Reports WRA 6 FLIGHT TESTS OF A PURSUIT AIRPLANE FITTED WITH AN EXPERIMENTAL BELLOWS-TYPE BOB WEIGHT, John R. Spreiter and James M. Nissen, October 1944 WRA 12 THE EFFECT OF WALL INTERFERENCE UPON THE AERODYNAMIC CHARACTER- ISTICS OF AN AIRFOIL SPANNING A CLOSED-THROAT CIRCULAR WIND TUNNEL, W. G. Vincenti and D. J. Graham, June 1945 WRA 13 MEASUREMENTS IN FLIGHT OF THE PRESSURE DISTRIBUTION ON THE RIGHT WING OF A P-39N-I AIRPLANE AT SEVERAL VALUES OF MACHNUMBER, L. A. Clousing, W. N. Turner, and L. S. Rolls, April 1945 WRA 15 MEASUREMENT OF FREE WATER IN CLOUD UNDER CONDITIONS OF ICING, J. K. Hardy, October 1944 WRA24 AN INVESTIGATION OF 0.15-CHORD AILERONS ON A LOW-DRAG TAPERED WING AT HIGH SPEEDS, E. V. Laitone, September 1944 WRA 42 COMPRESSIBLE POTENTIAL FLOW WITH CIRCULATION ABOUT A CIRCULAR CYLINDER, M. A. Heaslet, January 1944 WRA50 AN INVESTIGATION OF THE CHARACTERISTICS OF A PROPELLER ALCOHOL FEED RING, C. B. Neel, Jr., June 1944 WRA57 COMPARISON OF THE ENERGY METHOD WITH THE ACCELEROMETER METHOD OF COMPUTING DRAG COEFFICIENTS FROM FLIGHT DATA, Thomas L. Keller and Robert F. Keuper, October 1945 WRA61 FLIGHT INVESTIGATION OF THE VARIATION OF DRAG COEFFICIENTS WITH MACH NUMBER FOR THE BELL P-39N-I AIRPLANE, W. E. Gasich and L. A.

Clousing, May 1945 WRA62 CORRELATION OF THE DRAG CHARACTERISTICS OF A P-51B AIRPLANE OBTAINED FROM HIGH-SPEED WIND-TUNNEL AND FLIGHT TESTS, J. M.

Nissen, B. L. Gadeberg, and W. T. Hamilton, February 1945 WRA63 WALL INTERFERENCE IN A TWO-DIMENSIONAL-FLOW WIND TUNNEL WITH CONSIDERATION OF THE EFFECT OF COMPRESSIBILITY, H. J. Allen and W. G. Vincenti, December 1944 WRA64 A FLIGHT INVESTIGATION OF FUSELAGE STATIC-PRESSURE-VENT AIRSPEED INSTALLATIONS, Richard Scherrer and Lewis A. Rodert, November WRA65 INVESTIGATION OF DIVING MOMENTS OF A PURSUIT AIRPLANE IN THE AMES 16-FOOT HIGH-SPEED WIND TUNNEL, A. L. Erickson, October 1942 WRA66 WIND-TUNNEL INVESTIGATION OF DEVICES FOR IMPROVING THE DIVING CHARACTERISTICS OF AIRPLANES, A. L. Erickson, April 1943 WRA67 HIGH-SPEED AERODYNAMIC CHARACTERISTICS OF A FOUR-ENGINE TRANS- PORT AIRPLANE AS DETERMINED FROM TESTS OF A 0.075-SCALE MODEL, R. H. Barnes, January 1944 WRA69 HIGH-SPEED WIND-TUNNEL TESTS OF A 1/14-SCALE MODEL OF A FOUR- ENGINE CARGO AIRPLANE, W. T. Hamilton, February 1943 WRA 72 THE HIGH-SPEED CHARACTERISTICS OF SEVERAL FLAPS AND SPOILERS ON THE UPPER SURFACE OF THE HORIZONTAL STABILIZER OF A MODEL OF A RADIAL-ENGINE PURSUIT AIRPLANE, L. E. Boddy, January 1946 WRA 75 HIGH-SPEED WIND-TUNNEL TESTS OF A TWIN-FUSELAGE PURSUIT AIRPLANE, J. L. Anderson and V. B. Tkac, April 1946 WRA76 THE EFFECT OF MACH NUMBER ON THE AERODYNAMIC CHARACTERISTICS OF A SINGLE-ENGINE PURSUIT AIRPLANE AS DETERMINED FROM TESTS OF A I/3-SCALE MODEL, Robert C. Robinson and Henry Jessen, May 1945 WRA 82 HIGH-SPEED AERODYNAMIC CHARACTERISTICS OF A FOUR-ENGINE BOMBER AIRPLANE AS DETERMINED FROM TESTS OF A 0.075-SCALE MODEL, R. H.

Barnes, January 1944 WRA 83 HIGH-SPEED WIND-TUNNEL TESTS OF SEMISPAN HORIZONTAL TAILS WITH FABRIC-COVERED AND METAL-COVERED ELEVATORS FOR A BOMBER AIRPLANE, A. L. Erickson and W. H. Nelson, December 1944 WRA89 AERODYNAMIC CHARACTERISTICS OF A I/8-SCALE POWERED MODEL OF A HIGH-SPEED BOMBER WITH A DUAL PUSHER PROPELLER AFT OF THE EMPENNAGE, James A. Weiberg and Alfred W. Schnurbusch, October WRA 90 THE EFFECTS OF A HIGHLY CAMBERED LOW-DRAG WING AND OF AUXILIARY FLAPS ON THE HIGH-SPEED AERODYNAMIC CHARACTERISTICS OF A TWIN- ENGINE PURSUIT AIRPLANE MODEL, V. M. Ganzer, February 1944 WRA91 HIGH-SPEED WIND-TUNNEL TESTS OF A I/6-SCALE MODEL OF A TWIN- ENGINE PURSUIT AIRPLANE, V. M. Ganzer, December 1942 WRA93 FLYING QUALITIES OF A TWIN ENGINE PATROL AIRPLANE AS DETERMINED FROM WIND TUNNEL TESTS, Victor I. Stevens, Jr. and George B.

McCullough, October 1943 WRA94 WIND-TUNNEL INVESTIGATION OF A 1/20-SCALE POWERED MODEL OF A FOUR-ENGINE TRANSPORT AIRPLANE, V. I. Stevens, W. M. Douglas, and J. B. Dods, Jr., May and July 1944 WRE56 AN ELECTRONIC INDICATOR FORANGULAR VELOCITY ANDACCELERATION, Richard P. Krebs, August 1944 WRE 280 AERODYNAMICS OFTHECARBURETOR AIR SCOOP ANDTHEENGINE COWLING OF A SINGLE-ENGINE TORPEDO-BOMBER-TYPE AIRPLANE, John K.

Kuenzig and HermanPalter, June 1946 WRL 1 WIND-TUNNEL CALIBRATION ANDCORRECTION PROCEDURES FORTHREE DIMENSIONAL MODELS, R. S. Swansonand C. L. Gillis, October WRL NUMERICAL EVALUATION OFTHEWAKE SURVEY EQUATIONS FORSUB- SONICFLOW INCLUDING THEEFFECT OF ENERGY ADDITION,D. D.

Baals and M. J. Mourhess, November1945 WRL COMPARISONS OFMETHODS OFCOMPUTING BENDING MOMENTS IN HELI- COPTER ROTOR BLADES IN THEPLANE OF FLAPPING, J. E. Duberg and A. R. Luecker, August 1945 WRL 13 CHARTS OF PRESSURE, DENSITY,ANDTEMPERATURE CHANGES AT AN ABRUPT INCREASE IN CROSS SECTIONAL AREA OF FLOW OF COMPRES- SIBLEAIR, U. T. Joyner, January 1945 WRL 16 A METHOD FORTHERAPIDESTIMATION OF TURBULENT BOUNDARY LAYER THICKNESSES FORCALCULATING PROFILE DRAG,Neal Tetervin, July WRL 18 AN INFRARED CLOUD INDICATOR. I - ANALYSIS OF INFRARED RADIA- TION EXCHANGE WITHTABLES ANDCHARTS FORCALIBRATION OF THE CLOUD INDICATOR, C. N. Warfield and R. L. Kenlmer, November WRL 19 NOTE ONCOMPRESSIBILITY EFFECTS ONDOWNWASH AT THETAIL AT SUBCRITICAL SPEEDS, J. N. Nielsen and H. H. Sweberg, March 1945 WRL 23 VARIATION WITHMACH NUMBER OF STATICANDTOTAL PRESSURES THROUGH VARIOUS SCREENS, A. A. Adler, February 1946 WRL 26 EFFECT ONHELICOPTER PERFORMANCE OFMODIFICATIONS IN PROFILE DRAG CHARACTERISTICS OFROTOR BLADE AIRFOIL SECTIONS, F. B.

Gustafson, August 1944 WRL 29 AERODYNAMIC CHARACTERISTICS OF FOUR NACA AIRFOIL SECTIONS DESIGNED FORHELICOPTER ROTOR BLADES, L. S. Stlvers, Jr. and F. J. Rice, Jr., February 1946 WRL NOTES ONUNUSUAL V-G RECORDS FROM TRANSPORT AIRPLANES, Walter G. Walker, August 1944 WRL 38 COMPARISON OF TAlL ANDWING TIP SPINRECOVERY PARACHUTES AS DETERMINED BYTESTSIN THELANGLEY 20-FOOT FREESPINNING TUNNEL, R. W. Kamm and F. S. Malvestuto, Jr., March 1946 WRL 43 STATICPRESSURE ERROR OF AN AIRSPEED INSTALLATION ONAN AIRPLANE IN HIGHSPEED DIVESANDPULLOUTS,John A. Zalovcik and Clotaire Wood, February 1946 EFFECTS OF SPECIFICTYPES OF SURFACE ROUGHNESS ONBOUNDARY LAYER WRL 48 TRANSITION, Laurence K. Loftin, Jr., February 1946 A METHOD OFANALYSIS OFV-G RECORDS FROM TRANSPORT OPERATIONS, WRL 71 A. M. Peiser and M. Wilkerson, November1945 AIRSPEED FLUCTUATIONS AS A MEASURE OF ATMOSPHERIC TURBULENCE, WRL 72 H. B. Tolefson, July 1945 EXPERIMENTAL CONSTRUCTION EFFECTS IN HIGHSPEED WINDTUNNELS, WRL 74 R. W. Byrne, December1944 EFFECT OFMACH NUMBER ONPOSITION ERROR AS APPLIED TO A PITOT- WRL 75 STATICTUBELOCATED 0.55 CHORD AHEAD OFAN AIRPLANE WING,W. F.

Lindsey, May 1944 EFFECT OF COMPRESSIBILITY ONTHEPRESSURES ANDFORCES ACTING WRL 76 ONA MODIFIED NACA65,3-019 AIRFOIL HAVING A 0.20-CHORD FLAP, W. F. Lindsey, January 1946 EFFECTS OF COMPRESSIBILITY ANDLARGE ANGLES OF YAW ONPRESSURE WRL 77 INDICATED BYA TOTAL PRESSURE TUBE,M. D." Humphreys, April 1945 WRL 78 A SIMPLE METHOD FORESTIMATING TERMINAL VELOCITY INCLUDING EFFECT OF COMPRESSIBILITY ONDRAG,R. P. Bielat, August 1945 RESISTANCE TESTS OFMODELS OF THREE FLYINGBOAT HULLS WITHA WRL 79 LENGTH-BEAM RATIOOF 10.5, J. M. Bidwell and D. M. Goldenbaum, September1945 WINDTUNNEL TESTS OF DUALROTATING PROPELLERS WITHSYSTEMATIC WRL 80 DIFFERENCES IN NUMBER OF BLADES, BLADESETTING, ANDROTATIONAL SPEED OF FRONT ANDREAR PROPELLERS_ W. H. Gray, May 1944 LOW PRESSURE BOUNDARY LAYER CONTROL IN DIFFUSERS ANDBENDS, WRL 84 Addison M. Rothrock, Arnold E. Biermann and Lester C. Corrington, January 1942 WRL 90 FLIGHTINVESTIGATION AT HIGHMACH NUMBERS OF SEVERAL METHODS OF MEASURING STATICPRESSURE ONAN AIRPLANE WING,J. A. Zalovcik and F. L. Daum,November1944 FLIGHTINVESTIGATION AT HIGHSPEEDS OF FLOW CONDITIONS OVER AN WRL 91 AIRPLANE WING AS INDICATED BY SURFACE TURRETS, C. Woodand J. A.

Zalovcik, June 1945 EFFECT OF ROTOR TIP SPEED ONHELICOPTER HOVERING PERFORMANCE AND WRL 97 MAXIMUM FORWARD SPEED, F. B. Gustafson and A. Gessow, March 1946 WR L 107 TABLES AND CHARTS FOR THE EVALUATION OF PROFILE DRAG FROM WAKE SURVEYS AT HIGH SUBSONIC SPEEDS, M. J. Block and S. Katzoff, July 1945 WR L Ii0 CHARTS FOR ESTIMATION OF THE CHARACTERISTICS OF A HELICOPTER ROTOR IN FORWARD FLIGHT. I - PROFILE DRAG LIFT RATIO FOR UN- TWISTED RECTANGULAR BLADES, F. J. Bailey and F. B. Gustafson, August 1944 WR L iii EFFECT OF ELEVATOR-PROFILE MODIFICATIONS AND TRAILING-EDGE STRIPS ON ELEVATOR HINGE-MOMENT AND OTHER AERODYNAMIC CHARACTERISTICS OF A FULL-SCALE HORIZONTAL TAlL SURFACE, C. F. Schueller, P. F.

Korycinski, H. K. Strass, June 1945 WR L 113 THE CONFORMAL TRANSFORMATION OF AN AIRFOIL INTO A STRAIGHT LINE AND ITS APPLICATION TO THE INVERSE PROBLEM OF AIRFOIL THEORY, W. Mutterperl, December 1944 WR L 114 EFFECTS OF WING AND NACELLE MODIFICATIONS ON DRAG AND WAKE CHARACTERISTICS OF A BOMBER-TYPE AIRPLANE MODEL, R. H. Neely, R. W. Fairbanks, and D. W. Conner, December 1945 WR L 117 ESTIMATION OF PRESSURE DISTRIBUTIONS AT SUBCRITICAL SPEEDS FOR TURRETS LOCATED ON A WING, Virgil S. Ritchie and Everett J.

Daniels, July 1944 APPROXIMATE FORMULAS FOR THE COMPUTATION OF TURBULENT BOUNDARY WR L 119 LAYER MOMENTUM THICKNESSES IN COMPRESSIBLE FLOWS, N. Tetervin, March 1946 WR L 120 AN ELECTROMAGNETIC ANALOGY METHOD OF SOLVING LIFTING SURFACE THEORY PROBLEMS, R. S. Swanson and S. M. Crandall, May 1945 WR L 123 CHARTS FOR DETERMINING JET BOUNDARY CORRECTIONS FOR COMPLETE MODELS IN 7 BY i0 FOOT CLOSED RECTANGULAR WIND TUNNELS, C. L.

Gillis, E. C. Polhamus, and J. L. Gray, Jr., September 1945 WR L 126 EVALUATION OF THE INDUCED VELOCITY FIELD OF AN IDEALIZED HELI- COPTER ROTOR, R. P. Coleman, A. M. Feingold, and C. W. Stempin, June 1945 WR L 127 ON THE FLOW OF A COMPRESSIBLE FLUID BY THE HODOGRAPH METHOD.

i - UNIFICATION AND EXTENSION OF PRESENT DAY RESULTS, I. E.

Garrick and C. Kaplan, March 1944 WR L 131 AERODYNAMIC TESTS OF AN AN-M-65-AZON 1000-POUND RADIO-CONTROL BOMB IN THE LMAL 16-FOOT HIGH-SPEED TUNNEL, E. O. Pearson, Jr., June 1944 WRL 132 AERODYNAMIC TESTS OFAN M-31 BOMB IN THE8-FOOT HIGH-SPEED TUNNEL, D. D. Baals and N. F. Smith, August 1942 WRL 133 FORCES TESTS OF A 1/5 SCALE MODEL OF THETYPEGB-5 CONTROLLABLE GLIDEBOMB, M. Pitkin, March 1944 WRL 135 AIRFOIL CONTOUR MODIFICATIONS BASED ONE-CURVE METHOD OF CALCULAT- ING PRESSURE DISTRIBUTION, Theodore Theodorsen, July 1944 WRL 136 NUMERICAL EVALUATION OF THEe INTEGRAL OCCURRING IN THETHEODORSEN ARBITRARY AIRFOIL POTENTIAL THEORY, Irvin Naiman, April 1944 WRL 141 INVESTIGATION OF EFFECTS OFVARIOUS CAMOUFLAGE PAINTSANDPAINTING PROCEDURES ONTHEDRAG CHARACTERISTICS OFAN NACA 65(421)-420, a = 1.0 AIRFOIL SECTION, A. L. Braslow, July 1944 WRL 143 COMPLETED TABULATION IN THEUNITED STATES OF TESTS OF 24 AIRFOILS AT HIGHMACH NUMBERS (Derived from Interrupted Work at Guidonia, Italy in the 1.31 by 1.74 Foot High-Speed Tunnel), A. Ferri, June WRL 147 ONTHEFLOW OF A COMPRESSIBLE FLUID BY THEHODOGRAPH METHOD.II- FUNDAMENTAL SETOF PARTICULAR FLOW SOLUTIONS OF THECHAPLYGIN DIF- FERENTIAL EQUATION, I. E. Garrick and C. Kaplan, November1944 WRL 150 TANKTESTS OF A FLYINGBOAT MODEL EQUIPPED WITHSEVERAL TYPES OF FAIRINGDESIGNED TO REDUCE THEAIR DRAG OF THEAIR DRAG OF THE MAINSTEP,J. M. Benson and R. F. Havens, April 1945 WRL 152 SUPERSONIC TUNNEL TESTS OF PROJECTILES IN GERMANY ANDITALY, A.

Ferri, October 1945 WRL 153 NUMERICAL EVALUATION BY HARMONIC ANALYSIS OF THEFUNCTION OF THE THEODORSEN ARBITRARY AIRFOIL POTENTIAL THEORY, I. Naiman, September 1945 SUMMARY OFDATARELATING TO THEEFFECTS OF WIND MACHINE GUN AND WRL 158 CANNON INSTALLATIONS ONTHEAERODYNAMIC CHARACTERISTICS OF AIR- PLANES, J. H. Quinn, Jr., January 1945 WRL 159 A FLIGHTINVESTIGATION OF THEEFFECT OF SURFACE ROUGHNESS ONWING PROFILE DRAG WITHTRANSITION FIXED, John A. Zalovcik and Clotaire Wood, September 1944 WRL 162 EFFECTS ONLOWSPEED SPRAY CHARACTERISTICS OF VARIOUS MODIFICA- TIONSTOA POWERED MODEL OF THEBOEING XPBB-I FLYINGBOAT,D. A.

King and N. A. Mas, June 1945 WRL 163 THENACA IMPACT BASINANDWATER LANDING TESTS OF A FLOAT MODEL AT VARIOUS VELOCITIES ANDWEIGHTS, S. A. Batterson, August 1944 WRL 164 ANALYSIS OF FACTORS AFFECTING NET LIFT INCREMENT ATTAINABLE WITH TRAILING EDGE SPLIT FLAPS ON TAILLESS AIRPLANES, M. Pitkin and B. Maggin, September 1944 WRL 167 PRELIMINARY TANK TESTS WITH PLANING TAlL SEAPLANE HULLS, J. R.

Dawson and K. L. Wadlin, June 1943 WRL 170 EFFECT OF FABRIC DEFLECTION AT HIGH SPEEDS ON THE AERODYNAMIC CHARACTERISTICS OF THE HORIZONTAL TAlL SURFACE OF AN SB2D-I AIRPLANE, C. F. Schueller and P. F. Korycinski, June 1945 WRL 179 COMPRESSIBILITY EFFECTS OF HEAT TRANSFER AND PRESSURE DROP IN SMOOTH CYLINDRICAL TUBES, J. N. Nielsen, October 1944 WR L 188 DATA FOR DESIGN OF ENTRANCE VANES FROM TWO DIMENSIONAL TESTS OF AIRFOILS IN CASCADE, C. M. Zimmey and V. M. Lappi, October 1945 WR L 201 ESTIMATION OF PRESSURES ON COCKPIT CANOPIES, GUN TURRETS, BLISTERS, AND SIMILAR PROTUBERANCES, Ray H. Wright, May 1944 WR L 203 NACA MACH NUMBER WARNING DEVICE FOR USE IN FLIGHT, J. Goodman, July 1944 WR L 206 THE LOCUS OF POSSIBLE POSITIONS OF A HEAVY BOMBER IN SPACE AFTER A 12-SECOND TIME INTERVAL, Charles W. Mathews and Clotaire Wood, June 1943 WR L 208 DESIGN OF POWER-PLANT INSTALLATIONS PRESSURE-LOSS CHARACTERISTICS OF DUCT COMPONENTS, John R. Henry, June 1944 WR L 216 THE FLOW OF A COMPRESSIBLE FLUID PAST A CIRCULAR ARC PROFILE, C.

Kaplan, October 1944 CALCULATION OF TAB CHARACTERISTICS FOR FLIGHT CONDITIONS FROM WR L 218 WIND-TUNNEL DATA, Richard I. Sears, April 1942 WR L 223 EMERGENCY MEASURES FOR INCREASING THE RANGE OF FIGHTER AIRPLANES, Robert T. Jones and Joseph W. Wetmore, May 1943 WR L 226 EXPERIMENTS ON DRAG OF REVOLVING DISKS, CYLINDERS AND STREAMLINE RODS AT HIGH SPEEDS, T. Theodorsen and A. Regier, June 1944 WR L 230 BIBLIOGRAPHY AND REVIEW OF INFORMATION RELATING TO THE HYDRO- DYNAMICS OF SEAPLANES, J. M. Benson and J. M. Bidwell, September WR L 231 PRELIMINARY EXPERIMENTAL INVESTIGATION OF AIRFOILS IN CASCADE, A. Kantrowitz and F. L. Daum, July 1942 LANDING CHARACTERISTICS OFA MODEL OF A FLYINGBOAT WITHTHE WRL 234 DEPTH OF STEPREDUCED TO ZERO BYMEANS OFA RETRACTABLE PLANING FLAP, J. M. Bensonand A. Freihofner, February 1944 THEUSEOFA RETRACTABLE PLANING FLATINSTEAD OFA FIXEDSTEP WRL 237 ONA SEAPLANE, J. M. Benson and L. J. Lina, May 1943 WIND-TUNNEL TESTS OF FOUR FULL-SCALE SEAPLANE FLATS,R. N.

WRL 238 Conwayand Julian D. Maynard, July 1943 EXPERIMENTAL INVESTIGATION OF ENTRANCE-REGION HEAT-TRANSFER WRL 239 COEFFICIENTS, U. T. Joyner, November1943 DETERMINATION OF JET-BOUNDARY CORRECTIONS TO COWLING-FLAP- WRL 240 OUTLET PRESSURES BYAN ELECTRICAL ANALOGY METHOD, S. Katzoff and R. S. Finn, February 1944 THEBELTMETHOD FORMEASURING PRESSURE DISTRIBUTION, Blake WRL 244 W. Corson, Jr., February 1943 TIRE FRICTION COEFFICIENTS ANDTHEIRRELATION TO GROUND-RUN WRL 245 DISTANCE IN LANDING, F. B. Gustafson, June 1942 WRL 246 FULL-SCALE-TUNNEL INVESTIGATION OF A MULTIENGINE PUSHER-PROPELLER INSTALLATION, Herbert A. Wilson, Jr., November1942 WRL 247 FLIGHTINVESTIGATION OFWIND-GUN FAIRINGS ONA FIGHTER TYPE AIRPLANE, J. M. Nissen and M. D. White, October 1941 WRL 249 A STUDY OF THEEFFECTS OFRADII OF GYRATION ANDALTITUDE OF AILERON EFFECTIVENESS AT HIGHSPEED, L. F. Fehlner, April 1943 NACA PROCEDURE FORFLIGHTTESTS OF AILERON CHARACTERISTICS OF WRL 265 AIRPLANES, Harold I. Johnson, July 1943 EFFECT OFCOMPRESSIBILITY ONPRESSURE DISTRIBUTION OVER AN WRL 266 AIRFOIL WITHA SLOTTED FRISEAILERON, A. A. Luoma, July 1944 FLIGHTTESTS OFF2A-2 AIRPLANE WITHFULL-SPAN SLOTTED FLAPSAND WRL 272 TRAILING-EDGE ANDSLOT-LIPAILERONS, Joseph W. Wetmoreand Richard H. Sawyer, December1943 CALIBRATION OF THREE TEMPERATURE PROBES ANDA PRESSURE PROBE AT WRL 273 HIGHSPEEDS, W. F. Lindsey, April 1942 WRL 274 EFFECT OF TURBULENCE ONAIR-FLOW MEASUREMENTS BEHIND ORIFICE PLATES,J. N. Nielsen, July 1943 AERODYNAMIC ANDHYDRODYNAMIC TESTS OFA FAMILYOFMODELS OF WRL 277 FLYINGBOAT HULLS DERIVED FROM A STREAMLINE BODY NACA MODEL 84 SERIES,J. B. Parkinson, R. E. Olson, E. C. Draley and A. A.

Luoma, September 1943 WR L 282 THE DESIGN OF THE OPTIMUM HULL FOR A LARGE LONG-RANGE FLYING BOAT, J. B. Parkinson, September 1944 WR L 283 CHARTS FOR HELICOPTER-PERFORMANCE ESTIMATION, H. W. Talkin, August WR L 291 TIME-VELOCITY-ALTITUDE RELATIONS FOR AN AIRPLANE DIVING IN A STANDARD ATMOSPHERE, H. A. Pearson, March 1943 WR L 292 EFFECTS OF A SIMULATED ICE FORMATION ON THE AERODYNAMIC CHARACTER- ISTICS OF AN AIRFOIL, B. G. Gulick, May 1938 WR L 299 LIFT AND DRAG DATA FOR 30 PUSHER-PROPELLER SHAFT HOUSINGS ON AN NACA 65,3-018 AIRFOIL SECTION, Frank T. Abbott, Jr., November 1943 WR L 305 THE EFFECTS OF ANGLE OF DEAD RISE AND ANGLE OF AFTERBODY KEEL ON THE RESISTANCE OF A MODEL OF A FLYING-BOAT HULL, J. W. Bell and J. M. Willis, Jr., February 1943 ErR L 306 THE EFFECT OF DEAD RISE UPON THE HIGH-ANGLE PORPOISING CHARACTER- ISTICS OF TWO PLANING SURFACES IN TANDEM, J. M. Benson and M. M.

Klein, June 1943 WRL 308 THEORY OF SELF-EXCITED MECHANICAL OSCILLATIONS OF HINGED ROTOR BLADES, R. P. Coleman, July 1943 WR L 312 THEORY OF MECHANICAL OSCILLATIONS OF ROTORS WITH TWO HINGED BLADES, A. M. Feingold, September 1943 WR L 313 ON THE PLANE POTENTIAL FLOW PAST A LATTICE OF ARBITRARY AIRFOILS, I. E. Garrick, January 1944 WR L 320 THE FLOW OF A COMPRESSIBLE FLUID PAST A CURVED SURFACE, C. Kaplan, November 1943 ErR L 321 THE DESIGN OF COOLING DUCTS WITH SPECIAL REFERENCE TO THE BOUNDARY LAYER AT THE INLET, S. Katzoff, December 1940 ErR L 328 INVESTIGATION OF AIR FLOW IN RIGHT-ANGLE ELBOWS IN A RECTANGULAR DUCT, Charles H. McLellan and Walter A. Bartlett, Jr., October 1941 WRL 333 NOTES ON THE SKIPPING OF SEAPLANES, J. B. Parkinson, September 1943 WR L 334 MEASUREMENTS OF THE FLYING QUALITIES OF A SUPERMARINE SPITFIRE V-A AIRPLANE, William H. Phillips and Joseph R. Vensel, September 1942 WR L 335 EFFECT OF GROUND ON CHARACTERISTICS OF MODEL OF A LOW-WING AIR- PLANE WITH FULL-SPAN SLOTTED FLAP WITH AND WITHOUT POWER, I. G.

Recant and A. R. Wallace, September 1942 WRL 339 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS. IX- SOME ANALYTICAL CONSIDERATIONS ANDEXPERIMENTAL TESTRESULTS FOR AN INTERNALLY BALANCED FLAP, Richard I. Sears, July 1942 WRL 348 DRAG MEASUREMENTS OF A PROTRUDING 0.50-CALIBERMACHINE GUN,A. A.

Luoma, July 1941 ErR L 353 STALLING CHARACTERISTICS OFTHESUPERMARINE SPITFIREV-A AIRPLANE, J. R. Vensel and W. H. Phillips, September 1942 WRL 357 HIGH-SPEED WIND-TUNNEL TESTS OF THENACA23012 AND23013-64 AIR- FOILS, J. V. Becker, February 1941 EFFECT OF LENGTH-BEAM RATIONONRESISTANCE ANDSPRAY OF THREE WRL 358 MODELS OF FLYING-BOAT HULLS,J. W. Bell, Charlie C. Garrison, and H. Zeck, October 1943 WRL 364 FLIGHTINVESTIGATION OFAN NACAICE-DETECTOR SUITABLE FORUSEAS A RATE-OF-ICING INDICATOR, R. R. Gilruth, J. A. Zalovcik, and A. R. Jones, November1942 WRL 365 AERODYNAMIC FACTORS AFFECTING THEABILITY OF A PILOT TO RETURN AN AIRPLANE TO LEVELFROM A BANKED ATTITUDE BYUSEOFTHERUDDER ALONE ANDWITHOUT CHANGE OF HEADING, S. M. Harmon, October 1941 WRL 371 WIND-TUNNEL TESTS OF SEVERAL ARRANGEMENTS OF EXTERNAL AUXILIARY FUELTANKS ONA FIGHTER-TYPE AIRPLANE, E. Pepper, August 1942 WRL 373 WIND-TUNNEL INVESTIGATION OF PERFORATED SPLIT SLAPS FORUSEAS DIVE BRAKES ONA TAPERED NACA 23012 AIRFOIL, Paul E. Purser and ThomasR. Turner, November1941 THEEFFECT OF PROPELLER OPERATION ONTHEAIR FLOW IN THEREGION ErR L 381 OF THETAlL PLANE FORA TWIN-ENGINE TRACTOR MONOPLANE, Harold H.

Sweberg, August 1942 WRL 382 DETERMINATION OF GENERAL RELATIONS FORTHEBEHAVIOR OF TURBULENT BOUNDARY LAYERS, A. E. von Doenhoff and N. Tetervin, July 1943 A COMPARISON AT HIGHSPEED OF THEAERODYNAMIC MERITSOFMODELS WRL 390 OF MEDIUM BOMBERS HAVING THICKENED WINGROOTS ANDHAVING WINGS WITHNACELLES, E. C. Draley, December1943 WRL 396 CALIBRATIONS OF PITOT-STATIC TUBES AT HIGHSPEEDS, R. V. Hensley, July 1942 WRL 410 DESIGN CRITERIONS FORTHEDIMENSIONS OF THEFOREBODY OFA LONG- RANGE FLYINGBOAT,J. B. Parkinson, November1943 WRL 412 FLIGHTTESTS OFVARIOUS TAlL MODIFICATIONS ONTHEBREWSTER XSBA-I AIRPLANE. I - MEASUREMENTS OFFLYINGQUALITIES WITHORIGINAL TAlL SURFACES, W. H. Phillips and J. M. Nissen, June 1942 WRL 414 A STUDY OF THEAPPLICATION OF DATA ONVARIOUS TYPES OF FLAPTO THE DESIGN OF FLIGHTER BRAKES, P. E. Purser, June 1942 WRL 417 OBSERVATIONS OF COMPRESSIBILITY PHENOMENA IN FLIGHT,R. V. Rhode and H. A. Pearson, April 1943 WRL 419 COLLECTION OF BALANCED-AILERON TEST DATA,F. M. Rogallo, January WRL 423 NACA MACH NUMBER INDICATOR FORUSEIN HIGH-SPEED TUNNELS, N. F.

Smith, July 1943 WR L 424 AIR-FLOW SURVEYS IN THEREGION OF THETAlL SURFACES OFA SINGLE- ENGINE AIRPLANE EQUIPPED WITHDUAL-ROTATING PROPELLERS, H. H.

Sweberg, March 1943 WRL 438 WIND-TUNNEL INVESTIGATION OFREAR UNDERSLUNG FUSELAGE DUCTS, K.

R. Czarnecki and W. J. Nelson, September 1943 WRL 445 WIND-TUNNEL INVESTIGATION OF PERFORATED SPLIT SLAPS FORUSEAS DIVE BRAKES ONA RECTANGULAR NACA 23012 AIRFOIL, Paul E. Purser and ThomasR. Turner, July 1941 WRL 451 PRELIMINARY REPORT ONTHECHARACTERISTICS OF THENACA 4400R SERIES AIRFOILS, A. Sherman,March 1939 WRL 456 AERODYNAMIC CHARACTERISTICS OFA 4-ENGINE MONOPLANE SHOWING EFFECTS OF ENCLOSING THEENGINES IN THEWING ANDCOMPARISONS OFTRACTOR- ANDPUSHER-PROPELLER ARRANGEMENTS, Abe Silverstein and Herbert A.

Wilson, Jr., April 1938 WRL 457 EFFECTS OF HEAT-CAPACITY LAGIN GASDYNAMICS, A. Kantrowitz, January 1944 WRL 458 REFLECTION-PLANE MODELS IN RECTANGULAR WINDTUNNELS, R. S. Swanson and T. A. Toll, May i943 WRL 460 ONA FUNCTION-THEORY METHOD FOROBTAINING POTENTIAL-FLOW PATTERNS OFA COMPRESSIBLE FLUID, A. Gelbart, July 1943 WRL 462 INVESTIGATION OFDRAG ANDPRESSURE DISTRIBUTION OF WINDSHIELDS AT HIGHSPEEDS, J. B. Delano and R. H. Wright, January 1942 WRL 463 TESTS OFA LARGE SPHERICAL TURRET ANDA MODIFIED TURRET ONA TYPICALBOMBER FUSELAGE, A. T. Mattson, October 1942 WRL 471 AERODYNAMIC CHARACTERISTICS OF A 4-ENGINE MONOPLANE SHOWING COM- PARISON OF AIR-COOLED ANDLIQUID-COOLED ENGINE INSTALLATIONS, A. Silverstein and H. A. Wilson, Jr., July 1939 WRL 473 A SIMPLIFIEDCHART FORDETERMINING MACH NUMBER ANDTRUE AIRSPEED FROM AIRSPEED-INDICATOR READINGS, D. D. Baals and V. S. Ritchie, March 1943 WRL 474 CONDENSATION TRIALS - WHERE THEY OCCUR AND WHAT CAN BE DONE ABOUT THEM, R. V. Rhode and H. A. Pearson, September 1942 WRL 475 TANKS TESTS OF A 1/5 FULL-SIZE DYNAMICALLY SIMILAR MODEL OF THE ARMY 0A-9 AMPHIBIAN WITH MOTOR-DRIVEN PROPELLERS - NACA MODEL 117, J. B. Parkinson and R. E. Olson, December 1941 WR L 477 NACA RADIO GROUND-SPEED SYSTEM FOR AIRCRAFT, C. E. Hastings, February 1943 ErR L 485 WIND TUNNEL TESTS OF A SUBMERGED-ENGINE FUSELAGE DESIGN, J. V.

Becker and D. D. Baals, October 1940 WR L 494 WIND-TUNNEL TESTS OF A PISTON-TYPE CONTROLBOOSTER ON AN AIRFOIL AND AILERON MODEL, J. D. Bird and Robert A. Mendelson, November WRL 498 FLIGHT TESTS OF A GLIDER MODEL TOWED BY TWIN PARALLEL TOWLINES, M. Pitkin and M. O. McKinney, Jr., April 1943 WR L 502 HIGH-SPEED WIND-TUNNEL TESTS OF GUN OPENINGS IN THE NOSE OF THE FUSELAGE OF A 1/4 SCALE MODEL, H. A. Fedziuk, July 1942 ErR L 505 FLIGHT MEASUREMENTS OF COMPRESSIBILITY EFFECTS ON A THREE-BLADE THIN CLARK Y PROPELLER OPERATING AT CONSTANT ADVANCE-DIAMETER RATIO AND BLADE ANGLE, A. W. Vogeley, July 1943 ErR L 510 TESTS OF SEVERAL MODEL NACELLE-PROPELLER ARRANGEMENTS IN FRONT OF A WING, J. G. McHugh, September 1939 WR L 515 VARIATION OF PEAK PITCHING-MOMENT COEFFICIENTS FOR SiX AIRFOILS AS AFFECTED BY COMPRESSIBILITY, H. E. Cleary, October 1944 WR L 531 TESTS OF A 1/7 SCALE POWERED MODEL OF THE KAISER TAILLESS AIR- PLANE IN THE LANGLEY FULL-SCALE TUNNEL, G. W. Brewer and E. A.

Rickey, WR L 537 PERFORMANCE SELECTION CHARTS FOR GLIDERS AND TWIN-ENGINE TOW PLANES, H. Reese Ivey, G. M. Fitch, and Wayne F. Schultz, August 1943 WR L 542 HIGH-SPEED DRAG TESTS OF SEVERAL FUSELAGE SHAPES IN COMBINATION WITH A WING, E. C. Draley, August 1940 WRL 543 POWER-OFF WIND-TUNNEL TESTS OF THE1/8-SCALEMODEL OF THEBREWSTER F2AAIRPLANE, John G. Lowry, June 1941 WRL 545 FULL-SCALE-TUNNEL PERFORMANCE TESTS OF THEPV-2 HELICOPTER ROTOR, E. Migotsky, April 1945 WRL 547 FLIGHTMEASUREMENTS OF THERUDDER CONTROL ANDSIDESLIPCHARACTER- ISTICS OF FOUR VERTICAL TAIL ARRANGEMENTS ONTHEP-40 SERIES AIR- PLANES, Harold I. Johnson and Joseph R. Vensel, October 1942 WRL 549 AERODYNAMIC CHAP_CTERISTICS ANDFLAPLOADS OF THEBRAKE-FLAP INSTALLATION ONTHE0.40-SCALEMODEL OF THEF4F-3 LEFTWING PANEL,Paul E. Pusher and Robert B. Liddell, October 1942 WRL 550 FLIGHTTESTS OF BEVELED-TRAILING-EDGE AILERONS WITHVARIOUS MODIFICATIONS ONA NORTH AMERICAN XP-51 AIRPLANE, M. D. White and H. H. Hoover, December1943 WRL 556 MAXIMUM LIFT COEFFICIENTS OF AIRPLANES BASED ONSUM OF WING AND TAIL AREAS,Abe Silverstein and Herbert A. Wilson, Jr., April WRL 558 ONA NEW METHOD FORCALCULATING THEPOTENTIAL FLOW PASTA BODY OF REVOLUTION, C. Kaplan, July 1942 TESTS OF A 0.30-SCALESEMISPAN MODEL OF THEDOUGLAS XTB2D-I AIR- WRL 563 PLANE WING ANDFUSELAGE COMBINATION IN THENACA 19-PRESSURE TUNNEL. I - FULL-SPAN FLAPANDAIR-BRAKE INVESTIGATION, C. D.

Ashworth, S. H. Spooner, and R. T. Russell, September 1944 WRL 565 MEASUREMENTS OF THEFLYINGQUALITIES OFA HAWKER HURICANE AIR- PLANE,J. M. Nissen and W. H. Phillips, April 1942 WRL 566 FLYINGQUALITIES ANDSTALLING CHARACTERISTICS OF NORTH AMERICAN XP-51 AIRPLANE (AAF NO. 41-38), M. D. White, H. H. Hoover, and H. W. Garris, April 1943 WRL 571 MEASUREMENTS OF FLYING QUALITIES OF A CURTISS SB2C-I AIRPLANE, W. H. Phillips, W. C. Williams, and H. H. Hoover, March 1944 WRL 578 ANALYSIS OF V-G RECORDS FROM THE SNJ-4 AIRPLANE, _. Wilkerson and S. A. Bennett, December 1945 WRL 580 CALIBRATIONS OF SERVICE PITOT TUBES IN THE LANGLEY 24-INCH HIGH- SPEED TUNNEL, W. F. Lindsey, February 1946 WRL 581 DRAG MEASUREMENTS OF A PROTRUDING .50-CALIBER MACHINE GUN WITH BARREL JACKET REMOVED, A. A. Luoma, January 1943 WRL 585 GENERAL FREETO TRIMTESTS IN NACA TANKNO. 2 OF THREE I/8-FULL- SIZE MODELS OF FLYING-BOAT HULLS AT LOWSPEEDS-NACA MODELS l16E-3k, 120R, AND143, A. W. Carter, January 1943 WRL 590 INVESTIGATION OFMEANS FOREXTENDING THERANGE OF SEVERAL BOMBERS TO 6000 MILES, H. S. Riber and S. M. Harmon, July 1942 WRL 591 ATTAINMENT OF A STRAIGHT-LINE TRAJECTORY FORA PRESET GUIDED MIS- SILE WITHSPECIAL REFERENCE TO EFFECT OF WINDORTARGET MOTION, H. S. Ribner, July 1942 WRL 598 FLIGHTTESTS OFVARIOUS TAIL MODIFICATIONS ONTHEBREWSTER XSBA-I AIRPLANE. II - MEASUREMENTS OF FLYINGQUALITIES WITHTAlL CON- FIGURATION NUMBER TWO,W. H. Phillips and H. L. Crane, December WRL 599 FLIGHTTESTS OFVARIOUS TAIL MODIFICATIONS ONTHEBREWSTER XSBA-I AIRPLANE. III - MEASUREMENTS OF FLYINGQUALITIES WITHTAlL CON- FIGURATION 3, H. L. Crane and J. P. Reeder, July 1944 ErR L 602 MEASURemENTS OFTHEFLYINGQUALITIES OF A BELLP-39D-I AIRPLANE (AAFNO. 41-28378), H. I. Johnson, C. J. Liddell, and H. H. Hoover, September1943 WRL 603 JET-BOUNDARY CORRECTIONS TOA YAWED MODEL IN A CLOSED RECTANGULAR WINDTUNNEL, Robert S. Swanson, February 1943 WRL 609 AN EXPERIMENTAL SURVEY OF FLOW ACROSS BANKS OF ELLIPTICALAND POINTED TUBES,Upshur T. Joyner and Carl B. Palmer, January 1943 WRL 616 INVESTIGATION OF THEEFFECT OF SPRAY STRIPSONTHELOW-SPEED SPRAY CHARACTERISTICS OFA I/8-SIZE MODEL OF THECONSOLIDATED PB2Y-3 FLYINGBOAT NACA MODEL I16E-3, R. E. Olson, January 1943 WRL 624 TESTS OFA 1/14-SCALEPOWERED MODEL OF THEXB-36 AIRPLANE IN THE LANGLEY 19-FOOT PRESSURE TUNNEL. I - STALLING CHARACTERISTICS ANDAILERON EFFECTIVENESS OF SEVERAL WING ANDFLAPARRANGEMENTS, S. R. Alexander and J. C. Sivells, February 1945 WRL 625 AN INVESTIGATION OF THEMUTUAL INTERFERENCE EFFECTS OFA TAIL- SURFACE STERN PROPELLER INSTALLATION ONA MODEL SIMULATING THE DOUGLAS XB-42 EMPENNAGE, Walter A. Bartlett, Jr. and Alfred A.

Marino, November1944 WRL 627 FULL-SCALE TUNNEL TESTS OF A FLYINGMODEL OFTHECURTISS XP-55 AIRPLANE, William J. Biebel, January 1943 WRL 628 TESTS OF THENORTHROP MX-334 GLIDER AIRPLANE IN THENACA FULL- SCALE TUNNEL, G. W. Brewer, January 1944 WRL 630 FULL-SCALE TUNNEL MEASUREMENTS OF THEPRESSURES ONTHEELEVATOR ANDFUSELAGE OF THECURTISS XP-55 AIRPLANE, Richard C. Dingeldein, June 1943 WRL 633 TESTS OFA 1/40-SCALEWING-HULL MODEL ANDA 1/10-SCALEFLOAT- STRUT MODEL OFTHEHUGHES-KAISER CARGO AIRPLANE IN THETWO- DIMENSIONAL LOW-TURBULENCE PRESSURE TUNNEL, F. F. Fullmer, Jr., September1943 WRL 639 NOTE ONTHEINTERPRETATION OFWAKE-SURVEY DATA ANDITS USEIN THE ESTIMATION OF INDUCED DRAG DUETO IRREGULARITIES, S. Katzoff and Robert S. Finn, January 1944 WRL 641 LIFT TESTS OFA 0.1536c THICKDOUGLAS AIRFOIL SECTION OFNACA7- SERIES TYPEEQUIPPED WITHA LATERAL-CONTROL DEVICE FORUSEWITH A FULL-SPAN DOUBLE-SLOTTED FLAPONTHEC-74 AIRPLANE,Robert J.

Nuber and Fred J. Rice, Jr., March 1945 WRL 645 AERODYNAMIC CHARACTERISTICS FORINTERNAL-BALANCE ANDFRISETYPE AILERONS ONAN NACA 6-SERIESLOW-DRAG TIP SECTION OF THEWINGFOR THEXP-63 AIRPLANE, William J.Underwood, October 1942 WRL 656 SOME FLIGHTMEASUREMENTS OF PRESSURE DISTRIBUTION DURING TAIL BUFFETING, John Boshar, October 1945 WRL 660 INTERFERENCE EFFECTS OFLONGITUDINAL FLATPLATES ONLOW-DRAG AIR- FOILS, Ira H. Abbott, November1942 WRL 662 TESTS OFTWO MODELS REPRESENTING INTERMEDIATE INBOARD ANDOUTBOARD WING SECTIONS OF THEXB-36 AIRPLANE, S. M. Bogdonoff, January 1943 WRL 663 WIND-TUNNEL DATAONTHEAERODYNAMIC CHARACTERISTICS OF AIRPLANE CONTROL SURFACES, Richard I. Sears, December1943 WRL 672 GENERALIZED SELECTION CHARTS FORBOMBERS POWERED BYTWO,FOUR, ANDSIX 3000-HORSEPOWER ENGINES. I - CAPACITY ANDECONOMY, M. J. Brevoort, G. W. Stickle, and P. R. Hill, January 1943 WRL 674 AN INVESTIGATION OFTHEAIR FLOW AROUND A MARTIN PBM-3FLYING BOAT BYMEANS OF TUFTS,W. J_ Nelson and J. W. Ebert, Jr., April WRL 678 PRESSURE-DISTRIBUTION MEASUREMENTS OF A MODEL OFA DAVISWING SECTION WITHFLOWLER FLAPSUBMITTED BY CONSOLIDATED AIRCRAFT CORP- ORATION, Ira H. Abbott, January 1942 WRL 682 BOUNDARY-LAYER TRANSITION ONTHENACA 0012 AND23012 AIRFOILSIN THE8-FOOT HIGH-SPEED WINDTUNNEL, J. V. Becker, January 1940 RESISTANCE TESTS OFA 1/16-SIZE OF THEHUGHES-KAISER FLYINGBOAT, WRL 683 NACA MODEL 183, R. E. Olson, J. Posner, and D. R. Woodward,June WRL 687 TANK TESTS OF A I/8-SlZE DYNAMIC MODEL OF THEPB2Y-3AIRPLANE WITHSIMULATED JET MOTORS - NACA MODELS 131J, 131-J-l, AND131-J-2, J. W. Bell and R. F. Havens, June 1943 TANKTESTS OFA I/8-SIZE DYNAMIC MODEL OF THEPB2Y-3AIRPLANE WITH WRL 688 INCREASED POWER - NACA MODEL 131, J. W. Bell and R. F. Havens, June 1943 PRELIMINARY INVESTIGATION IN THENACA LOW-TURBULENCE TUNNEL OF WRL 694 LOW-DRAG AIRFOIL SECTIONS SUITABLE FORADMITTING AIR AT THE LEADING EDGE, A. E. von Doenhoff and E. A. Horton, July 1942 LIFT ANDDRAG CHARACTERISTICS OFA LOW-DRAG AIRFOIL WITHSLOTTED WRL 703 FLAPSUBMITTED BY CURTISS-WRIGHT CORPORATION, I. H. Abbott, December1941 POWER-ON WIND-TUNNEL TESTS OF THEI/8-SCALE MODEL OF THEBREWSTER ErRL 707 F2A AIRPLANE WITHFULL-SPAN SLOTTED FLAPS,John G. Lowry, August JET-BOUNDARY CORRECTIONS TO THEDOWNWASH BEHIND POWERED MODELS WRL 711 IN RECTANGULAR WINDTUNNELS WITHNUMERICAL VALUES FOR7- BY 10- FOOT CLOSED WINDTUNNELS, R. S. Swansonand M. J. Schuldenfrei, August 1942 WRL 717 FLIGHTMEASUREMENTS OF THEFLYINGQUALITIES OFAN F6F-3 AIRPLANE (BUAER NO. 04776). III - STALLING CHARACTERISTICS, Walter C.

Williams and John P. Reeder, February 1945 FLIGHTTESTSOFA RUDDER WITHA SPRING TABONAN F6F-3 AIRPLANE WRL 718 (BUAER NO. 04776), Walter C. Williams, March 1945 A METHOD FORTHECALCULATION OF EXTERNAL LIFT, MOMENT, ANDPRES- WRL 720 SURE DRAG OF SLENDER OPEN-NOSE BODIES OF REVOLUTION AT SUPERSONIC SPEEDS, C. E. Brown and H. M. Parker, March 1946 WRL 722 THEAERODYNAMIC TESTS OF THREE EDO FLOATS FORTHESB2U-3, OS2U02, ANDXSB2C-2SEAPLANES - NACA MODELS I06-X, 107-K AND125-AH, R. B.

Liddell, March 1942 PRELIMINARY TANKTESTS OFAN OUTBOARD FLOAT HAVING THEFORM OF A WRL 724 STREAMLINE BODY OF REVOLUTION FITTEDWITHA HYDROFOIL, D. A. King, April 1944 WRL 725 PRELIMINARY TANKEXPERIMENTS WITHA HYDROFOIL ONA PLANING-TAIL SEAPLANE HULL, K. L. Wadlin, March 1944 WRL 726 EFFECTS OF EXTERNAL FUEL TANKS AND BOMBS ON CRITICAL SPEEDS OF AIRCRAFT, S. Katzoff and R. S. Finn, February 1946 WRL 735 PATHS OF TARGET-SEEKING MISSILES IN TWO DIMENSIONS, C. E.

Watkins, July 1946 WRL 741 FLIGHT MEASUREMENTS BY VARIOUS METHODS OF THE DRAG CHARACTERISTICS OF THE XP-51 AIRPLANE, H. A. Pearson and D. E. Beadle, June 1946 WRL 745 PRELIMINARY DRAG TESTS IN FLIGHT OF LOW-DRAG WING ON THE CURTISS XP-60 AIRPLANE, Eastman N. Jacobs, December 1941 WRL 751 WIND-TUNNEL INVESTIGATION OF CARBURETOR-AIR SCOOPS FOR THE XTB2D-I AIRPLANE WITH EMPHASIS ON MEANS FOR BYPASSING THE BOUNDARY LAYER, Mark R. Nichols, Arvid L. Keith, Jr. and Robert W. Boswinkle, Jr., June 1944 WRL 757 CHARACTERISTICS OF AN NACA 66,S-209 SECTION HYDROFOIL AT SEVERAL DEPTHS, N. S. Land, May 1943 WRL 758 AN INVESTIGATION OF HYDROFOILS IN THE NACA TANK. I - EFFECT OF DIHEDRAL AND DEPTH OF SUBMERSION, J. M. Benson and N. S. Land, September 1942 WRL 759 ANALYSIS OF V-G RECORDS FROM THE SNB-I AIRPLANE, Walter G. Walker and May T. Meadows, July 1946 WRL 760 INVESTIGATION FOR THE DEVELOPMENT OF A HIGH-SPEED ANTIAIRCRAFT TOW TARGET, E. Migotsky, July 1943 WRL 762 TANK TESTS OF A POWERED DYNAMIC MODEL OF A FLYING BOAT HAVING AN AFTERBODY LENGTH-BEAM RATIO OF 4.7 LANGLEY TANK MODEL 203C-I, R. E. Olson and M. I. Haar, October 1945 ErR L 763 SPRAY CHARACTERISTICS OF A POWERED DYNAMIC MODEL OF A FLYING BOAT HAVING A HULL WITH A LENGTH-BEAM RATIO OF 9.0, R. E. Olson and J. W. Bell, January 1946 WRL 766 PRELIMINARY TESTS IN THE NACA TANK TO INVESTIGATE THE FUNDAMENTAL CHARACTERISTICS OF HYDROFOILS, K. E. Ward and N. S. Land, September WRL 769 TESTS OF BELL XP-63 LOW-DRAG _XNG MODEL WITH SPLIT FLAP, W. J.

Underwood, September 1941 WRL 778 FLIGHT TESTS OF DIVE-RECOVERY FLAPS ON AN XP-51 AIRPLANE, D. E.

Beeler and Walter C. Williams, May 1945 WR L 781 ESTIMATION OF CRITICAL SPEEDS OF AIRFOILS AND STREAMLINE BODIES, R. G. Robinson and R. H. Wright, March 1940 THEORETICAL INVESTIGATION OF METHODS FOR COMPUTING DRAG FROM WAKE WRW SURVEYS AT HIGH SUBSONIC SPEEDS, Max A. Heaslet, June 1945 CRITICAL MACH NUMBERS OF THIN AIRFOIL SECTIONS WITH PLAIN FLAPS, WRW Max A. Heaslet and Otway O'M. Pardee, April 1946 WRW COMPARISONS OF VARIOUS METHODS FOR COMPUTING DRAG FROM WAKE SURVEYS, Wallace F. Davis, January 1943 8 LAMINAR-BOUNDARY-LAYER OSCILLATIONS AND TRANSITION ON A FLAT WRW PLATE, G. B. Schubauer and H. K. Skramstad, April 1943 WRW 39 PRESSURE LOSS IN DUCTS WITH COMPOUND ELBOWS, John R. Weske, February 1943 WR W 40 ALTITUDE RATING OF ELECTRIC APPARATUS, Paul Lebenbaum, Jr., January 1943 WR W 66 SOME YAWING TESTS OF A 1/30-SCALE MODEL OF THE HULL OF THE XPB2M-I FLYING BOAT, F. W. S. Locke, Jr., July 1943 WR W 69 A METHOD FOR MAKING QUANTITATIVE STUDIES OF THE MAIN SPRAY CHARACTERISTICS OF FLYING-BOAT HULL MODELS, F. W. S. Locke, Jr.

and Helen L. Bott, November 1943 WR W 71 SOME SYSTEMATIC MODEL EXPERIMENTS OF THE BOW-SPRAY CHARACTERISTICS OF FLYING-BOAT HULLS OPERATING AT LOW SPEEDS IN WAVES, F. W. S.

Locke, Jr., December 1943 WRW72 "GENERAL" MAIN-SPRAY TESTS OF FLYING-BOAT MODELS IN THE DISPLACE- MENT RANGE, F. W. S. Locke, Jr., April 1945 WRW81 THE DEVELOPMENT OF SATISFACTORY FLYING QUALITIES ON THE DOUGLAS DIVE BOMBER, MODEL SBD-I THROUGH FLIGHT TESTING SUCCESSIVE MODIFICATIONS IN CONTROL-SURFACE AREA, HINGE-LINE LOCATION, AND AERODYNAMIC-BALANCE NOSE SHAPE, L. E. Root, May 1942 WRW 86 THEORY AND APPLICATION OF HOT-WIRE INSTRUMENTS IN THE INVESTIGA- TION OF TURBULENT BOUNDARY LAYERS, G. B. Schubauer and P. S.

Klebanoff, March 1946 WRW 87 INVESTIGATION OF BOUNDARY LAYER TRANSITION ON CONCAVE WALLS, H. W.

Lupmann, February 1945 WRW90 INVESTIGATION OF THE BEHAVIOR OF PARALLEL TWO-DIMENSIONAL AIR JETS, Stanley Corrsin, November 1944 WR W 94 INVESTIGATION OF FLOW IN AN AXIALLY SYMMETRICAL HEATED JET OF AIR, Stanley Corrsin, December 1943 WRW105 GENERAL TANKTESTS ONTHEHYDRODYNAMIC CHARACTERISTICS OF FOUR FLYING-BOAT HULLMODELS OF DIFFERING LENGTH-BEAM RATIO, Kenneth S. M. Davldson and F. W. S. Locke, Jr., June 1944 WR W 107 INVESTIGATIONS ONLAMINAR BOUNDARY-LAYER STABILITYANDTRANSITION ONCURVED BOUNDARIES, Hans W. Liepmann, August 1943 WRW108 HEAT-TRANSFER COEFFICIENTS FORAIR FLOWING IN ROUND TUBES,IN RECTANGULAR DUCTS, ANDAROUND FINNED CYLINDERS, Roger E. Drexel and William H. McAdams, February 1945 5O8 Applicable NACA Research Memoranda AN APPROXIMATE METHOD FOR CALCULATING THE EFFECT OF SURFACE RM A7B24 ROUGHNESS ON THE DRAG OF AN AIRPLANE, Charles F. Hall and Fred F.

Fitzgerald, July 1947 A method for computing the effect of surface roughness on the drag coefficient of an airplane is presented. Calculated results using this method are compared with experimental results from both flight and wind-tunnel tests. In general, the agreement is believed satisfactory. In order to provide means to estimate the effect of various degrees of roughness on any airplane, the method discussed in this report was developed. The method combines several relations used in determining the skin-friction drag of flat plates with various surface conditions.

In this particular discussion three different types of boundary- layer flow are of interest, namely, laminar flow, turbulent flow over a smooth surface, and turbulent flow over a rough surface.

a b c d At point a, the leading edge of the plate, the boundary-layer thickness is zero. From points a to b, the boundary layer is laminar. Transition is assumed to occur at point b, causing a turbulent boundary layer on a smooth surface to exist from points b to c. A turbulent boundary layer on a rough surface exists from c to d. In order to compute the drag of this surface it is necessary to know the decrease in boundary-layer momentum.

Various equations have been determined analytically and empiric- ally from which the ordinates of these curves (momentum losses from the leading edge) can be found, provided the conditions set forth in the derivation of these equations are met: i. The boundary layer must be the same type as that used in the derivation of the equation.

2. The same type of boundary layer must extend over the entire surface.

3. The momentum losses in the boundary layer must be zero at the upstream edge of the surface.

The basic skin-friction drag equations as given in the references are : 1.327 For a laminar boundary layer Cf = 1/2 (R) 0.455 Cf = For a turbulent boundary layer 2.58 on a smooth surface (lOgl0R) x -2.5 For a turbulent boundary layer Cf = (1.89 + 1.62 lOgl0 _-) s on a rough surface If the equations are modified by multiplying by a length term then Cfx is then the drag per unit width of the plate divided by the dynamic pressure.

In order to use the method previously discussed it is necessary to determine the types of flow over the surface and the length of each type of flow. The transition point thus becomes important.

For airfoils having maximum velocity far forward, it is assumed that transition will occur at the point of laminar separation.

If the surface is in the wake of the wing, as for example the horizontal tail, or in the propeller slipstream, it is assumed that transition occurs at the leading edge of the surface. The boundary layer over a rough surface is assumed to be turbulent except near the stagnation point.

Results i. In most of the comparisons, the calculated increment was within 20 percent of experimental increment.

2. Due to an inability to estimate accurately the extent that a roughened surface will cause premature transition, experimental and calculated results in which only the leading edge of the wing is roughened do not agree very well. This is not believed too serious since in most cases the entire wing will be roughened.

The tests were made on a P-51B airplane.

RMA7F25 A COMPARISON WITH FLIGHT DATA OF VERTICAL-TAIL LOADS IN VARIOUS MANEUVERS ESTIMATED FROM SIDESLIP ANGLES AND RUDDER DEFLECTIONS, Howard L. Turner, December 1947 A comparison is made of the vertical-tail loads determined from pressure-distribution measurements in flight in various maneuvers with the corresponding vertical-tail loads calculated, using the values of sideslip angles and rudder deflections as measured during the various maneuvers. The maneuvers investigated included slow rolls, steady sideslips, fishtails, and rolling pull-outs. The loads were calculated only for the sideslip angles and rudder deflections corresponding to the maximum measured load in each maneuver. In order to provide data to further substantiate the validity of one step in the prediction of tail loads, flight tests were conducted on a propeller-driven fighter-type airplane in which vertical-tail loads were measured, by orifices on the surface of the vertical tail, in various static and dynamic maneuvers. Simultaneous values of side-slip angle, rudder deflection, and yawing velocity were also measured. From these data and the aerodynamic parameters evaluated using the vertical-tail geometry, the vertical-tail loads were computed and then comparedwith the corresponding loads measured in flight.

Steady sideslips were madewith power off and with normal rated power. All other maneuverswere performed with normal rated power only.

Results i. The effective angle of attack of the vertical tail under maximum loading conditions is adequately defined by combining the sideslip angle with the fin offset angle and the angle increment equivalent to the rudder'deflection.

2. If the maximum sideslip angle and the rudder deflection at the time of maximum loading of the vertical tail are known, the maximum loads in static and dynamic maneuvers may be predicted fairly accurately. Using current methods of estimation, the calculated vertical-tail loads were found to be approximately 16 percent greater than the corresponding flight-measured loads.

3. The most important single factor in this estimation of vertical-tail loads appears to be the vertical-tail lift-curve slope. Further improvements in the accuracy of estimating the vertical-tail loads appear to be dependent upon more accurate means for estimating the vertical-tail lift-curve slope.

RM A7K24 WIND-TUNNEL INVESTIGATION OF HORIZONTAL TAILS. I - UNSWEPT AND 35 ° SWEPT-BACK PLAN FORMS OF ASPECT RATIO 3, Jules B. Dods, Jr., April 1948 The results are presented of a wind tunnel investigation of the low speed characteristics of horizontal tails of aspect ratio 3 with unswept and swept back plane forms. Two models were tested which had identical areas, aspect ratio, tapper ratio, and air- foil section, differing only in the angle of sweepback and elevator area ratios.

Data are presented for variations of the lift, hinge moment, and pitching moment coefficients with angle of attack. The major effect of sweepback, as measured from the tests of the two models, was to increase the rate of change of hinge momentcoefficient with angle of attack, to reduce the rate of change with elevator deflection, and to reduce the elevator effectiveness.

RMA8BII WIND-TUNNEL INVESTIGATION OFHORIZONTAL TAILS. II - UNSWEPT AND 35 ° SWEPT-BACK PLAN FORMS OF ASPECT RATIO 4.5, Jules B. Dods, Jr., April 1948 The results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails having unswept and 35 ° swept-back plan forms are presented. The two models had an aspect ratio of 4.5, taper ratio of 0.5, and an NACA 64A010 airfoil section. The data presented supplement pre- viously reported results of tests of models having the same air- foil section, taper ratio, and sweepback, but with an aspect ratio of 3.0. Test results are presented for the models with and without standard roughness applied to their leading edges and with sealed and unsealed radius-nose elevators. The 0.25-chord lines were swept back 7.6 ° for the unswept model and 35 ° for the swept-back model. Model lift and pitching moment were measured by the wind-tunnel balance system. Elevator hinge moments were measured by a resistance-type torsional strain gage. Pressures above and below the elevator-nose seal in the balance chamber were measured by a manometer connected to the orifices in the balance chamber. Tunnel wall corrections were applied.

Results i. The value of Ch6 e was changed from -0.0095 for the unswept tail to -0.0069 for the 35 ° swept-back tail. The change in Ch was negligible.

2. The elevator-effectiveness parameter _ was changed from 0e -0.68 for the unswept model to -0.52 for the swept-back model.

3. The effect of standard leading-edge roughness was greater for the unswept model than for the swept-back model. The maximum lift coefficient of the unswept tail was increased from 0.87 to 0.91 with an elevator deflection of 0 °, and the changes of hinge- moment coefficient were less severe near the stall. Practically no effect of roughness was observed for the swept-back tail.

4. Removal of the elevator-nose seal had the greatest effect upon the elevator effectiveness of the unswept tail. The hinge- moment parameters were relatively unaffected for both tails.

RMA8H30 WIND-TUNNEL INVESTIGATION OF HORIZONTAL TAILS. III - UNSWEPT AND 35 ° SWEPT-BACK PLAN FORMS OF ASPECT RATIO 6, Jules B. Dods, Jr., December 1948 Results of wind tunnel tests of a horizontal tail of aspect ratio 6 with unswept and 35 ° swept back plan forms are presented. The lift, hinge moment and pitching moment coefficients and the pres- sure coefficients across the elevator nose seal are given as functions of the angle of attack and elevator deflection.

The major effects of the swept wing, as measured in the low speed tests of the two models having an aspect ratio of 6, were to reduce the rate of change of hinge moment coefficient with angle of attack and with elevator deflection, and to reduce the eleva- tor effectiveness. Roughness increased the maximum lift coeffi- cient of the unswept tail, but practically no effect was noted for the sweptback tail. Removal of the elevator nose seal result- ed only in small changes to the lift and hinge moment parameters.

WIND-TUNNEL INVESTIGATION OF HORIZONTAL TAILS. IV - UNSWEPT PLAN RMA8J21 FORM OF ASPECT RATIO 2 AND A TWO-DIMENSIONAL MODEL, Jules B.

Dods, Jr., December 1948 This report presents the results of a wind tunnel investigation of the low speed characteristics of an unswept horizontal tail model of aspect ratio 2, and of a two dimensional model which had the same airfoil section as all models previously reported in this series.

The lift, hinge moment, and pitching moment coefficients and the pressure coefficient across the elevator nose seal are given as functions of the angle of attack.

The major effect of standard leading edge roughness as to in- crease (positively) the rate of change of hinge moment coeffi- cient with angle of attack of the model of aspect ratio 2.

Removal of the elevator nose seal reduced the lift effectiveness of the elevator for the two dimensional model. No significant scale effects were encountered for either model through the Reynolds number range investigated.

These data supplement previously reported results of tests on un- swept back models of aspect ratios 3, 4, 5, and 6.

PRELIMINARY WIND-TUNNEL INVESTIGATION OF THE EFFECT OF AREA SUC- RM L7LI5 TION ON THE LAMINAR BOUNDARY LAYER OVER AN NACA 64A010 AIRFOIL, Albert L. Braslow, Fioravante Visconti, and Dale L. Burrows, A preliminary investigation was made in the Langley two- dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Boundary- layer velocity profiles were measured at Reynolds numbers of 2.0 x 106, 4.0 x 106, and 6.0 x 106 and at various chordwise stations for values of the flow coefficient up to 0.012.

Flow measurements were made by means of an orifice plate in the suction duct. The suction flow was taken through one of the model end plates and was regulated by varying the blower speed and the orifice diameter. A conventional multitube total-pressure "mouse" was used to obtain the boundary-layer measurements. The airfoil pressure distribution was obtained from a static-pressure tube on the boundary-layer mouse. Flow coefficients up to 0.008 were used. All tests were made at 0 ° angle of attack.

Results It was indicated that the area suction had a stabilizing effect on the laminar boundary layer in the presence of surface waves and irregularities, at least for the lower range of Reynolds numbers investigated. The suction quantities required to main- tain a laminar layer on this wavy surface were very much greater than the quantity predicted from the theory for small disturb- ances for a smooth flat plate. The results emphasize the neces- sity for obtaining quantitative measurements on a model of stiffer surface construction in order to determine the degree to which area suction is stabilizing in the presence of varying degrees of disturbances and at large values of the Reynolds number.

RML8AI5a AIR-FLOW SURVEYS IN THE VICINITY OF REPRESENTATIVE NACA I- SERIES COWLINGS, Robert W. Boswinkle, Jr., May 1948 Air-flow surveys in the vertical plane of symmetry of six NACA 1-series cowling-spinner combinations and one NACA 1-series nose inlet were conducted in the Langley propeller-research tunnel to obtain quantitative propeller-removed flow-field information useful for the design of propeller shanks and cuffs. The test conditions investigated included the values of inlet-velocity ratio and angle of attack considered most likely to be en- countered in both high-speed and climbing flight. It was found that the gradients in the speeds and directions of the flow are sufficient to warrant consideration in the design of propeller shanks or cuffs for cowling-spinner combinations. The gradients were much less severe over the cowling where the propeller is located in the case of the rotating cowling. The results appear to be directly applicable for propeller design for low and mod- erate Mach numbers; corrections for the effect of Mach number are necessary for high subsonic Mach numbers.

RML8B02 AERODYNAMIC CHARACTERISTICS OF SEVERSL NACA AIRFOIL SECTIONS AT SEVEN REYNOLDS NUMBERS FROM 0.7 x 106 TO 9.0 x 106 , Laurence K.

Loftin, Jr., and M. Irene Poteat, May 1948 An investigation was madeof the two dimensional aerodynamic characteristics of several NACA airfoil sections at four Reynolds numbers from 2.0 x 106 to 0,7 x 106. The group of airfoils tested consisted of four NACA64-series sections varying in thickness from 9 percent to 18 percent and having design lift coefficients of 0.4, and two NACA230-series sections of 12-percent and 15- percent thickness. Data was obtained both with and without split flaps, in the smooth condition and with roughened leading edges.

The results of this test, as well as previously published data, are presented. The airfoil sections for which experimental results were obtained are: 64-409, 641-412, 642-415, 643-418, 23012, and 23015.

Results i. The minimum drag of each of the smooth airfoils increased progressively as the Reynolds number was lowered from 9.0 x 106 to 0.7 x 106 . The magnitude of this increase appeared to become larger as the thickness ratio of the NACA 64-series sections was increased.

2. Decreasing the Reynolds number from 9.0 x 106 to 0.7 x 106 caused a reduction in the maximum lift of all the airfoils both in the smooth and rough condition. The magnitude and character of this reduction, however, varied with airfoil design and surf- ace condition so that the comparative merits of the various air- foils changed markedly with Reynolds number and surface condition.

3. Although the results are not entirely consistent, some de- creases in the lift-curve slope of both the smooth and rough air- foils usually accompanied a reduction in Reynolds number.

4. Both the angle of zero lift and the quarter-chord pitching moment appeared to be nearly independent of variations in the Reynolds number between 9.0 x 106 and 0.7 x 106 .

RML8K22 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF TWO NACA 6-SERIES AIRFOILS'WITH LEADING-EDGE SLATS, Stanley M. Gottlieb, January An investigation was made in a two dimensional low-turbulence tunnel of two NACA 6-series airfoils, the NACA 641-212 and the NACA 65AI09, equipped with leading-edge slats and split flaps deflected 60 ° . The optimum slat positions were determined at a Reynolds number of 2.0 x 106 . The airfoil section lift character- istics were obtained with the slats at the optimum _ositlon tested, at Reynolds number of 2.0 x 106 to 9.0 x 10 °. Pitching- moment characteristics were determined at a Reynolds number of 6.0 x 106.

Results i. Extension of the leading-edge slats caused increases in maximum section lift coefficients and in angles of attack for maximum lift coefficient so that for the NACA 641-212 airfoil section increases in maximum lift coefficient of 0.60 and in angle of attack of 14 ° were attained with flaps retracted and 0.60 and 5 ° with flaps deflected, and for the NACA 65AI09 airfoil section increases in maximum lift coefficient of 0.69 and in angle of attack of i0 ° were attained with flaps retracted and 0.81 and 6 ° with flaps deflected.

2. The split flap was slightly more effective in increasing the maximum section lift coefficient than the leading-edge slat on the airfoils tested.

3. Extension of the leading-edge slats caused the aerodynamic center to move forward to a point apparoximately equal to the quarter-chord point of the extended chord.

4. Extension of the leading-edge slat on the plain airfoil or an increase in Reynolds number on the airfoils with leading-edge slats extended caused the stall to become more gradual.

5. On the NACA 641-212 airfoil section, for which sufficient data were obtained to show optimum slat location, deflection of the split flap caused the optimum slat location to change in such a way as to form a smaller gap between the slat trailing edge and the main part of the airfoil section.

RM L8L08 TWO-DIMENSIONAL AERODYNAMIC CHARACTERISTICS OF 34 MISCELLANEOUS AIRFOIL SECTIONS, Laurence K. Loftin, Jr., and Hamilton A. Smith, January 1949 The aerodynamic characteristics of 34 miscellaneous airfoils tested in the Langley two-dimensional low-turbulence tunnels were present- ed. The data include lift, drag, and in some cases, pitching- moment characteristics, for Reynolds numbers between 3.0 x 106 and 9.0 x 106 . The airfoils consist of modified or unconventional NACA 6-series airfoils and airfoils which were derived by various aircraft manufacturers. The data was presented in the same form as the data in "Theory of Wing Sections" by Abbott, von Doenhoff, and Stivers.

RM L9A20 WIND-TUNNEL INVESTIGATION OF NACA 65,3-418 AIRFOIL SECTION WITH BOUNDARY-LAYER CONTROL THROUGH A SINGLE SUCTION SLOT APPLIED TO A PLAIN FLAP, Albert E. von Doenhoff and Elmer A. Horton, February An investiBation was conducted in the Langley two-dimensional low- turbulence tunnel of the NACA 65,3-418 airfoil section having a

25-percent-airfoil-chord plain flap and a suction slot on the

flap. The tests were conducted at a Reynolds number of 3.20 x 106

for the aerodynamically smooth condition and with leading-edge

roughness. The purpose of the investigation was to determine

the effect of this type of boundary-layer control on the section

lift-drag ratio. Lift and drag of the model for various flap de-

flections were measuredby meansof tunnel floor and ceiling

pressure orifices and wake survey apparatus, respectively. The

quantity of flow through the suction slot was measuredby meansof

a venturi meter. For the rates of flow involved in this investiga-

tion the velocities in the duct of the model were sufficiently

low that the pressure as measuredby the flush orifice within the

duct could be assumedto be total pressure.

Results i. A flow coefficient of 0.0015 was sufficient to delay separa- tion over the flap for a flap deflection of 20 ° up to a lift coefficient of 1.37 for the smooth model and for a flap deflection of 15 ° up toa lift coefficient of approximately 1.0 for the model with leading-edge roughness.

2. For the 20 degree flap deflection, the total drag coeffi- cient, including the drag coefficient equivalent of the boundary- layer control power, was 0.0048 at a lift coefficient of 1.37 for the smooth model; the corresponding value of the section lift to total-drag ratio was 286.

3. Boundary-layer control for the model with leading-edge roughness produced a substantial decrease in the section drag co- efficient at low as well as at high lift coefficients.

4. Boundary-layer control was ineffective in producing any sub- stantial decrease in the minimum section drag coefficient of the smooth model.

5. For the model with leading-edge roughness and a flap deflec- tion of 15 ° , the total drag coefficient was 0.0097 at a lift coefficient of 1.0; the corresponding value of the section lift to total-drag ratio was 103.

6. The data indicate that the maximum lift to total-drag ratio of finite-span wings of reasonable aspect ratio made up entirely of NACA 65,3-418 airfoil sections would not be improved by this type of boundary-layer control for the aerodynamically smooth condition; however, the maximum lift to total-drag ratio for the rough leading-edge condition would be increased by this type of boundary-layer control but would still be less than that of the aerodynamically smooth wing.

RML9B23 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF TWO NACA 7-SERIES

TYPEAIRFOILSEQUIPPED WITHA SLOT-LIPAILERON,TRAILING-EDGE

FRISEAILERON, ANDA DOUBLE SLOTTED FLAP, Albert L. Braslow and

Fioravante Visconti, March 1949

A two dimensional wind-tunnel investigation was madeof two NACA

7-series type airfoils of approximate 17.7-percent chord and 15.4-

percent chord thickness, each equipped with a 30-percent-airfoil-

chord double slotted flap, a slot-lip aileron, and a trailing-

edge Frise aileron with two amounts of aerodynamic overhang

balance. Airfoil lift and drag, Frise aileron hinge moment, and

slot-lip aileron hinge momentwere measured for both airfoils

through a large range of deflection of flap. Frise aileron, and

slot-lip aileron and section angle of attack. During each test

run, the deflections of the movable surfaces were held constant

while the angle of attack was varied in both an increasing and a

decreasing direction. The Reynolds number for all tests was

approximately 6 x 106 and the Machnumber was less than 0.13.

Results Sharp breaks in the lift curves and irregular flow conditions occurred at a flap deflection of 50 ° which indicate the advis- ability of limiting defl_ction of the double slotted flap to 40 ° .

At a flap deflection of 40 ° with both ailerons neutral, values of maximum section lift coefficient of 2.92 and 2.85 were obtained on the 17.7-percent and 15.4-percent thick airfoils, respectively.

The lift effectiveness of the slot lip aileron increased with flap deflection and was greater than the Frise aileron effective- ness at a flap deflection of 40 degrees. With the flap re- tracted, the slot lip aileron lift effectiveness was negligible and slot lip aileron hinge moments indicated an opening tendency at positive deflections of the Frise aileron. The data presented indicated that a slot lip aileron can be combined with a trailing- edge Frise aileron on a full-span double slotted flap so as to provide satisfactory lateral-control characteristics at large flap deflections on a wing having a profile of the NACA 7-series type.

RML9E27 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF A SYMMETRICAL AIR- FOIL SECTION WITH A SEALED INTERNALLY BALANCED CONTROL SURFACE AND A LEADING TAB, Robert J. Nuber and Felicien F. Fullmer, Jr., July 1949 An investigation was made in the Langley two dimensional low- turbulence tunnel of a symmetrical airfoil section equipped with a 0.30-airfoil-chord sealed internally balanced flap having a 0.70-flap-chord overhang and a 0.33-flap-chord leading tab. Air- foil lift, surface pressure, flap hinge-moment, and flap-balance- chamber pressure characteristics were determined at various flap deflections for range of tab-flap deflection ratios from 0.5

to 2.0. The tests were madeat a Reynolds number, for the most part, of about 2.0 x 106 with transition fixed.

Results i. The flap effectiveness, in general, decreased with increasing flap deflection and with increasing angle of attack and increased with increasing tab-flap deflection ratio.

2. Good agreement was obtained between the predicted and experi- mental lift and hlnge-moment parameters for the tab-flap deflec- tion ratios investigated.

3. Deflecting the balance-chamber cover plate outward, in general, decreased the flap effectiveness and caused an increase in the effective aerodynamic balance.

RML56J19 EXPERIMENTAL INVESTIGATION OF FLOW FIELDS AT ZERO SIDESLIP NEAR SWEPT- AND UNSWEPT-WING-FUSELAGE COMBINATION AT LOW SPEED, William J. Afford, Jr., and Thomas J. King, Jr., January 1957 An experimental investigation of the flow fields beneath swept- and unswept-wing-fuselage combinations made at low speed indi- cated that significant gradients in the flow parameters with chordwise and vertical distances were incurred by the finite thickness of the wings at zero angle of attack and that, when the angle of attack was increased, pronounced changes in the gradients occurred. The effect of wing sweep (near zero angle of attack) was to increase the lateral flow angles. The results also indicated that the wing was the predominant factor in dis- turbing the field of flow for the conditions investigated.

The report presented many pages of graphs, for angle of local flow between local flow and wing-fuselage combination in XZ and XY planes, and ratio of local dynamic pressure to free-stream dynamic pressure.

Not Applicable NACA Research Memoranda RM A6G22 A STUDY OF SEVERAL PARAMETERS CONTROLLING THE TRAJECTORIES OF A SUPERSONIC ANTIAIRCRAFT MISSILE POWERED WITH SOLID- OR LIQUID- FUEL ROCKETS_ Ralph F. Huntsberger_ April 1947 RM A6HI9 THE LINEAR PERTURBATION THEORY OF AXIALLY SYMMETRIC COMPRESSIBLE FLOW WITH APPLICATION TO THE EFFECT OF COMPRESSIBILITY ON THE PRESSURE COEFFICIENT AT THE SURFACE OF A BODY OF REVOLUTION_ John G. Herriot_ July 1947 RM A6K22 AERODYNAMIC CHARACTERISTICS INCLUDING SCALE EFFECT OF SEVERAL WINGS AND BODIES ALONE AND IN COMBINATION AT A MACH NUMBER 1.53_ Milton D. Van Dyke_ December 1946 RM A7A31a EXPERIMENTAL INVESTIGATION OF THE EFFECTS OF VISCOSITY ON THE DRAG OF BODIES OF REVOLUTION AT A MACH NUMBER OF 1.5_ Dean R.

Chapman and Edward W. Perkins_ April 1947 RM A7B06 THE CALCULATION OF DRAG FOR AIRFOIL SECTIONS AND BODIES OF REVOLUTION AT SUBCRITICAL SPEEDS_ Max. A. Heaslet and Gerald E.

Nitzberg_ April 1947 RM A7 BIO LOCATION OF DETACHED SHOCK WAVE IN FRONT OF A BODY MOVING AT SUPERSONIC SPEEDS_ Edmund V. Laitone and Otway O'M. Pardee_ May 1947 RM A7B28 BLOCKAGE CORRECTIONS FOR THREE-DIMENSIONAL-FLOW CLOSED-THROAT WIND TUNNELS_ WITH CONSIDERATION OF THE EFFECT OF COMPRESSIBILITY_ John G. Herriot_ July 1947 AERODYNAMIC CHARACTERISTICS AT SUBCRITICAL AND SUPERCRITICAL RM A7CIO MACH NUMBERS OF TWO AIRFOIL SECTIONS HAVING SHARP LEADING EDGES AND EXTREME REARWARD POSITIONS OF MAXIMUM THICKNESS_ A. J.

Eggers_ Jr._ November 1947 RM A7F09 A SUMMARY AND ANALYSIS OF DATA ON DIVE-RECOVERY FLAPS_ Lee E.

Boddy and Walter C. Williams_ September 1947 RM A7FI2 HIGH-SPEED WIND-TUNNEL INVESTIGATION OF THE EFFECTS OF COMPRES- SIBILITY ON A PITOT-STATIC TUBE_ Louis S. Stivers_ Jr. and Charles N° Adams_ Jr._ August 1947 CHARACTERISTICS OF A 15-PERCENT-CHORD AND A 35-PERCENT-CHORD PLAIN RM A7HI9 FLAP ON THE NACA 0006 AIRFOIL SECTION AT HIGH SUBSONIC SPEEDS_ Richard J. llk_ October 1947 RM A7H29 HIGH-SPEED AERODYNAMIC CHARACTERISTICS OF HORN AND OVERHANG BALANCES ON A FULL-SCALE ELEVATOR_ Joseph W. Cleary and Walter J. Krumm_ February 1948 AN EXPLORATORY INVESTIGATION OF THE RELATIVE MERITS OF SPLIT RMA8AI6 AND CHORD-EXTENSION FLAPS ON A 45 ° SWEPT-BACK WING_ Edward J.

Hopkins_ May 1948 RMA8C25 VISUAL OBSERVATION OF THE SHOCK WAVE IN FLIGHT_ George E. Cooper and George A. Rathert_ Jr._ May 1948 EFFECT OF A NACELLE ON THE LOW-SPEED AERODYNAMIC CHARACTERISTICS RM ABEl2 OF A SWEPT-BACK WING_ Frederick H. Hanson_ Jr. and Robert E.

Dannenberg_ July 1948 WIND-TUNNEL INVESTIGATION OF HORIZONTAL TAILS. III - UNSWEPT RM A8H30 AND 35 ° SWEPT-BACK PLAN FORMS OF ASPECT RATIO 6_ Jules B. Dods_ Jr._ December 1948 HEAT-TRANSFER AND BOUNDARY-LAYER TRANSITION ON A HEATED 20 ° CONE RM A8L28 AT A MACH NUMBER OF 1.53_ Richard Scherrer_ William R. Wimbrow_ and Forrest E. Gowen_ January 1949 RM A9EI9 CALCULATIVE METHOD FOR ESTIMATING THE INTERFERENCE PRESSURE FIELD AT ZERO LIFT ON A SYMMETRICAL SWEPT-BACK WING MOUNTED ON A CIRCULAR CYLINDRICAL BODY_ Jack N. Nielsen and Frederick H.

Matteson_ August 1949 RM A52AI8 INSTRUMENTATION OF THE AMES SUPERSONIC FREE-FLIGHT WIND TUNNEL_ Robert O. Briggs_ William J. Kerwin_ and Stanley F. Schmidt_ April 1952 RM A52E23 EFFECTS OF SIMULATED SKIN WRINKLES OF THE WING SURFACE ON THE AERODYNAMIC CHARACTERISTICS OF TWO WING-BODY COMBINATIONS EMPLOY- ING WINGS OF LOW ASPECT RATIO AT SUBSONIC AND SUPERSONIC SPEEDS_ John C. Heitmeyer and William G. Smith_ August 1952 RM A52J31 WIND-TUNNEL INVESTIGATION AT SUBSONIC AND SUPERSONIC SPEEDS OF A MODEL OF A TAILLESS FIGHTER AIRPLANE EMPLOYING A LOW-ASPECT- RATIO SWEPT-BACK WING--EFFECTS OF EXTERNAL FUEL TANKS AND ROCKET PACKETS ON THE DRAG CHARACTERISTICS_ Willard G. Smith_ January RMA52K07 AN EXPERIMENTAL INVESTIGATION OF THE APPLICABILITY OF THE HYPER- SONIC SIMILARITY LAW TO BODIES OF REVOLUTION, Stanford E. Neice and Thomas J. Wong_ January 1953 RM A5 3D02 EXPERIMENTAL INVESTIGATION OF THE ZERO-LIFT DRAG OF A FIN- STABILIZED BODY OF FINENESS RATIO i0 AT MACH NUMBERS BETWEEN 0.6 AND 103 Carlton S. James and Robert J. Carros_ June 1953 RM A53G09 TESTS OF THE NACA 0010-1.50 40/1.051 AIRFOIL SECTION AT HIGH SUBSONIC MACH NUMBERS_ Albert D. Hemenover_ September 1953 RMA53HI2 AN ANALYSIS OF THETRACKING PERFORMANCES OF TWO STRAIGHT-WING ANDTWO SWEPT-WING FIGHTER AIRPLANES WITHFIXEDSIGHTS IN A STANDARDIZED TEST MANEUVER_ GeorgeA. Rathert_ Jr._ Burnett L.

Gadeberg_and HowardL. Ziff_ October 1953 RMA53L22 AN EXPERIMENTAL INVESTIGATION OF FOUR TRIANGULAR-WING-BODY COMBINATIONS IN SIDESLIPAT MACH NI_BERS 0.6_ 0.9_ 1.4_ AND1.7_ Frederik B. Christensen_ March 1954 RMA54A05 AN EVALUATION OF TWO COOLING-AIR EJECTORS IN FLIGHTAT TRANSONIC SPEEDS_ L. Stewart Rolls and C. DeweyHavill_ March 1954 RMA54BI6 EFFECT OF A LEADING-EDGE FLAPUPON THELIFT_ DRAG_ ANDPITCHING MOMENT OF ANAIRPLANE EMPLOYING A THIN_UNSWEPT WING_ John C.

Heitmeyer_ October 1954 RMA54DI9 PRESSURE DISTRIBUTIONS ONTRIANGULAR ANDRECTANGULAR WINGS TO HIGHANGLES OF ATTACK--MACH NUMBERS 1.45 TO 1.97_ GeorgeE.

Kaattari_ June 1954 RMA54JI2 PRESSURE DISTRIBUTIONS ONTRIANGULAR ANDRECTANGULAR WINGS TO HIGHANGLES OF ATTACK--MACH NUMBERS 2.46 AND3.36_ George E.

Kaattari_ January 1955 RMA54KI6 TRACKING PERFORMANCE OF SWEPT-WING FIGHTER WITHDISTURBED RETICLE LEAD-COMPUTING SIGHT[with list of references]_ Burnett L. Gadebergand GeorgeA. Rathert_ Jr._ February 1955 RMA54LI3 INITIAL EXPERIMENTS ONTHEAERODYNAMIC COOLING ASSOCIATED WITH LARGE-SCALE VORTICAL MOTIONS IN SUPERSONIC FLOW_ A. J. Eggers_ Jr. and C. A. Hermach_ March 1955 RMA55C07 FLIGHTTESTS OFLEADING-EDGE AREASUCTION ONFIGHTER-TYPE AIR- PLANE WITH35° SWEPTBACK WING[with list of references]_ Richard S. Bray and Robert C. Innis_ June 1955 RMA55D08 EXPERIMENTAL INVESTIGATION OF SOME AERODYNAMIC EFFECTS OF A GAP BETWEEN WING ANDBODY OF A MODERATELY SLENDER WING-BODY COMBINA- TIONAT A MACH NUMBER OF 1.4_ DuaneW. Dugan_May 1955 RMA55 E02 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OF THEEFFECT OFYAW ONHEAT TRANSFER TO CIRCULAR CYLINDERS IN HYPERSONIC FLOW_ A. J.

Eggers_ Jr._ C. Frederick Hanse_and Bernard E. Cunningham_ July RMA55E26 SOME ASPECTS OF THEDESIGN OF HYPERSONIC BOOST-GLIDE AIRCRAFT_ Alvin Seiff and H. Julian Allen_ August 1955 RMA55FI5 DRAG ANDROLLING-MOMENT EFFECTIVENESS OF TRAILING-EDGE SPOILERS AT MACH NUMBERS 2.2 AND5.0_ ThomasN. Canning and Charles E.

DeRose_ October 1955 A DISCUSSION OFMETHODS FORREDUCING AERODYNAMIC HEATING IN SUPER- RMA55F21a SONIC FLIGHT,A. J. Eggersj Jr., September 1955 RMA55F23 PRELIMINARY EXPERIMENTAL INVESTIGATION OF A VARIABLE-AREA, VARIABLE-INTERNAL-CONTRACTION AIR INLETAT MACH NUMBERS BETWEEN 1.42 AND2.44_ Richard Scherrer and Forrest E. Gowen,September TEMPERATURE RECOVERY FACTORS ONA SLENDER 12° CONE-CYLINDER AT RMA55G20 MACH NUMBERS FROM 3.0 TO 6.3 ANDANGLES OF ATTACK UP TO 45o_ John O. Relier, Jr., and Frank M. Hamaker_October 1955 RMA55H04a EFFECT OF LEADING-EDGE SWEEPBACK ONLIFT, DRAG_ ANDPITCHING- MOMENT CHARACTERISTICS OF THINWINGS OF ASPECT RATIO4 ANDTAPER RATIO0.4 AT SUBSONIC ANDSUPERSONIC SPEEDS_ Benton E. Wetzel_ November1955 EFFECTS OF BOUNDARY-LAYER SEPARATION ONNORMAL FORCE ANDCENTER RMA55H09 OF PRESSURE OF CONE-CYLINDER MODEL WITHLARGE BASE FLAREAT MACH NUMBERS FROM 3.00 TO 6.28_ David H. Dennis and Clarence A.

Syverson_ October 1955 INVESTIGATION OFLOCALHEAT-TRANSFER ANDPRESSURE DRAG CHARACTER- RMA55H31 ISTICS OFA YAWED CIRCULAR CYLINDER AT SUPERSONIC SPEEDS_ Glen Goodwin_ Marcus O. Creager_ and Ernest L. Winkler, January 1956 RMA55J07 AERODYNAMIC CHARACTERISTICS OF TWO RECTANGULAR-PLAN-FORM_ ALL- MOVABLE CONTROLS IN COMBINATION WITHA SLENDER BODY OF REVOLUTION AT MACH NUMBERS FROM 3.00 TO 6.25_ ThomasJ. Wongand Hermilo R.

Gloria_ December1955 APPLICATION OF TCHEBICHEF FORM OF HARMONIC ANALYSIS TO THE RMA55J28 CALCULATION OF ZERO-LIFT WAVE DRAG OF WING-BODY-TAlL COMBINATIONS_ GeorgeH. Holdaway and William A. Mersman_ February 1956 RMA55K01 A FLIGHTEVALUATION OF A WING-SHROUD-BLOWING BOUNDARY-LAYER CON- TROLSYSTEM APPLIED TO THEFLAPSOF ANF9F-4 AIRPLANE_ L. Stewart Rolls and Robert C. Innis_ February 1956 RMA55K07 EFFECTS OF TWO TRAILING-EDGE CONTROLS ON THE AERODYNAMIC CHARAC- TERISTICS OF A RECTANGULAR WING AND BODY COMBINATION AT MACH NUMBERS FROM 3.00 TO 5.05, Hermilo R. Gloria and Thomas J. Wong_ February 1956 RM A55K09 FORCE_ MOMENT_ AND PRESSURE-DISTRIBUTION CHARACTERISTICS OF RECTANGULAR WINGS AT HIGH ANGLES OF ATTACK AND SUPERSONIC SPEEDS_ William C. Pitts_ February 1956 RMA55K21 LIFT, DRAG_ AND STATIC LONGITUDINAL STABILITY CHARACTERISTICS OF CONFIGURATIONS CONSISTING OF THREE TRIANGULAR WING PANELS AND A BODY OF EQUAL LENGTH AT MACH NUMBERS FROM 3.00 TO 6.28_ Raymond C. Savin and Thomas J. Wong_ February 1956 RMA55K30 A STUDY OF A MISSILE DESIGNED TO FLY AT LOW SPEED WITH ITS LONGITUDINAL AXIS ALINED WITH THE FLIGHT PATH_ Edward J. Hopkins and Norman E. Sorensen_ February 1956 RMA55L05 AIRCRAFT CONFIGURATIONS DEVELOPING HIGH LIFT-DRAG RATIOS AT HIGH SUPERSONIC SPEEDS_ A. J. Eggers_ Jr._ and Clarence A. Syvertson_ March 1956 _5_9 INVESTIGATION OF THE POSSIBILITY OF SIMPLIFYING MISSILE GUIDANCE SYST_2dS BY THE USE OF FREE-FLOATING FLAPS AND SPRING-MOUNTED CONTROL SURFACES_ Katsumi Hikido_ Paul H. Hayashi_ and Henry Co Lessing_ May 1956 RMA55LI3a HEAT-TRANSFER CHARACTERISTICS OF BLUNT 2 AND 3-DIMENSIONAL BODIES AT SUPERSONIC SPEEDS_ Glen Goodwin_ February 1956 RMA55LI3b AERODYNAMICS OF MISSILES EMPLOYING WINGS OF VERY LOW ASPECT RATIO [with list of references]_ Elliott D. Katzen and Leland H.

Jorgensen_ March 1956 RMA55LI4 PRELIMINARY REPORT ON A STUDY OF SEPARATED FLOWS IN SUPERSONIC AND SUBSONIC STREAMS_ Dean R. Chapman_ Donald M. Kuehnj and Howard K. Larson_ June 1956 RMA55LI4a EXTERNAL-STORE DRAG REDUCTION AT TRANSONIC AND LOW SUPERSONIC MACH NUMBERS BY APPLICATION OF BALDWIN'S MOMENT-OF-AREA RULE_ Lionel L. Levy_ Jr._ and Robert R. Dickey_ March 1956 RMA55LI5 PROBL_S OF PERFORMANCEAND HEATING OF HYPERSONIC VEHICLES_ H. Julian Allen and Stanford E. Neice_ March 1956 RMA55L21 REVIEW OF RECENT INFORMATION ON BOUNDARY-LAYER TRANSITION AT SUPERSONIC SPEEDS [with list of references]_ Frank A. Lazzeroni and Frank A. Pfyl_ February 1956 RMA56B27a A METHOD OF REDUCING HEAT TRANSFER TO BLUNT BODIES BY AIR INJECTION_ Jackson R. Stalder and Mamoru Inouye_ May 1956 A.56C0 6 THE CHANGE WITH MASS-FLOW RATIO OF THE COWL PRESSURE DRAG OF NORMAL-SHOCK INLETS AT SUPERSONIC SPEEDS_ Wallace F. Davis and Forrest E. Gowen_ June 1956 EXPERIMENTAL INVESTIGATION AT MACHNUMBERS FROM 2.1 TO 3.0 OF RM A56GO 6 CIRCULAR-INTERNAL-CONTRACTION INLETS WITH TRANSLATING CENTER- BODIES [with list of references]_ Emmet A. Mossman and Frank A.

Pfy_October 1956 LARGE-SCALE WIND-TUNNEL TESTS OF AN AIRPLANE MODEL WITH A 45 ° RM A56H08 SWEPTBACK WING OF ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED TO TRAILING-EDGE FLAPS AND WITH SEVERAL WING LEADING-EDGE MODIFICATIONS_ David G. Koenig and Kiyoshi Aoyagi_ November 1956 RMA56H27 AN EXPERIMENTAL INVESTIGATION OF THELIFT_ DRAG_ ANDSTATIC- STABILITYCHARACTERISTICS OFA TRIANGULAR-WING AIRPLANE AT MACH NUMBERS FROM 3.00 TO 6.28_ Hermilo R. Gloria_ December1956 RMA56H31 AERODYNAMIC CHARACTERISTICS IN PITCHOF SEVERAL TRIPLE-BODY MISSILE CONFIGURATIONS AT MACH NUMBERS FROM 0.6 TO 1.4_ Earl D. Knechtel and Arvid N. Andrea_ November1956 SOME EXPERIMENTS AT HIGHSUPERSONIC SPEEDS ONAERODYNAMIC AND RMA56105 BOUNDARY-LAYER TRANSITION CHARACTERISTICS OFHIGH-DRAG BODIES OF REVOLUTION 3 Alvin Seiff_ Simon C. Sommer_ and ThomasN. Canning_ January 1957 EXPERIMENTAL INVESTIGATION OF A METHOD OF WAVE-DRAG REDUCTION RMA56118 FORCOMBINATIONS EMPLOYING QUASI-CYLINDRICAL BODIES AND SWEPT WINGS AT SUPERSONIC SPEEDS_ Daniel P. Hickey_ February 1957 THE EFFECT OF BODY CONTOURING ON THE LONGITUDINAL CHARACTERISTICS RM A56J08 AT MACH NUMBERS UP TO 0.92 OF A WING-FUSELAGE-TAlL AND SEVERAL WING-FUSELAGE COMBINATIONS HAVING SWEPTBACK WINGS OF RELATIVELY HIGH ASPECT RATIO_ Fred B. Sutton and J. Walter Lautenberger_ Jr.j January 1957 RM A56K26 INVESTIGATION OF SYMMETRICAL BODY INDENTATIONS DESIGNED TO REDUCE THE TRANSONIC ZERO-LIFT WAVE DRAG OF A 45 ° SWEPT WING WITH AN NACA 64A006 SECTION AND WITH A THICKENED LEADING-EDGE SECTION 3 George H. Holdaway and Elaine W. Hatfield_ March 1957 RM A56LI8 EFFECTS OF CONICAL CAMBER ON THE LIFT_ DRAG_ AND PITCHING-MOMENT CHARACTERISTICS OF A TRIANGULAR WING OF ASPECT RATIO 3.0_ Victor L. Peterson and John W. Boyd_ February 1957 RM A57AO 2 AN INVESTIGATION OF WING-BODY JUNCTURE INTERFERENCE EFFECTS AT TRANSONIC SPEEDS FOR SEVERAL SWEPT-WING AND BODY COMBINATIONS 3 John B. McDevitt and Robert A. Raylor_ May 1957 RM A57A25 LATERAL-DIRECTIONAL AERODYNAMIC CHARACTERISTICS OF SEVERAL CO- PLANAR TRIPLE-BODY MISSILE CONFIGURATIONS AT MACH NUMBERS FROM 0.6 TO 1.43 Stuart L. Treon and Earl D. Knechtel 3 April 1957 RM A57BII LEADING-EDGE CONTOURS FOR THIN SWEPT WINGS: AN ANALYSIS OF LOW- AND HIGH-SPEED DATA_ William T. Evans_ March 1957 RM A57BI4 A FLIGHT INVESTIGATION OF AREA-SUCTION AND BLOWING BOUNDARY- LAYER CONTROL ON THE TRAILING-EDGE FLAPS OF A 35 ° SWEPT-WING CARRIER-TYPE AIRPLANE_ Hervey C. Quigley_ Francis W. K. Hom_ and Robert C. Innis 3 April 1957 RM A57C25 INVESTIGATION OF BOUNDARY-LAYER TRANSITION ON FLAT-FACED BODIES OF REVOLUTION AT HIGH SUPERSONIC SPEEDS_ Thomas N. Canning and Simon C. Sommer_ June 1957 RMA57DII WIND-TUNNEL TESTS OF STATICLONGITUDINAL CHARACTERISTICS AT LOW SPEED OF SWEPT-WING AIRPLANE WITHBLOWING FLAPSANDLEADING-EDGE SLATS_ Harry A. Jamesand Ralph A. Maki_ July 1957 RMA57D30 A COMPARISON OF CARRIER APPROACH SPEEDS AS DETERMINED FROM FLIGHT TESTS ANDFROM PILOT-OPERATED SIMULATOR STUDIES_ Maurice D. White and Fred J. Drinkwater_ III_ June 1957 RMA57E02 THEEFFECTS AT SUBSONIC SPEEDS OFWING FENCES ANDA TAIL ONTHE LONGITUDINAL CHARACTERISTICS OF A 63° SWEPT-WING ANDFUSELAGE COMBINATION_ Donald A. Buell and Carl D. Kolbe_ July 1957 RMA57EI5 SOME PROPERTIES OF WING ANDHALF-BODY ARRANGEMENTS AT SUPERSONIC SPEEDS_ EugeneMigotsky and Gaynor J. Adams_July 1957 RMA57E24 INVESTIGATION OF AXIALLYSYMMETRIC FLOW OVER STEPS AT TRANSONIC SPEEDS WITHCOMPARISONS OF ESTIMATED ANDEXPERIMENTAL DRAG RE- SULTS_ GeorgeH. Holdaway and Minor R. Wallace_ Jr._ July 1957 RMA57F03a HEATTRANSFER TO BLUNT NOSE SHAPES WITHLAMINAR BOUNDARY LAYERS AT HIGHSUPERSONIC SPEEDS_ John O. Reller_ Jr.j August 1957 RMA57F06a A BUFFET INVESTIGATION AT HIGHSUBSONIC SPEEDS OFWING-FUSELAGE- TAlL COMBINATIONS HAVING SWEPTBACK WINGS WITHNACA64A THICKNESS DISTRIBUTIONS_ FENCESj A LEADING-EDGE EXTENSION_ ANDBODY CON- TOURING_ Fred B. Sutton and J. Walter Lautenberger_ Jr._ August RMA57FO 6b EFFECTS OF WING-TIPDROOP ONTHELONGITUDINAL CHARACTERISTICS OF TWO HIGHLY SWEPT WING-BODY COMBINATIONS AT MACH NUMBERS FROM 0.6 TO 1.4_ Earl D. Knechtel and GeorgeLee_ August 1957 RMA57GI0 FLIGHTINVESTIGATION OF THELOW-SPEED CHARACTERISTICS OF A 35° SWEPT-WING AIRPLANE EQUIPPED WITHAN AREA-SUCTION EJECTOR FLAP ANDVARIOUS WING LEADING-EDGE DEVICES_ Seth B. Anderson_ Alan E.

Faye_ Jr._ and Robert C. Innis_ September 1957 RMA57H19 EFFECTS OF A LEADING-EDGE SLATANDA TRAILING-EDGE SPLIT FLAPON THEAERODYNAMIC CHARACTERISTICS OFA WING-FUSELAGE COMBINATION HAVING A NEARLY TRIANGULAR WINGOFASPECT RATIO2.9 AT MACH NUMBERS FROM 0.60 TO0.92_ Fred A. Demele_January 1958 RMA57H19 a A TRANSONIC INVESTIGATION OF THEEFFECTS OF SEMISUBMERGED-STORE CAVITIESANDOF SLOTS ONTHEZERO-LIFT DRAG OF A BODY OF REVOLU- TION_GeorgeH. Holdaway_Minor R. Wallace_ Jr. 3 and Elaine W.

Hatfield_ October 1957 RMA57H21 THEUSEOFA LEADING-EDGE AREA-SUCTION FLAPANDLEADING-EDGE MODIFICATIONS TO IMPROVE THEHIGH-LIFTCHARACTERISTICS OFAN AIRPLANE MODEL WITHA WING OF 45° SWEEP ANDASPECT RATIO2.8_ David G. Koenig and Kiyoshi Aoyagi_ November1957 RMA57109 EFFECTS OF STING-SUPPORT INTERFERENCE ONTHEDRAG OFAN OGIVE' CYLINDER BODY WITHANDWITHOUT A BOATTAIL AT 0.6 TO 1.4 MACH NUMBER_ GeorgeLee and JamesL. Summers_ December1957 RMA57110 EFFECTS OF VERTICAL LOCATION OFWING ANDHORIZONTAL TAIL ONTHE AERODYNAMIC CHARACTERISTICS IN PITCHAT MACH NUMBERS FROM 0.60 TO 1.40 OF ANAIRPLANE CONFIGURATION WITHAN UNSWEPT WING_Louis S. Stivers_ Jr._ and Garth W. Lippmann_November1957 RMA57117 EXPERIMENTAL LIFT OF LOW-ASPECT-RATIO TRIANGULAR WINGS AT LARGE ANGLES OF ATTACK ANDSUPERSONIC SPEEDSj William A. Hill_ Jr._ November1957 RMA57126 EXPERIMENTAL INVESTIGATION OF THESIMULATION OF ATMOSPHERIC ENTRY OF BALLISTICMISSILES_Stanford E. Neice_ JamesA. Carson_ and Bernard E. Cunningham_ December1957 AN INVESTIGATION OF THECONTROL EFFECTIVENSSS OF TIP AILERONS AND RMA57126a SPOILERS ONA LOW-ASPECT-RATIO TRAPEZOIDAL-WING AIRPLANE MODEL AT MACH NUMBERS FROM 1.55 TO 2.35_ NormanD. Wong_December1957 RMA57130 EFFECTS OF BOUNDARY-LAYER SEPARATION OVER BODIES OF REVOLUTION WITHCONICAL TAlL FLARES_ David H. Dennis_ December1957 RMA57JI6 TRANSONIC LATERAL ANDLONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A LATERAL-CONTROL SYSTEM _PLOYINGROTATABLE AIRFOILSMOUNTED VERTICALLY AT THEWING TIPS OFAN UNSWEPT WING-FUSELAGE-TAlL COMBINATION_ John A. Axelso_ January 1958 RMA57K01 WIND-TUNNEL INVESTIGATION OF THEUSEOFLEADING-EDGE ANDTRAILING- EDGE AREA-SUCTION FLAPSONA 13-PERCENT-THICK STRAIGHT WING AND FUSELAGE MODEL_ Curt A. Holzhauser_ January 1958 SUBSONIC AERODYNAMIC CHARACTERISTICS UP TO EXTREME ANGLES OF RMA57K05 ATTACK OFAN AIRPLANE MODEL HAVING AN UNSWEPT WING ANDA HIGH HORIZONTAL TAIL_ Bruce E. Tinling_ February 1958 HEATTRANSFER ONAFTERBODY IMMERSED IN SEPARATED WAKE OF H_MI- RMA57K07a SPHERE_ Helmer V. Nielsen_ January 1958 EXPERIMENTAL LIFT-DRAG RATIOS FORTWO FAMILIESOFWING-BODY RMA58A08 COMBINATIONS AT SUPERSONIC SPEEDS_ Leland H. Jorgensen_ March LARGE-SCALE WIND-TUNNEL TESTS OF AN AIRPLANE MODEL WITHA 45o RMA58A09 SWEPTBACK WING OF ASPECT RATIO2.8 EMPLOYING HIGH-VELOCITY BLOW- ING OVER THELEADING- ANDTRAILING-EDGE FLAPS_David H. Hickey and Kiyoshi Aoyagi_ May 1958 RMA58A31 THEEFFECT OFMOMENT-OF-AREA-RULE MODIFICATIONS ONTHEZERO-LIFT DRAG OF THREE WING-BODY COMBINATIONS_ Robert R. Dickey_ May 1958 RMA58DI4 DATA FROM FLOW-FIELD SURVEYS BEHIND LARGE-SCALE THIN STRAIGHT WING OF ASPECT RATIO3 [with list of references]_ William T. Evans_ June RMA58DI5 EXPERIMENTAL INVESTIGATION OF THEDRAG DUETOWEDGES ALONG THE TRAILINGEDGE OF A SWEPT WING_ Bruno J. Gambucciand John A.

Wyss_June 1958 RMA58D25 PROSPECTS FORLAMINAR FLOW ONHYPERSONIC AIRPLANES, Alvin Seiff, June 1958 RMA58E05 FLIGHTINVESTIGATION OFTHELOW-SPEED CHARACTERISTICS OFA 45° SWEPT-WING FIGHTER-TYPE AIRPLANE WITHBLOWING BOUNDARY-LAYER CONTROL APPLIED TO THETRAILING-EDGE FLAPS_Hervey C. Quigley, Seth B. Anderson, and Robert C. Innis_ August 1958 RMA58EI9 EXPERIMENTAL INVESTIGATION OF THEEFFECT OFYAW ONRATES OF HEAT TRANSFER TO TRANSVERSE CIRCULAR CYLINDERS IN A 6500-FOOT-PER- SECOND HYPERSONIC AIR STREAM_ Bernard E. Cunningham and Samuel Kraus_ August 1958 RMA58E21a FORCES ANDPITCHING MOMENTS ONAN ASPECT-RATIO-3.1 WING-BODY COMBINATION AT MACH NUMBERS FROM 2.5 TO 3.5 ANDSUBLIMATION STUDIES OF THEEFFECT OF SINGLE-ELEMENT ROUGHNESS ONTHE BOUNDARY-LAYER FLOW,EdwardJ. Hopkins_ Stephen J. Keating_ Jr., and Richard R. Muhl_ August 1958 RMA58F02 APPROXIMATE SOLUTIONS FORFLOW ABOUT FLAT-TOP WING-BODY CON- FIGURATIONS AT HIGHSUPERSONIC AIRSPEEDS_ Raymond C. Savin_ September 1958 RMA58FO 3 WIND-TUNNEL INVESTIGATION OF THELOW-SPEED AERODYNAMIC CHARACTER- ISTICS OF A HYPERSONIC GLIDER CONFIGURATION_ Mark W. Kelly, September 1958 RMA58HI2 LARGE-SCALE WIND-TUNNEL TESTS OF JET-TRANSPORT-TYPE MODEL WITH LEADING ANDTRAILINGEDGE HIGH-LIFT DEVICES, David H. Hickey and Koyoshi Aoyagi_ September 1958 RME50J23a METHODS FORCONNECTION TO REVOLVING THERMOCOUPLES_ Philip R. Tarr_ January 1951 RME5 IHI7 AERODYNAMIC CHARACTERISTICS OF A SLENDER CONE-CYLINDER BODY OF REVOLUTION AT A MACH NUMBER OF 3.85_ John R. Jack, November1951 AERODYNAMICS OF SLENDER BODIES AT MACH NUMBER OF 3.12 ANDREYNOLDS RME52CI0 NUMBERS FROM 2 x i06 TO 15 x I06 . II - AERODYNAMIC LOAD DIS- TRIBUTIONS OF SERIES OF FIBE BODIES HAVING CONICAL NOSES AND CYLINDRICAL AFTERBODIES_ John R. Jack and Lawrence I. Gould_ May RME52EI3 INFLUENCE OFA CANARD-TYPE CONTROL SURFACE ONFLOW FIELD IN VICINITY OF SYMMETRICAL FUSELAGE AT MACH NUMBERS 1.8 AND2.0_ GeorgeA. Wise and Murray Dryer_ July 1952 RME53E04 MEASUREMENTS OF HEAT-TRANSFER AND FRICTION COEFFICIENTS FOR AIR FLOWING IN TUBE OF LENGTH-DIAMETER RATIO OF 15 AT HIGH SURFACE TEMPERATURES_ Walter F. We[land and Warren H. Lowdermilk_ July RME53E07 INVESTIGATION OF AERODYNAMIC AND ICING CHARACTERISTICS OF FLUSH ALTERNATE-INLET INDUCTION SYSTEM AIR SCOOP_ James P. Lewis_ July RME53 E28 EXPERIMENTAL INVESTIGATION OF EFFECTS OF SUPPORT INTERFERENCE ON PRESSURE DISTRIBUTION OF A BODY OF RE_OLUTION ATTACH NUMBER OF 3.12 AND REYNOLDS NUMBERS FROM 2 x i0 v TO 14 x I0_ L. Eugene Baughman and John R. Jack_ August 1953 RME53F02 PRELIMINARY RESULTS OF HEAT TRANSFER FROM STATIONARY AND ROTATING ELLIPSOIDAL SPINNER_ U. von Glahn_ August 1953 RME53F19 MEASUREMENT AND ANALYSIS OF TURBULENT FLQW CONTAINING PERIODIC FLOW FLUCTUATIONS_ William R. Mickelsen and James C. Laurence_ August 1953 PRELIMINARY DRAG AND HEAT-TRANSFER DATA OBTAINED FROM AIR- RME53104 LAUNCHED CONE-CYLINDER TEST VEHICLE OVER MACH NUMBER RANGE FROM 1.5 TO 5.18_ Wesley E. Messing_ Leonard Rab_ and John H. Disher_ November 1953 RME53J07 MEASUREMENT OF HEAT-TRANSFERAND FRICTION COEFFICIENTS FOR FLOW OF AIR IN NONCIRCULAR DUCTS AT HIGH SURFACE TEMPERATURESj Warren H. Lowdermilk_ Walter F. Weilandj Jr._ and John N. B. Livingood_ December 1954 RME53J27 AERODYNAMICS OF SLENDER BODIES AT MACH NUMBER OF 3.12 AND REYNOLDS NUMBERS FROM 2 x 106 TO 15 x 106 . IV - AERODYNAMIC CHARACTERIS- TICS OF SERIES OF FOUR BODIES HAVING NEAR-PARABOLIC NOSES AND CYLINDRICAL AFTERBODIES_ John R. Jack and Barry Moskowitz_ Jan- uary 1954 RME53L29b FORCE MEASUREMENTS ON CONE-CYLINDER BODY OF REVOLUTION WITH VARIOUS NOSE AND FIN CONFIGURATIONS AT MACH NUMBER 4.0_ Leonard Rabb and Wesley E. Messing_ March 1954 RME54BII AERODYNAMICS OF SLENDER BODIES AT MACH NUMBER OF 3.12 AND REYNOLDS NUMBERS FROM 2 x 106 TO 15 x 106 . V - AERODYNAMIC LOAD DISTRIBU- TIONS FOR A SERIES OF FOUR BOAT-TAILED BODIES_ Barry Moskowitz and John R. Jack_ May 1954 RME54DI2 FORCED-CONVECTION HEAT-TRANSFER ANDPRESSURE-DROP CHARACTERISTICS OFA CLOSELY SPACED WIREMATRIX_ Louis Gedeonand Milton D. Grel% August RME54FII EXPERIMENTAL HEAT-TRANSFER ANDFRICTIONCOEFFICIENTS FORAIR FLOW- ING THROUGH STACKS OF PARALLEL FLATPLATES [with list of refer- ences]_ Eldon W. Samsand Walter F. Weiland_ Jr._ August 1954 RME54G28 EFFECTS OF SECONDARY-AIR FLOW ONANNULAR BASE FORCE OF SUPERSONIC AIRPLANE_ Donald J. Vargo_ October 1954 RME54LI4 WIND-TUNNEL INVESTIGATION AT MACH 1.9 OFMULTIJET-MISSILE BASE PRESSURES [with list of references]_ L. EugeneBaughman_ March RME55D0 7b EXPLORATORY INVESTIGATION OFFLOW IN SEPARATED REGION AHEAD OF TWO BLUNT BODIES AT MACH NUMBER 2 [with list of references]_ Harry Bernstein and William E. Brunk_ June 1955 RME55F27 FREE-FLIGHT HEAT-TRANSFER MEASUREMENTS ONTWO 20°-CONE-CYLINDERS AT MACH NIIMBERS FROM 1.3 TO 4.9_ Leonard Rabb and Scott H.

Simpkinso% July 1955 RME55115 BOUNDARY-LAYER TRANSITION AT HIGHREYNOLDS NUMBERS AS OBTAINED IN FLIGHTOFA 20° CONE-CYLINDER WITHWALL TOLOCALSTREAM TEMPERATURE RATIOS NEAR1.0_ Leonard Rabb and John H. Disher_ November1955 RME56EI0 BOUNDARY-LAYER TRANSITION AT SUPERSONIC SPEEDS_ GeorgeM. Low_ August 1956 OBSERVATION OFLAMINAR FLOW ONBLUNTED 15° CONE-CYLINDER IN RME56G23 FREEFLIGHTAT HIGHREYNOLDS NUMBERS ANDFREE-STEAM MACH NUMBERS TO 8.17_ John H. Disher and Leonard Rabb_October 1956 OBSERVATION OF LAMINAR FLOW ONAIR-LAUNCHED 15° CONE-CYLINDER RME5 6LO 3 AT LOCAL REYNOLDS NUMBERS TO50 x 106 AT PEAK MACH NUMBER OF 6.75_ Leonard Rabb and Milan J. Krasnician_ March 1957 RME56L04 ARRANGEMENTS OF JET ENGINE ANDAIRFRAME FORINCREASED RANGE_ Roger W. Luidens_ July 1957 RME57E06 JET EFFECTS ONBASE PRESSURES OF CONICAL AFTERBODIES AT MACH 1.91 AND3.12_ L. EugeneBaughman and Fred D° Kochendorfer_ August 1957 RME57FI0 FREE-FLIGHT DETERMINATION OF BOUNDARY-LAYER TRANSITION ANDHEAT TRANSFER FORHEMISPHERE-CYLINDER AT MACH NUMBERS TO 5.6_ M. J.

Krasnician and R. J. Wisniewski_ October 1957 53O EFFECTS OF SURFACE ROUGHNESS AND EXTREME COOLING ON BOUNDARY- RME57KI9 LAYER TRANSITION FOR 15 ° CONE-CYLINDER IN FREE FLIGHT AT MACH NUMBERS TO 7.6_ Leonard Rabb and Milan J. Krasnican_ March 1958 RME57K19a CORRELATION OF TURBULENT HEAT TRANSFER IN TUBE FOR DISSOCIATING SYSTEM N204 2NO 2 [with list of references]_ Richard S. Brokaw_ March 1958 RME57LI9 PRELIMINARY SURVEY OF POSSIBLE COOLING METHODS FOR HYPERSONIC AIRCRAFT_ Jack B. Esgar_ Robert O. Hickel_ and Francis S. Stepka_ May 1958 RME58A03a DILUTION OF LIQUID OXYGEN WHEN NITROGEN IS USED FOR PRESSURIZA- TION [with list of references]_ Thomas J. Walsh_ R. R. Hibbardj and Paul M. Ordin 3 April 1958 RME58GI7 EXPERIMENTAL STUDY OF BALLISTIC-MISSILE BASE HEATING WITH OPERATING ROCKET_ J. Cary Nettles_ September 1958 RMH54HO 6 WING PRESSURE DISTRIBUTIONS AT LOW LIFT FOR THE XF-92A DELTA- WING AIRPLANE AT TRANSONIC SPEEDS_ Earl R. Keenerj October 1954 RMH55A03 FLIGHT-DETERMINED PRESSURE DISTRIBUTIONS OVER A SECTION OF THE 35 ° SWEPT WING OF THE DOUGLAS D-558-II RESEARCH AIRPLANE AT MACH NUMBERS UP TO 2.0_ Gareth H. Jordan and Earl R. Keener_ March RMH56EO 2 LIFT AND DRAG OF THE BELL X-5 RESEARCH AIRPLANE IN THE 45 ° SWEPTBACK CONFIGURATION AT TRANSONIC SPEEDS_ Jack Nugent_ July H56E08 FLIGHT-DETERMINED TRANSONIC LIFT AND DRAG CHARACTERISTICS OF THE YF-102 AIRPLANE WITH TWO WING CONFIGURATIONS_ Edwin Jo Saltzman_ Donald R. Bellman_ and Norman T. Musialowski_ July 1956 RM H57A02 STATIC-PRESSURE ERROR CALIBRATIONS FOR NOSE-BOOM AIRSPEED INSTAL- LATIONS OF 17 AIRPLANES_ Terry J. Larson_ Wendell H. Stillwell_ and Katharine H. Armistead_ March 1957 RM H57DI8b FLIGHT MEASUREMENTS OF AIRPLANE STRUCTURAL TEMPERATURES AT SUPER- SONIC SPEEDS_ Richard D. Banner_ June 1957 EFFECT OF WING-MOUNTED EXTERNAL STORES IN THE LIFT AND DRAG OF RM H57EI5a THE DOUGLAS D-558-II RESEARCH AIRPLANE AT TRANSONIC SPEEDS_ Jack Nugent_ July 1957 RM H5 7J30 A SIMULATOR INVESTIGATION OF FACTORS AFFECTING THE DESIGN AND UTILIZATION OF A STICK PUSHER FOR THE PREVENTION OF AIRPLANE PITCH-UP_ Euclid C. Holleman and David L. Boslaugh_ January 1958 RMH58B24 FLIGHTINVESTIGATION OF THEAERODYNAMIC FORCES ONA WING-MOUNTED EXTERNAL-STORE INSTALLATION ONTHEDOUGLAS D-558-II RESEARCH AIR- PLANE_ Clinton T. Johnson_May 1958 RML6H28a INVESTIGATION OF THECHARACTERISTICS OFA HIGH-ASPECT RATIOWING IN THELANGLEY 8-FOOTHIGH-SPEED TUNNEL_ Richard T. Whitcomb_ August 1946 RML6KI8a EFFECTS OF 45° SWEEPBACK ONTHEHIGH-SPEED CHARACTERISTICS OFA WING HAVING A MODIFIED NACA16-012 AIRFOIL SECTION_ Luke L.

Liccinij July 1947 RML6K20 FULL-SCALE INVESTIGATION OF THEMAXIMUM LIFT ANDFLOW CHARACTERIS- TICS OF AN AIRPLANE HAVING APPROXIMATELY TRIANGULAR PLANFORM_ Herbert A. Wilson_ Jr._ and J. Calvin Lovell 3 February 1947 RML7C24 EFFECTS OF COMBINATIONS OFASPECT RATIOANDSWEEPBACK AT HIGH SUBSONIC MACH NUMBERS_ Alfred A. Adler_ June 1947 RML7F24 ESTIMATE OF HULL-WEIGHT CHANGE WITHVARYING LENGTH-BEAM RATIO FORFLYINGBOATS_ Stanley U. Benscoter_ August 1947 RML7HO5a PERFORMANCE POSSIBILITIESOF THETURBOJET SYSTEM ASA POWER PLANT FORSUPERSONIC AIRPLANES_ GeorgeP. Wood_August 1947 RML7H27 THEEFFECT OF SAMPLE SIZE ONTHEDETERMINATION OFMAXIMUM GUST VELOCITIES IN CLOUDS_ Harry Press_ October 1947 RMLSAI5a AIR-FLOW SURVEYS IN THEVICINITY OF REPRESENTATIVE NACA 1-SERIES COWLINGS_ Robert W. Boswinkle_ Jr._ May 1948 RML8C22 SOME FLIGHTMEASUREMENTS OFPRESSURE-DISTRIBUTION ANDBOUNDARY- LAYERCHARACTERISTICS IN THEPRESENCE OF SHOCK_ John A. Zalovcik and Ernest P. Luke_ July 1948 RML8G30a THEEFFECTS OF FRICTION IN THECONTROL SYSTEM ONTHEHANDLING QUALITIES OF A C-54D AIRPLANE_ Donald B. Talmage and John P.

Reeder_ November1948 RML8101 AN EVALUATION OFAIR-BORNE RADAR AS A MEANS OFAVOIDING ATMOSPHERIC TURBULENCE_ Roy Steiner_ November1948 RESULTS OBTAINED DURING EXTENSION OF U. S. AIR FORCE TRANSONIC - RML8128 FLIGHTTESTS OF XS-I AIRPLANE_ Harold R. Goodman and Hubert M.

Drake_ November 1948 RML8JI4 NOTE ONTHEIMPORTANCE OF IMPERFECT-GAS EFFECTS ANDVARIATION OF HEATCAPACITIES ONTHEISENTROPIC FLOW OF GASES_ Colemandu P.

Donaldson_ December1948 RMLSK22 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF TWO NACA6-SERIES AIRFOILSWITHLEADING-EDGE SLATS_ Stanley M. Gottlieb_ January RML9A03 AERODYNAMIC CHARACTERISTICS OF A FLYING-BOAT HULLHAVING A LENGTH-BEAM RATIOOF 15 ANDA WARPED FOREBODY_ Richard G. MacLeod_ February 1949 AN APPROXIMATE METHOD FORESTIMATING THEINCOMPRESSIBLE LAMINAR RML9C02 BOUNDARY-LAYER CHARACTERISTICS ONA FLATPLATEIN SLIPPINGFLOW_ ColemanduP. Donaldson_June 1949 RML9C29 PRELIMINARY FULL-SCALE INVESTIGATION OFA 1/3 - SCALE MODEL OF A CONVERTIBLE-TYPE AIRPLANE_ Roy H° Lange_ Bennie W. Cocke_ Jr._ and Anthony J. Proterra_ June 1949 RML9E27 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF A SYMMETRICAL AIR- FOIL SECTION WITHA SEALED INTERNALLY BALANCED CONTROL SURFACE ANDA LEADING TAB_Robert J. Nuber and Felicien F. Fullmer_ Jr._ July 1949 RML9K25 EXPERIMENTAL INVESTIGATION OF VARIOUS EXTERNAL-STORE CONFIGURA- TIONSONA MODEL OF A TAILLESS AIRPLANE WITHA SWEPTBACK WING_ H. NormanSilvers and Kenneth P. Spreemann_ January 1950 RML9L30 LANGLEY 9-1NCHSUPERSONIC TUNNEL TESTS OF SEVERAL MODIFICATIONS OFA SUPERSONIC MISSILE HAVING TAND_ CRUCIFORM LIFTING SURFACES.

THREE-COMPONENT DATARESULTS OFMODELS HAVING RATIOS OF WINGSPAN TO TAlL SPAN EQUAL TO I_ Robert W. Rainey_ March 1951 RML50Bl4a A PRESSURE-DISTRIBUTION INVESTIGATION OF A SUPERSONIC-AIRCRAFT FUSELAGE ANDCALIBRATION OF THEMACH NUMBER 1.40 NOZZLE OF THE LANGLEY 4- BY 4-FOOTSUPERSONIC TUNNEL_ Lowell E. Hasel and Archibald R. Sinclair_ April 1950 RML50G07 LANGLEY 9-1NCHSUPERSONIC TUNNEL TESTS OF SEVERAL MODIFICATIONS OF A SUPERSONIC MISSILE HAVING TANDEM CRUCIFORM LIFTING SURFACES.

THREE-COMPONENT DATARESULTS OFMODELS HAVING RATIOS OF WING SPAN TO TAlL SPAN EQUAL TOANDLESSTHAN i ANDSOME STATICROLLING- MOMENT DATA_ Robert W. Rainey_March 1951 RML50H29a PRELIMINARY RESULTS OF THEFLIGHTINVESTIGATION BETWEEN MACH NUMBERS OF 0.80 AND1.36 OFA ROCKET-POWERED MODEL OF A SUPERSONIC AIRPLANE CONFIGURATION HAVING A TAPERED WING WITHCIRCULAR-ARC SECTIONS AND40° SWEEPBACK_ Charles T. D'Aiutolo and HomerP.

Masonj October 1950 RML50129a LANGLEY 9-1NCHSUPERSONIC TUNNEL TESTOF SEVERAL MODIFICATIONS OF SUPERSONIC MISSILE HAVING TANDEM CRUCIFORM LIFTING SURFACES: THREE-COMPONENT DATA RESULTS OFMODELS HAVING RATIOS OF WINGSPAN TO TAlL SPAN LESSTHANI_ Robert W. Rainey_ March 1951 RML51104a AN INVESTIGATION AT TRANSONIC SPEEDS OFTHEEFFECTS OF THICKNESS RATIOANDOFTHICKENED ROOT SECTIONS ONTHEAERODYNAMIC CHARAC- TERISTICS OFWINGS WITH47° SWEEPBACK_ ASPECT RATIO3.5_ AND TAPER RATIO0.2 IN THESLOTTED TESTSECTION OFTHELANGLEY 8-FOOTHIGH-SPEED TUNNEL_ Ralph P. Bielat_ Daniel E. Harrison_ and DomenicA. Coppolino_ October 1951 RML5i J09 AN INVESTIGATION OF THEAERODYNAMIC CHARACTERISTICS OF A SERIES OF CONE-CYLINDER CONFIGURATIONS AT A MACH NUMBER OF 6.86_ Ralph D. Cooper and Raymond A. Robinson_ December1951 RML5IL20 PRESSURE MEASUREMENTS ONAN OGIVE-CYLINDER BODY AT MACH NUMBER 4.04_ Douglas R. Lord and EdwardF. Ulmann_February 1952 RML52BI8a BIBLIOGRAPHY OFNACA PAPERS ONROTATING-WING AIRCRAFT_ Alfred Gessow_ January 1952 RML52EO2a AN INVESTIGATION OF A SUPERSONIC AIRCRAFT CONFIGURATION HAVING A TAPERED WING WITHCIRCULAR-ARC SECTIONS AND40° SWEEPBACK.

PRESSURE-DISTRIBUTION MEASUREMENTS OFTHEINTERFERENCE EFFECT OF THEWING ONTHEFUSELAGE AT MACH NUMBERS OF 1.40 AND1.59_ John P. Gapcynski and JamesW. Clark_ July 1952 RML52E20a INVESTIGATION OF SUPERSONIC AIRCRAFT CONFIGURATION HAVING TAPERED WING WITHCIRCULAR-ARC SECTIONS AND40° SWEEPBACK_ PRESSURE- DISTRIBUTION MEASUREMENTS OF INTERFERENCE EFFECT OFWINGON FUSELAGE AT MACH NUMBERS OF 1.40 AND1.59_ John P. Gapcynski and JamesW. Clark_ September 1959 RML52G01 INVESTIGATION OF SEVERAL SUPERSONIC MISSILE CONFIGURATIONS DIRECTED TOWARD MINIMIZINGCENTER-OF-PRESSURE TRAVEL [with list of references]_ Robert W. Rainey_ September 1952 RML52H08 A STUDY OF THEZERO-LIFTDRAG-RISE CHARACTERISTICS OF WING-BODY COMBINATIONS NEAR THESPEED OF SOUND_ Richard T. Whitcomb_ September 1952 RML52JI5 THEEFFECTIVE DOWNWASH CHARACTERISTICS AT TRANSONIC SPEEDS OFA 6-PERCENT-THICK WING WITH47° OF SWEEPBACK IN COMBINATION WITHA CYLINDRICAL BODY AS DETERMINED FROM FORCE MEASUREMENTS OF A HORIZONTAL TAIL_ DomenicA. Coppolino_ November1952 RML52JI7 INVESTIGATION AT MACH NUMBERS OF 1.41 AND2.01 OFAERODYNAMIC CHARACTERISTICS OF SWEPT-WING SUPERSONIC BOMBER CONFIGURATION_ NormanF. Smith and Lowell E. Hasel_ February 1956 RML52KO5a EFFECT OF LONGITUDINAL WING POSITION ONTHEPRESSURE CHARACTERIS- TICS AT TRANSONIC SPEEDS OF A 45° SWEPTBACK WING-FUSELAGE MODEL_ William Solomonand JamesW. Sehmeer_ March 1953 WIND-TUNNEL INVESTIGATION TO DETERMINE THEAERODYNAMIC CHARACTER- RML52K24 ISTICS IN STEADY ROLLOF A MODEL AT HIGHSUBSONIC SPEEDS_ Richard E. Kuhn and JamesW. Wiggins_ January 1953 RML52L29b EXPERIMENTAL STUDY OF RELATION BETWEEN AIRPLANE ANDWIND-VANE MEASUREMENTS OFATMOSPHERIC TURBULENCE_ H. B. Tolefson_ K. G.

Pratt_ and J. K. Thompson_ July 1953 RML53AI6a NOTEONDRAG DUETOLIFT OFDELTA WINGS AT MACH NUMBERS UP TO 2.0_ Robert S. Osborne and ThomasC. Kelly_ April 1953 RML53A27 LOW-LIFTDRAG ANDSTABILITYDATA FROM ROCKET MODELS OF A MODIFIED-DELTA-WING AIRPLANE WITHANDWITHOUT EXTERNAL STORES AT MACH NUMBERS FROM 0.8 TO 1.36_ Grady L. Mitcham and Willard S. Blanchard_ Jr._ March 1953 AERODYNAMIC CHARACTERISTICS AT MACH NUMBER 4.04 OFA RECTANGULAR RML53D03 WINGOFASPECT RATIO1.33 HAVING A 6-PERCENT-THICK CIRCULAR-ARC PROFILE ANDA 30-PERCENT-CHORD FULL-SPAN TRAILING-EDGE FLAP_ Robert W. Dunning and EdwardF. Ulmann_May 1953 RML53DI3 EFFECTS OF TRAILING-EDGE BLUNTNESS ONTHELIFT_ DRAG_ AND PITCHING-MOMENT CHARACTERISTICS OFUNSWEPT_ 45° SWEPTj AND45o DELTA WINGS AT MACH NUMBERS OF 1.41_ 1.62_ AND1.96_ Kennith L.

Goin and Gertrude C. Westrick_ June 1953 RML53D30a AERODYNAMIC CHARACTERISTICS OF TWO DELTA WINGS ANDTWO TRAPEZOIDAL WINGS AT MACH NUMBER 4.04_ Robert W. Dunning and Fred M. Smith_ June 1953 RiM L53E22 FLIGHTINVESTIGATION OF AERODYNAMIC DERIVATIVES ANDPERFORMANCE OF CONTROL SYSTEMS OF 2 FULL-SCALE GUIDED BOMBS_ Ernest C.

Seaberg and Edward S. Geller_ June 1954 RML53F04 A BRIEFHYDRODYNAMIC INVESTIGATION OFA NAVYSEAPLANE DESIGN EQUIPPED WITHA HYDRO-SKI_ Lloyd J. Fisher and Edward L. Hoffman_ September 1953 RML53F22a A TRANSONIC WIND-TUNNEL INVESTIGATION OF THEEFFECTS OFNACELLES ONTHEAERODYNAMIC CHARACTERISTICS OF A COMPLETE MODEL CONFIGURA- TION_Melvin M. Carmel and ThomasL. Fischetti_ September 1953 RML53GO 3 PRELIMINARY INVESTIGATION OFTHEEFFECTS OF BODY CONTOURING AS SPECIFIED BY THETRANSONIC AREA RULEONTHEAERODYNAMIC CHARAC- TERISTICS OF A DELTA WING-BODY COMBINATION AT MACH NUMBERS OF 1.41 AND2.01_ Harry W. Carlson_ September 1953 RML53GISa THEVARIATION OFATMOSPHERIC TURBULENCE WITHALTITUDE ANDITS EFFECT ONAIRPLANE GUST LOADS_ Robert L. McDougal_ThomasL.

Coleman_and Philip L. Smith_ November1953 RML53G20a CHARTS FORESTIMATION OFPROFILE DRAG-LIFT RATIOOF HELICOPTER ROTOR HAVING RECTANGULAR BLADES WITH-8° TWIST_F. B. Gustafson_ October 1953 EXPLORATORY INVESTIGATION OF TRANSPIRATION COOLING TOALLEVIATE RML53H06 AERODYNAMIC HEATING ONAN 8° CONE IN A FREEJET AT A MACH NUMBER OF 2°05_ William J. O'Sullivan_ Leo T. Chauvi_ and Charles B.

Rumsey_ September 1953 DEVELOPMENT OFA SUPERSONIC AREA RULEANDAN APPLICATION TO THE RML53H31a DESIGN OF A WING-BODY COMBINATION HAVING HIGHLIFT-TO-DRAGRATIOS_ Richard T. Whitcomband ThomasL. Fischetti_ October 1953 RML53103 COMPONENT TESTS TO DETERMINE THEAERODYNAMIC CHARACTERISTICS OFAN ALL-MOVABLE 70° DELTA CANARD-TYPE CONTROL IN THEPRESENCE OFA BODY AT A MACH NUMBER OF I. 61, M. Leroy Spearman_ October 1953 RML53114 AERODYNAMIC CHARACTERISTICS IN PITCHOF A SERIESOF CRUCIFORM- WING MISSILESWITHCANARD CONTROLS AT A MACH NUMBER OF 2.01_ M. Leroy Spearman_ October 1953 RML53118a FACTORS AFFECTING TRANSITION AT SUPERSONIC SPEEDS_ K. R.

Czarnecki and Archibald R. Sinclair_ October 1953 RML53124a DATA ONSPOILER-TYPE AILERONS_ John G. Lowry, October 1953 RML53J02 SUMMARY OF ROCKET-MODEL TESTS AT ZERO LIFT OF AN ARROW-WING MISSILE CONFIGURATION FROM MACH NUMBERS OF 0.9 TO 1.8_ Richard G. Arbic and Warren Gillespie_ Jr._ January 1954 RML53J08 THEAERODYNAMIC CHARACTERISTICS AT TRANSONIC SPEEDS OF A MODEL WITHA 45° SWEPT-BACK WING_INCLUDING THEEFFECT OF LEADING- EDGE SLATS ANDA LOW HORIZONTAL TALL, Jack F. Runckel and James W. Schmeer_April 1954 RML53J26a SOME MEASUREMENTS AT SUBSONIC SPEEDS OF THEAERODYNAMIC FORCES ANDMOMENTS ONTWO DELTA WINGS OFASPECT RATIOS 2 AND4 OSCILLAT- ING ABOUT THEMIDCHORD_ SumnerA. Leadbetter and ShermanA.

Clevenson_ December1953 RML53L29 A WIND-TUNNEL INVESTIGATION OF BOMB RELEASE AT A MACH NUMBER OF 1.62, Robert W. Rainey_ March 1954 RML54A07 FLIGHT-DETERMINED PRESSURE MEASUREMENTS OVER THEWING OF THE DOUGLAS D-558-II RESEARCH AIRPLANE AT MACH NUMBERS UP TO 1.14_ JamesR. Peele_ March 1954 RML54BI5 A TRANSONIC WIND-TUNNEL INVESTIGATION OF THEEFFECTS OF TWISTAND CAMBER WITHANDWITHOUT INCIDENCE_ TWIST_ ANDBODY INDENTATION ON THEAERODYNAMIC CHARACTERISTICS OF A 45° SWEPTBACK WING-BODY CON- FIGURATION_ J. Lawrence Cooper_April 1954 THEAERODYNAMIC CHARACTERISTICS OF TWO SERIES OF LIFTING BODIES RML54C15 AT MACH NUMBER 6.86_ Herbert W. Ridyard_ May 1954 RML54D09a EFFECTS OFFENCES_ LEADING-EDGE CHORD-EXTENSIONS_ BOUNDARY-LAYER RAMPS 3 ANDTRAILING-EDGE FLAPSONLONGITUDINAL STABILITYOF TWISTED ANDCAMBERED 60° SWEPTBACK-WING-INDENTED-BODY CONFIGURA- TION AT TRANSONIC SPEEDS_ ThomasL. Fischetti_ June 1954 RML54DI9 AERODYNAMIC CHARACTERISTICS OF SEVERAL FLAP-TYPE TRAILING-EDGE CONTROLS ONA TRAPEZOIDAL WING AT MACH NUMBERS OF 1.61 AND2.01_ Douglas R. Lord and K. Ro Czarnecki_ June 1954 RML54D30a NORMAL FORCE_ CENTER OF PRESSURE_ ANDZERO-LIFT DRAG OF SEVERAL BALLISTIC-TYPE MISSILESAT MACH NUMBER 4.05_ EdwardF. Ulmann and Robert W. Dunning_ July 1954 RML54E20 INVESTIGATION OF A CANARD MISSILE CONFIGURATION (NASA RM-4) IN THELANGLEY 9-1NCHSUPERSONIC TUNNEL AT MACH NUMBERS OF 1.62 AND 1.93_ Carl E. Grigsby_ June 1954 RML54E26 EFFECT ONDRAG OF LONGITUDINAL POSITIONING OF HALF-SU_ERGED AND PYLON-MOUNTED DOUGLAS AIRCRAFT STORES ON. A FUSELAGE WITHAND WITHOUT CAVITIESBETWEEN MACH NUMBERS 0.9 AND1.8_ Sherwood Hoffman and Austin L. Wolff_ July 1954 RML54F04 THEORETICAL INVESTIGATION BASED ONEXPERIMENTAL FREQUENCY- RESPONSE MEASUREMENTS OF AN AUTOMATIC ALTITUDE CONTROL IN COMBINA- TIONWITHA SUPERSONIC MISSILE CONFIGURATION_ Ernest C. Seaberg_ Edward S. Geller_ and William W. Willoughby_ August 1954 RML54FI6 AN ASSESSMENT OF THEAIRPLANE DRAG PROBLEM AT TRANSONIC AND SUPERSONIC SPEEDS_ Charles J. Donlan_ July 1954 RML54G23b THEEFFECTS OF WINGINCIDENCE ONTHEAERODYNAMIC LOADING CHARAC- TERISTICS OFA SWEPTBACK WING-BODY COMBINATION AT TRANSONIC SPEEDS_ Harold L. Robinson_ October 1954 RML54HI6a THEEFFECT OF A CHANGE IN AIRFOIL SECTION ONTHEHINGE-MOMENT CHARACTERISTICS OF A HALF-DELTA TIP CONTROL WITHA 60° SWEEP ANGLE AT A MACH NUMBER OF 6.9_ David E. Fetterman and Herbert W.

Ridyard_ October 1954 RML54107a AN EXPERIMENTAL TRANSONIC INVESTIGATION OF A 45° SWEPTBACK- WING-BODY COMBINATION WITHSEVERAL TYPES OF BODY INDENTATION WITH THEORETICAL COMPARISONS INCLUDED_ Melvin M. Carmel_ November1954 RML54120a EFFECTS OF SOME EXTERNAL-STORE MOUNTING ARRANGEMENTS ANDSTORE SHAPES ONTHEBUFFET ANDDRAG CHARACTERISTICS OF WINGLESS ROCKET- POWERED MODELS AT MACH NUMBERS FROM 0.7 TO 1.4_ HomerP. Mason and Allen B. Henning_ December1954 RML54122 EXPERIMENTAL INVESTIGATION OF EFFECTS OFPRIMARY JET FLOW AND SECONDARY FLOW THROUGH A ZERO-LENGTH EJECTOR ONBASE ANDBOATTAIL PRESSURES OF A BODY OFREVOLUTION AT FREE-STREAM MACH NUMBERS OF 1.62_ 1.93_ AND2.41_ Robert M. O'Donnell and Russell W. McDearmon December1954 RML54J29 A PRESSURE-DISTRIBUTION INVESTIGATION OFTHEAERODYNAMIC CHARAC- TERISTICS OF A BODY OF REVOLUTION IN THEVICINITY OFA REFLECTION PLANE AT MACH NUMBERS OF 1.41 AND2.01_ John P. Gapcynski and Harry W. Carlson_ January 1955 RML54K01 EFFECTS OF SOME LEADING-EDGE MODIFICATIONS_ SECTION ANDPLAN- FORM VARIATIONS_ ANDVERTICAL POSITION ONLOW-LIFT WING DRAG AT TRANSONIC ANDSUPERSONIC SPEEDS_ Clement J. Welsh_ Harvey A.

Wallskog_ and Carl A. Sandahl_ January 1955 RML54KI6a EFFECTS OF AN INSETTABONTHEHINGE-MOMENT ANDEFFECTIVENESS CHARACTERISTICS OFAN UNSWEPT TRAILING-EDGE CONTROL ONA 60° DELTA WING AT MACH NUMBERS FROM 0.75 TO 1.96_ Lawrence D. Guy and Hoyt V. Brown_February 1955 RML54KI9a TRANSONIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OFFIGHTER- TYPEAIRPLANE MODEL WITHLOW-ASPECT-RATIO UNSWEPT WING ANDTEE- TAIL_ Gerald Hieser_ and Charles F. Reid_ Jr._ October 1956 RML54L03b LIFT_ DRAG_ ANDSTATICLONGITUDINAL STABILITYDATAFROM AN EXPLORATORY INVESTIGATION AT A MACH NUMBER OF 6.86 OFAN AIRPLANE CONFIGURATION HAVING A WING OF TRAPEZOIDAL PLANFORM_ Jim A.

Penland_ Herbert W. Ridyard_ and David E. Fetterman_ Jr._ January RML54L06 INVESTIGATION OFAERODYNAMIC CHARACTERISTICS IN PITCHANDSIDESLIP OF A 45° SWEPTBACK-WING AIRPLANE MODEL WITHVARIOUS VERTICAL LOCATIONS OFWING ANDHORIZONTAL TALL. BASIC-DATA PRESENTATION_ M = 2.01_ M. Leroy Spearman_ Cornelius Driver_ and William C.

Hughes_January 1955 RML54L06a APPLICATION OFNONLINEAR AERODYNAMIC STABILITYCHARACTERISTICS TO SIMPLIFY MISSILE CONTROL ANDGUIDANCE SYSTEMS_ HowardJ. Curfman_ Jr._ February 1955 RML54L29a PERFORMANCE MEASUREMENTS FROM A ROCKET-POWERED EXPLORATORY RE- SEARCH MISSILE FLOWN TO A MACH NUMBER OF i0.4_ Robert O. Piland_ March 1955 RML54L31a AN EXPERIMENTAL STUDY OF A METHOD OF DESIGNING THESWEPTBACK- WING--FUSELAGE JUNCTURE FORREDUCING THEDRAG AT TRANSONIC SPEEDS_ Robert R. Howell and Albert L° Braslow_ March 1955 AN AERODYNAMIC ANDHYDRODYNAMIC INVESTIGATION OF TWO MULTIJET RML55AIIa WATER-BASED AIRCRAFT HAVING LOW TRANSONIC DRAG RISE_Roland E.

Olson and Ralph P. Bielat_ February 1955 EXPERIMENTAL STATICAERODYNAMIC FORCES ANDMOMENTS AT LOWSPEED RML55AI2 ONA CANARD MISSILEDURING SIMULATED LAUNCHING FROM THEMID- SEMISPAN ANDWING-TIPLOCATIONS OF A 45° SWEPTBACK WING-FUSELAGE COMBINATION_ William J. Alford_ Jr._ April 1955 ORIGINANDDISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM RML55AI3a MEASURI_IENT OF INDIVIDUAL FORCES ONSEVERAL WING-FUSELAGE-STORE CONFIGURATIONS: i_ SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE (NACELLE)_ LIFT ANDDRAG_ MACH NUMBER_ 1.61 [with list of references]_ NormanF. Smith and Harry W. Carlson_ March AERODYNAMIC-HEATING DATA OBTAINED FROM FREE-FLIGHT TESTSBETWEEN RML55AI4a MACH NUMBERS OF 1 AND5_ Charles B. Rumsey_ Robert O. Piland_ and Russell N. Hopko_March 1955 AERODYNAMIC CHARACTERISTICS OFA 60° DELTA WING HAVING A HALF- RML55AI9 DELTA TIP CONTROL AT A MACH NUMBER OF4.04_ EdwardF. Ulmannand Fred M. Smith_ April 1955 PRELIMINARY RESULTS OFAN INVESTIGATION AT TRANSONIC SPEEDS TO RML55A24a DETERMINE THEEFFECTS OF A HEATED PROPULSIVE JET ONTHEDRAG CHARACTERISTICS OF A RELATED SERIES OF AFTERBODIES_ Beverly Z.

Henry_ Jr._ and Maurice S. Cahn_March 1955 EFFECT OF SURFACE ROUGHNESS ONCHARACTERISTICS OF SPHERICAL SHOCK RML55B04 WAVES_ Paul W. Huber and Donald R. McFarland_ May 1955 DEVELOPMENT OF 8-1NCHSLOTTED TUNNEL FORMACH NUMBERS UP TO 1.28_ RML55B08 B. H. Little_ Jr._ and JamesM. Cubbage_Jr._ May 1955 AN INVESTIGATION OF THEAERODYNAMIC CHARACTERISTICS OF THIN DELTA RML55BI4 WINGS WITHA SYMMETRICAL DOUBLE-WEDGE SECTION AT A MACH NUMBER OF 6.9_ Mitchel H. Bertram and William D. McCauley_April 1955 INVESTIGATION OF THEAERODYNAMIC CHARACTERISTICS IN PITCHAND RML55BI8 SIDESLIPOF A 45° SWEPTBACK-WING AIRPLANE MODEL WITHVARIOUS VERTICAL LOCATIONS OF THEWING ANDHORIZONTAL TALL. EFFECT OF WINGLOCATION ANDGEOMETRICAL DIHEDRAL FORTHEWING-BODY COMBINA- TION_M = 2.01_ M. Leroy Spearman_April 1955 FLIGHTINVESTIGATION OF THESUPERSONIC AREA RULE FORA STRAIGHT RML55C09 WING-BODY CONFIGURATION AT MACH NUMBERS BETWEEN 0.8 AND1.5_ SherwoodHoffman_Austin L. Wolff_ and MaximeA. Faget_ APPENDIX: A SHORT METHOD OF DETERMINING THEAVERAGE AREA DISTRIBUTION FOR AIRCRAFT AT SUPERSONIC SPEEDS_ MaximeA. Faget_ April 1955 RML55DI3 EXPERIMENTAL INVESTIGATION OF THEZERO-LIFT WAVE DRAG OF SEVEN PAIRSOF DELTA WINGS WITHCONSTANT ANDVARYING THICKNESS RATIOS AT MACH NUMBERS OF 1.62_ 1.93_ AND2.41_ Arthur Henderson_Jr._ June 1955 RML55D20 EXPERIMENTAL STATICAERODYNAMIC FORCES AND MOMENTS AT LOWSPEED ONA MISSILEMODEL DURING SIMULATED LAUNCHING FROM THE25-PERCENT- SEMISPAN ANDWING-TIPLOCATIONS OF A 45° SWEPTBACK WING-FUSELAGE COMBINATION_ William J. Alford_ Jr._ H. NormanSilvers_ and Thomas J. King_ Jr._ May 1955 RML55D26 AN INVESTIGATION AT SUPERSONIC SPEEDS OFTHEEFFECT OF VARYING THEMAXIMUM-THICKNESS POSITION UPON THEAERODYNAMIC CHARACTERIS- TICS OFA SERIES OF 3½-PERCENT-THICK DELTA WINGS_ JamesN. Mueller_ August 1955 RML55D28 INVESTIGATION AT SUPERSONIC SPEEDS OF EXTERNAL-DRAG EFFECTS AND PUMPING CHARACTERISTICS OF A SHORT EJECTOR_ EugeneS. Love and Robert M° O'Donnell_ June 1955 RML55E04 AN INVESTIGATION AT HIGHSUBSONIC SPEEDS OF THEEFFECTS OF HORIZONTAL-TAlL HEIGHT ONTHEAERODYNAMIC ANDLOADING CHARACTER- ISTICS IN SIDESLIPONA 45° SWEPTBACK_ UNTAPERED TAlL ASSEMBLY AS DETERMINED FROM FORCE TESTS ANDINTEGRATED VERTICAL-TAlL SPAN LOADINGS_ Harleth G. Wiley and William C. Moseley_ Jr._ June 1955 RML55EI0c AERODYNAMIC HEATING OFROCKET-POWERED RESEARCH VEHICLES AT HYPER- SONIC SPEEDS_ Robert O. Piland and Katherine A. Collie_ July 1955 RML55E24 DRAG INVESTIGATION OF A SWEPT-WING FIGHTER-AIRPLANE MODEL INCOR- PORATING TWO DRAG-RISE-REDUCING FUSELAGE REVISIONS_ Charles F.

Whitcomband Edwin E. Lee_ Jr._ July 1955 RML55E26a ORIGINANDDISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUALFORCES ONSEVERAL WING-FUSELAGE-STORE CONFIGURATIONS_ 2_ SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE (NACELLE)_ LATERAL FORCES ANDPITCHING MOMENTS_ MACH NUMBER_ 1.61_ NormanF. Smith and Harry W. Carlson_ July 1955 RML55E27 INVESTIGATION OF EFFECTS OF BOMB-BAY CONFIGURATION UPON AERO- DYNAMIC CHARACTERISTICS OF BODY WITHCIRCULAR CROSS SECTION AT SUPERSONIC SPEEDS_ Robert W. Rainey_ August 1955 RML55F06a INVESTIGATION AT TRANSONIC SPEEDS OF THEHINGE-MOMENT CHARACTERIS- TICS OF A I/8-SCALEMODEL OF THEX-IE AILERON_ William C° Moseley_ Jr._ August 1955 RML55FO8a INVESTIGATION OF EQUILIBRIUM TEMPERATURES ANDAVERAGE LAMINAR HEAT- TRANSFER COEFFICIENTS FORTHEFRONT HALFOF SWEPT CIRCULAR CYLINDERS AT A MACH NUMBER OF 6.9_ William V. Feller_ August 1955 THEORETICAL INVESTIGATION OF LAMINAR HEATTRANSFER ONYAWED RML55F09 INFINITE CYLINDERS IN SUPERSONIC FLOW ANDA COMPARISON WITH EXPERIMENTAL DATA_ Ivan E. Beckwith_ August 1955 LONGITUDINAL AERODYNAMIC CHARACTERISTICS AT TRANSONIC SPEEDS OF RML55F30 A COMPLETE MODEL WITHAN UNSWEPT WING ANDA SWEPTBACK HORIZONTAL TAIL AT TWO VERTICAL LOCATIONS_ Gerald Hieser and Louis Kudlacik_ September1955 A FREE-FLIGHT INVESTIGATION AT HIGHSUBSONIC ANDLOWSUPERSONIC RML55GIIa SPEEDS OF THEROLLING EFFECTIVENESS ANDDRAG OF THREE SPOILER CONTROLS HAVING POTENTIALLY LOW ACTUATING-FORCE REQUIR_ENTS_ EugeneD. Schult_ September 1955 RML55G21 NOTE ONHOVERING TURNS WITHTANDEN HELICOPTERS_ P. Reeder and Robert J. Tapscott_ September 1955 FREE-FLIGHT MEASUREMENTS OF AERODYNAMIC HEAT TRANSFER TOMACH RML55G28a NUMBER 3.9 ANDOF DRAG TOMACH NUMBER 6.9 OFA FIN-STABILIZED CONE-CYLINDER CONFIGURATION_ Charles B. Rumsey_ October 1955 SUMMARY OF LOCATIONS ANDEXTENTS OF TURBULENT AREAS ENCOUNTERED RML55HO4a DURING FLIGHTINVESTIGATIONS OF JET STREAM_ October 1953-May 1954 ANDNovember1954-July 1955 [with list of references]_ Mary W. Fetner 3 November1956 AN INVESTIGATION OF THEADAPTATION OF A TRANSONIC SLOTTED TUNNEL RML55HI5 TO SUPERSONIC OPERATION BY ENCLOSING THESLOTS WITHFAIRINGS_ Clarence W. Matthews_ October 1955 WIND-TUNNEL INVESTIGATION AT TRANSONIC SPEEDS OF A JET CONTROL RML55H22 ONAN 80° DELTA-WING MISSILE_ThomasR. Turner and RaymondD.

Vogler_ November1955 FORCE ANDPRESSURE MEASUREMENTS ONSEVERAL CANOPY-FUSELAGE CON- RML55H23 FIGURATIONS AT MACH NUMBERS 1.41 AND2.01_ A. Warner Robins_ December1955 RML55H29 EXPERIMENTAL INVESTIGATION OF FLOW PHENOMENA OVER BODIES AT HIGH ANGLES OFATTACK AT MACH NUMBER OF 2.01_ John P. Gapsynski_ October 1955 RML55H30 TRANSONIC INVESTIGATION OFAERODYNAMIC CHARACTERISTICS OF A SWEPT- WING FIGHTER-AIRPLANE MODEL WITHLEADING-EDGE DROOP IN COMBINATION WITHOUTBOARD CHORD-EXTENSIONS ANDNOTCHES_ Charles F. Whitcomb and Harry T. Norton_ Jr._ March 1956 RML55I06 COMPARATIVE DISPERSION DATA FROM GROUND-LAUNCHED 2.25-1NCHROCKETS EQUIPPED WITHCRUCIFORM ANDMONOPLANE FINS_ Paul E. Purser_ November1955 RML55112 LIFT_ DRAG_ ANDLONGITUDINAL STABILITYAT MACH NUMBERS FROM 1.4 TO 2.3 OF A ROCKET-POWERED MODEL HAVING A 52.5° SWEPTBACK WING OFASPECT RATIO3 ANDINLINE TAlL SURFACES_ Warren Gillespie_ Jr._ December1955 RML55113 FLIGHTINVESTIGATION OF EFFECT OF UNDERWING PROPULSIVE JETSON LIFT_ DRAG_ ANDLONGITUDINAL STABILITYOF DELTA-WING CONFIGURA- TION AT MACH NUMBERS FROM 1.23 TO 1.62_ Ralph A. Falanga and Joseph H. Judd_ December1955 RML55114 INVESTIGATION OF INTERFERENCE LIFT_ DRAG_ ANDPITCHING MOMENT OF A SERIES OF TRIANGULAR-WING ANDBODY COMBINATIONS AT A MACH NUMBER OF 1.94_ Donald E. Coletti_ December1955 RML55127a ORIGINANDDISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUALFORCES ONSEVERAL WING-FUSELAGE-STORE CONFIGURATIONS_ 4_ DELTA-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE_ MACH bFUMBER_ 1.61 [with list of references]_ Odell A. Morris_ December1955 RML55129 LOW-SPEED PRESSURE-DISTRIBUTION INVESTIGATION OFA SPOILER ANDA SPOILER-SLOT-DEFLECTOR ONA 30° SWEPTBACK WING-FUSELAGE MODEL HAVING ANASPECT RATIOOF 3_ A TAPER RATIOOF0.5_ ANDNACA 65A004AIRFOIL SECTION_ Alexander D. Hammond_ January 1956 RML55J04 TABULATED PRESSURE DATAFORSEVERAL FLAP-TYPE TRAILING-EDGE CONTROLS ONA TRAPEZOIDAL WING AT MACH NUMBERS OF 1.61 AND2.01_ Douglas R. Lord and K. R° Czarnecki_ ]February 1956 RML55J07 A TRANSONIC INVESTIGATION OF CHANGING INDENTATION DESIGN MACH NUMBER ONTHEAERODYNAMIC CHARACTERISTICS OF A 45° SWEPTBACK-WING --BODYCOMBINATION DESIGNED FORHIGHPERFORMANCE_ Donald L.

Loving_ January 1956 I RML55JI9 LIMITEDHYDRODYNAMIC INVESTIGATION OF A I-_-SIZE MODEL OF A MODIFIED NOSE-INLET MULTIJET WATER-BASED AIRCRAFT_ Robert E.

McKannand Claude W. Coffee_ February 1956 RML55J24 SIMULATED FLIGHTINVESTIGATION OF SCALED-SPEED ELASTICSWEPT-WING BOMBER ANDFIGHTER MODELS COUPLED WING TIP TO WING TIP_ Robert E.

Thompson_ February 1956 RML55KI5 ORIGINANDDISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ONSEVERAL WING-FUSELAGE-STORE CONFIGURATIONS: 5_ SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE (NACELLE)_ MACH NUMBER 2.01_ H. W. Carlson and D. J.

Geier_ February 1956 RML55K23 THEEFFECTS AT A MACH NUMBER OF 6.86 OF DRAG BRAKES ONTHELIFT_ DRAG_ ANDPITCHING MOMENT OF AN OGIVECYLINDER_ Jim A. Penland and David E. Fetterman_ Jr._ March 1956 RML55L06 INVESTIGATION OFAERODYNAMIC CHARACTERISTICS IN PITCHANDSIDESLIP OF A 45° SWEPTBACK-WING AIRPLANE MODEL WITHVARIOUS VERTICAL LOCATIONS OFWING ANDHORIZONTAL TALL. STATICLONGITUDINAL STABILITYANDCONTROL_ M = 2.01_ M. Leroy Spearma_and Cornelius Driver_ February 1956 RML55L08 ORIGINANDDISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ONSEVERAL WING-FUSELAGE-STORE CONFIGURATIONS: 6_ SWEPT-WING HEAVY BOMBER CONFIGURATION WITH STORES OF DIFFERENT SIZESANDSHAPES_ NormanF. Smith_ February RML55L20a FACTORS AFFECTING MAXIMUM LIFT-DRAG RATIOAT HIGHSUPERSONIC SPEEDS_ Charles H. McLellan and Robert W. Dunning_ February 1956 RML55L23 DRAG OF CANOPIES AT TRANSONIC ANDSUPERSONIC SPEEDS_ Sherwood Hoffman and A. Warner Robins_ February 1956 RML56A03 INVESTIGATION OF THEEFFECTS OF BODY CAMBER ANDBODY INDENTATION ONTHELONGITUDINAL CHARACTERISTICS OF A 60° DELTA-WING-BODY COMBINATION AT A MACH NUMBER OF 1.61_ John R. Sevier_ Jr._ April RML56A09 THEEFFECTS UPON BODY DRAG OF JETSEXHAUSTING FROM WING-MOUNTED NACELLES_ Robert W. Rainey_ April 1956 RML56AI6 FLIGHTINVESTIGATION OF THEEFFECT OF A PROPULSIVE JET POSITIONED ACCORDING TO THETRANSONIC AREARULE ONTHEDRAG COEFFICIENTS OF A SINGLE-ENGINE DELTA-WING CONFIGURATION AT MACH NUMBERS FROM 0.83 TO 1.36_ Joseph H. Judd and Ralph A. Falanga_ April 1956 RML56A25 TWO EXPERIMENTS ONAPPLICATIONS OF THETRANSONIC AREA RULETO ASYMMETRIC CONFIGURATIONS_ JamesRudyard Hall_ April 1956 RML56B07 MEASUREMENTS OF AERODYNAMIC HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONA I0° CONE IN FREEFLIGHTAT SUPERSONIC MACH NUMBERS UP TO5.9_ Charles B. Rumseyand Dorothy B. Lee_ April 1956 RML56B09 A BRIEFINVESTIGATION OF THEEFFECT OF WAVES ONTHETAKE-OFF RESISTANCE OF A SEAPLANE_ Elmo J. Mottard_ April 1956 RML56B24 AERODYNAMIC CHARACTERISTICS OF A 6-PERCENT-THICK SYMMETRICAL CIRCULAR-ARC AIRFOIL HAVING A 30-PERCENT-CHORD TRAILING-EDGE FLAPAT MACH NUMBER OF 6.9_ Herbert W. Ridyard and David E.

Fetteman_ Jr._ June 1956 RML56B27 SUPERSONIC-AREA-RULE DESIGN ANDROCKET-PROPELLED FLIGHTINVESTI- GATION OF A ZERO-LIFTSTRAIGHT-WING--BODY--NACELLE CONFIGURATION BETWEEN MACH NUMBERS 0.8 AND1.53_ SherwoodHoffman_April 1956 TURBULENT ANDLAMINAR HEAT-TRANSFER MEASUREMENTS ONA I/6-SCALE RML56C05 NACA RM-IOMISSILEIN FREEFLIGHTTOA MACH NUMBER OF4.2 ANDTO A WALL TEMPERATURE OF 1400 ° R_ Robert O. Piland_ Katherine A.

Collie_ and William E. Stoney_ APPENDIX A: ESTIMATED ERRORS_ William E. Stoney_ July 1956 FREE-FLIGHT MEASUREMENTS OF THEZERO-LIFT DRAG OF SEVERAL WINGS RML56C13 AT MACH NUMBERS FROM 1.4 TO 3.8_ H. Herbert Jackson_ June 1956 EFFECT OFLEADING-EDGE DROOP ONTHEAERODYNAMIC ANDLOADING RML56C14 CHARACTERISTICS OF A 4_PERCENT-THICK UNSWEPT-WING--FUSELAGE COMBINATION AT TRANSONIC SPEEDS_ JamesW. Schmeer_ May 1956 HEATTRANSFER ONTHELIFTING SURFACES OF A 60° DELTA WING AT RML56C23 ANGLE OF ATTACK FORMACH NUMBER 1.98_ HowardS. Carter_ May 1956 AN INVESTIGATION OF THEHYDRODYNAMIC CHARACTERISTICS OFA DYNAMIC RML56C28a MODEL OF A TRANSONIC SEAPLANE DESIGN HAVING A PLANING-TAIL HULL_ Archibald E. Morse_ Jr._ David R. Woodward_ and Ulysse J. Blanchard_ June 1956 SOME EXAMPLES OFTHEAPPLICATIONS OF THETRANSONIC ANDSUPERSONIC RML56DIi AREA RULES TO THEPREDICTION OFWAVE DRAG_ Robert L. Nelson and Clement J. Welsh_March 1957 TRANSONIC INVESTIGATION AT LIFTING CONDITIONS OF STREAMLINE CON- RML56DIIa TOURING IN THESWEPTBACK-WING--FUSELAGE JUNCTURE IN COMBINATION WITHTHETRANSONIC AREA RULE_ William E. Palmer_ Robert R. Howell_ and Albert L. Braslow_ July 1956 ZERO-LIFT DRAG OF SERIES OF BOMB SHAPES AT MACH NUMBERS 0.60 TO RML56DI6 I.I0 [with list of references]_ William E. Stoney_ Jr._ and John F. Royall_ July 1956 FORCE ANDPRESSURE-DISTRIBUTION MEASUREMENTS AT A MACH NUMBER OF RML56DI7 3.12 OF SLENDER BODIES HAVING CIRCULAR_ ELLIPTICAL_ANDTRIANGULAR CROSS SECTIONS ANDTHESAME LONGITUDINAL DISTRIBUTION OF CROSS- SECTIONAL AREA_ Roy H. Lange and Charles E. Wittliff_ July 1956 FREE-FLIGHT AERODYNAMIC-HEATING DATATOMACH NUMBER 10.4 FORA RML56D25 MODIFIED VON KARMAN NOSE SHAPE_ William M. Bland_ Jr._ and Katherine A. Collie_ July 1956 FREE-FLIGHT INVESTIGATION OF EFFECTS OF SIMULATED SONICTURBOJET RML56D30 EXHAUST ONTHEDRAG OFTWIN-JETBOATTAIL BODIES AT TRANSONIC SPEEDS_ AbrahamLeiss_ July 1956 COMPARISON OF THEMINIMUM DRAG OF TWO VERSIONS OFA MODIFIED RML56E04 DELTA-WING FIGHTER AS OBTAINED FROM FLIGHTTESTS OF ROCKET- BOOSTED MODELS ANDEQUIVALENT BODIES BETWEEN MACH NUMBERS OF0.80 AND1.64_ Earl C. Hastings_ Jr. 3 and Grady L. Mitcham_ September RML56E09 EXPERIMENTAL INVESTIGATION OFTHEEFFECT OF BOUNDARY-LAYER TRANSITION ONTHEAVERAGE HEATTRANSFER TO A YAWED CYLINDER IN SUPERSONIC FLOW_ Ivan E. Beckwith and JamesJ. Gallagher_ July 1956 RML56E22 PRESSURE DISTRIBUTIONS ANDAERODYNAMIC CHARACTERISTICS OF SEVERAL SPOILER-TYPE CONTROLS ONTRAPEZOIDAL WING AT MACH NUMBERS OF I. 61 AND2.01_ Douglas R. Lord and K. R. Czarnecki_ July 1956 RML56FIIa AERODYNAMIC HEATING OFA WING AS DETERMINED FROM A FREE-FLIGHT ROCKET-MODEL TESTTO MACH NUMBER 3.64_ Andrew G. Swansonand Charles B. Rumsey_ September 1956 RML56F20 WIND-TUNNEL INVESTIGATION OF THEEFFECT OF ASPECT RATIOAND CHORDWISE LOCATION ONEFFECTIVENESS OF PLAIN SPOILERS ONTHIN UNTAPERED WINGS AT TRANSONIC SPEEDS_ Alexander D. Hammond_ September 1956 RML56F26 MEASUREMENTS OF AERODYNAMIC HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONA 15° CONE IN FREEFLIGHTAT SUPERSONIC MACH NUMBERS UP TO5.2_ Charles B. Rumseyand Dorothy B. Lee_ October 1956 RML56G05 AERODYNAMIC HEATTRANSFER ANDZERO-LIFTDRAG OFFLATWINDSHIELD CANOPY ONNACA RM-10RESEARCH VEHICLE AT HIGHREYNOLDS NUMBERS FOR FLIGHTMACH NUMBER RANGE FROM 1.5 TO 3.0_ SherwoodHoffman and Leo T° Chauvin_ September 1956 RML56GI2 ADDITIONAL RESULTS OF AN INVESTIGATION AT TRANSONIC SPEEDS TO DETERMINE THEEFFECTS OF A HEATED PROPULSIVE JET ONTHEDRAG CHARACTERISTICS OF A SERIESOF RELATED AFTERBODIES_ Beverly Z.

Henry_ Jr._ and Maurice S. Cahn_September 1956 RML56GI2a EFFECTS OF TWO LEADING-EDGE MODIFICATIONS ONTHEAERODYNAMIC CHAR- ACTERISTICS OFA THINLOW-ASPECT-RATIO DELTA WING AT TRANSONIC SPEEDS_ John P. Mugler_ Jr._ October 1956 RML56H01 AERODYNAMIC ANDHYDRODYNAMIC CHARACTERISTICS OF A DECK-INLET MULTIJET WATER-BASED-AIRCRAFT CONFIGURATION DESIGNED FORSUPERSONIC FLIGHT_Ralph P. Bielat_ Claude W. Coffee_ Jr._ and William W.

Petynia_ December1956 RML56H07 AN EXPERIMENTAL STUDY OF THEZERO-ANGLE-OF-ATTACK TRANSONIC DRAG ASSOCIATED WITHTHEVERTICAL POSITION OFA HORIZONTAL TAlL AT ZERO INCIDENCEj Robert R. Howell_ October 1956 RML56H20 INVESTIGATION AT SUPERSONIC SPEEDS OF EFFECTS OF BOMB-BAY CON- FIGURATION UPON AERODYNAMIC CHARACTERISTICS OF FUSELAGES WITH NON-CIRCULAR CROSS SECTIONS_ Robert W. Rainey_ November1956 RM L56H21 EFFECT OF INCREASE IN ANGLE OF DEAD RISE ON THE HYDRODYNAMIC QUALITIES OF A SEAPLANE CONFIGURATION INCORPORATING HIGH WING LOADING_ Walter J. Kapryan and Irving Weinstein_ October 1956 PRESSURE DISTRIBUTIONS OF FOUR CANOPY-FUSELAGE CONFIGURATIONS AT RML56H22 TRANSONIC SPEEDS_ Elden S. Cornette_ December 1956 RM L56H22a WIND-TUNNEL INVESTIGATION OF TWO VERTICAL-TAKE-OFF-AND-LANDING JET BOMBER AIRPLANE CONFIGURATIONS AT MACH NUMBERS OF 1.94 AND 2.40_ Robert A. Jones and Robert W. Rainey_ October 1956 FREE-FLIGHT INVESTIGATION AT TRANSONIC SPEEDS OF DRAG COEFFICIENTS RM L56H23 OF A BOATTAIL BODY OF REVOLUTION WITH A SIMULATED TURBOJET EXHAUST ISSUING AT THE BASE FROM CONICAL SHORT-LENGTH EJECTORS_ Ralph A. Falanga and Abraham Leiss_ December 1956 INVESTIGATION OF EJECTION RELEASE OF SEVERAL DYNAMICALLY SCALED RM L56H28 BLUFF INTERNAL STORES AT MACH NUMBERS 0.8_ 1.39_ AND 1.98_ Howard S. Carter and John B. Lee_ December 1960 A WIND-TUNNEL INVESTIGATION OF THE DEVELOPMENT OF LIFT ON WINGS RM L56H28a IN ACCELERATED LONGITUDINAL MOTION_ Thomas R. Turner_ November FREE-FLIGHT INVESTIGATION AT MACH NUMBERS BETWEEN 0.5 AND 1.7 OF RM L5 6H29 ZERO-LIFT ROLLING EFFECTIVENESS AND DRAG OF VARIOUS SURFACE_ SPOILER_ AND JET CONTROLS ON 80 ° DELTA-WING MISSILE_ Eugene D.

Schult_ November 1956 SOME CONSIDERATIONS OF THE INFLUENCE OF BODY CROSS-SECTIONAL SHAPE RM L56H30 ON THE LIFTING EFFICIENCY OF WING-BODY COMBINATIONS AT SUPERSONIC SPEEDS_ E. B. Klunker and Keith C. Harder_ October 1956 A LOW-SPEED INVESTIGATION OF A HIGH-LIFT LATERAL-CONTROL DEVICE RM L56H31 CONSISTING OF A SPOILER-SLOT-DEFLECTOR AND A TRAILING-EDGE FLAP ON A TAPERED 45 ° SWEPTBACK WING_ Alexander D. Hammond and Jarrett K. Huffman_October 1956 FORCE TEST RESULTS FOR BODY-MOUNTED LATERAL CONTROLS AND SPEED RM L56105 BRAKES ON A 45 ° SWEPT-WING MODEL AT MACH NUMBERS FROM 0.80 TO 0.98_ F. E. West_ Jr._ and Chris C. Critzos_ December 1956 PRESSURE DISTRIBUTION INDUCED ON A FLAT PLATE BY A SUPERSONIC AND RM L56106 SONIC JET EXHAUST AT A FREE-STREAM MACH NUMBER OF 1.80_ Abraham Leiss and Walter E. Bressette_ January 1957 LOW-SPEED PRESSURE-DISTRIBUTION INVESTIGATION OF A THIN-DELTA-WING RM L56111 --FUSELAGE MODEL WITH DOUBLE SLOTTED FLAP_ EXTENDED DOUBLE SLOTTED FLAP_ AND CANARD_ Delwin R. Croom and Jarrett K. Huffman_ November 1956 RM L56113 INVESTIGATION OF STATIC PRESSURES AND BOUNDARY-LAYER CHARACTERIS- TICS ON FORWARD PARTS OF 9 FUSELAGES OF VARIOUS CROSS-SECTIONAL SHAPES AT Moo = 2.0I s Lowell E. Hasel and Walter L. Kouyoumjian s January 1957 RM L57117 AERODYNAMIC CHARACTERISTICS OF MODEL OF ESCAPE CAPSULE FOR SUPER- SONIC BOMBER-TYPE AIRPLANE AT MACH NUMBER OF 2.49 s John G.

Presnell s Jr._ December 1957 RM L56124 WIND-TUNNEL INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF A SERIES OF SWEPT s HIGHLY TAPERED_ THIN WINGS AT TRANSONIC SPEEDS.

TRANSONIC-BUMP METHOD s Albert G. Few s Jr. s and Paul G. Fournier_ January 1957 EFFECTIVENESS AT TRANSONIC SPEEDS OF FLAP-TYPE AILERONS FOR RM L56J04 SEVERAL SPANWISE LOCATIONS ON A 4-PERCENT-THICK SWEPTBACK-WING-- FUSELAGE MODEL WITH AND WITHOUT TAILS s Gerald Hieser and Charles F. Whitcomb_ February 1957 RM L56J05 EXPERIMENTAL STATIC AERODYNAMIC FORCES AND MOMENTS AT HIGH SUB- SONIC SPEEDS ON A MISSILE MODEL DURING SIMULATED LAUNCHING FROM THE MIDSEMISPAN LOCATION OF A 45 ° SWEPTBACK WING-FUSELAGE-PYLON COMBINATION s William J. Alford s Jr. s and Thomas J. King s Jr._ January 1957 THEORETICAL INVESTIGATION OF THE ATTACK PHASE OF AN AUTOMATIC RM L56J08 INTERCEPTOR SYSTEM AT SUPERSONIC SPEEDS WITH PARTICULAR ATTENTION TO AERODYNAMIC AND DYNAMIC REPRESENTATION OF THE INTERCEPTOR s Windsor L. Sherman and Albert A. Schy s January 1957 RM L56J09 EXPLORATORY MATERIALS AND MISSILE-NOSE-SHAPE TESTS IN A 4_000 ° F SUPERSONIC AIR JET s Paul E. Purser and Russell N. Hopko_ December RM L56JI7 HINGE-MOMENT AND EFFECTIVENESS CHARACTERISTICS OF AN ASPECT- RATIO-8.2 FLAP-TYPE CONTROL ON A 60o DELTA WING AT MACH NUMBERS FROM 0.72 TO 1.96 s Lawrence D. Guy s January 1957 RM L56JI8 TRANSONIC AND SUPERSONIC CHARACTERISTICS OF A HORN-BALANCED CONTROL WITH UNBALANCING TAB ON A 55 ° SWEPTBACK WING_ Lawrence D. Guy_ January 1957 RM L56JI9 EXPERIMENTAL INVESTIGATION OF FLOW FIELDS AT ZERO SIDESLIP NEAR SWEPT- AND UNSWEPT-WING-FUSELAGE COMBINATIONS AT LOW SPEED s William J. Alford s Jr. s and Thomas J. King_ Jr. s January 1957 RM L56J29 EXPERIMENTAL STUDY OF THE EFFECTS OF SCALE ON THE ABSOLUTE VALUES OF ZERO-LIFT DRAG OF AIRCRAFT CONFIGURATIONS AT TRANSONIC SPEEDS_ Robert R. Howell and Albert L. Braslow s February 1957 RML56K05 PRESSURE DISTRIBUTIONS OVER A SERIES OFRELATED AFTERBODY SHAPES AS AFFECTED BYA PROPULSIVE JET AT TRANSONIC SPEEDS, Beverly Z.

Henry_ Jr._ and Maurice S. Cahn_January 1957 RML56K22 DRAG OF CONICAL ANDCIRCULAR-ARC BOATTAIL AFTERBODIES AT MACH NUMBERS FROM 0.6 TO 1.3_ Frank V. Silhan and JamesM. Cubbage_ Jr._ January 1957 RML56L07 LOW-SPEED PRESSURE-DISTRIBUTION INVESTIGATION OFA THIN-DELTA- WING--FUSELAGE MODEL HAVING DOUBLE SLOTTED FLAPSANDSPOILERS_ Delwin R. Croomand Jarrett K. Huffman_February 1957 RML56LI0 SUPERSONIC FREE-FLIGHT MEASUREMENT OF HEAT TRANSFER ANDTRANSI- TION ONA i0 ° CONE HAVING A LOW TEMPERATURE RATIO_Charles F. Merlet and Charles B. Rumsey_ January 1957 RML56LII TWO-DIMENSIONAL TRANSONIC INVESTIGATION OFFLOWS ANDFORCES ONA 9-PERCENT-THICK AIRFOILWITH30-PERCENT-CHORD FLAP_Walter F.

Lindsey and Robert G. Pitts_ February 1957 RML56L21 ZERO-LIFT DRAG OFA LARGE FUSELAGE CAVITYANDA PARTIALLY SUB- MERGED STORE ONA 52.5o SWEPTBACK-WING--BODY CONFIGURATION AS DETERMINED FROM FREE-FLIGHT TESTS AT MACH NUMBERS OF0.7 TO 1.53, SherwoodHoffman_February 1957 PRELIMINARY MEASUREMENTS OF ATMOSPHERIC TURBULENCE AT HIGH RML57AII ALTITUDE AS DETERMINED FROM ACCELERATION MEASUREMENTS ONLOCKHEED U-2 AIRPLANE [with list of references]_ ThomasL. Colemanand Jack Funk_ March 1957 SUPERSONIC AERODYNAMIC CHARACTERISTICS OF A LOW-DRAG AIRCRAFT RML57A25 CONFIGURATION HAVING ANARROW WING OF ASPECT RATIO1.86 ANDA BODY OFFINENESS RATIO20_ Warren Gillespie_ Jr._ March 1957 HINGE-MOMENT CHARACTERISTICS FORA SERIES OF CONTROLS ANDBALANC- RML57BOI ING DEVICES ONA 60° DELTA WING AT MACH NUMBERS OF 1.61 AND2.01_ Douglas R. Lord and K. R. Czarnecki_ April 1957 EXPERIMENTAL STATIC AERODYNAMIC FORCES AND MOMENTS AT HIGHSUBSONIC RML57B04 SPEEDS ONA MISSILEMODEL DURING SIMULATED LAUNCHING FROM UNSWEPT-_ SWEPTBACK-_ ANDMODIFIED-DELTA-WING - FUSELAGE COMBINATIONS AT ZERO SIDESLIP_William J. Alford_ Jr., and ThomasJ. King_ Jr._ March 1957 MEASUREMENT OF AERODYNAMIC HEATTRANSFER TODEFLECTED TRAILING- RML57B20 EDGE FLAPONDELTA FIN IN FREEFLIGHTAT MACH NUMBERS FROM 1.5 TO 2.6_ Leo T. Chauvin and JamesJ. Buglia_ April 1957 JET EFFECTS ONTHEDRAG OF CONICAL AFTERBODIES FORMACH NUMBERS OF RML57B21 0.6 TO 1.28_ JamesM. Cubbage_Jr._ April 1957 RML57B27 A FLIGHTINVESTIGATION TO DETERMINE THEEFFECTIVENESS OFMACH NUMBER 1.0_ 1.2_ AND1.41 FUSELAGE INDENTATIONS FORREDUCING THEPRESSURE DRAG OF A 45° SWEPTBACK WINGCONFIGURATION AT TRANSONIC ANDLOWSUPERSONIC SPEEDS_ Willard S. Blanchard_ Jr._ and SherwoodHoffman_May 1957 RML57C08 AN EXPERIMENTAL STUDY AT HIGHSUBSONIC SPEEDS OF SEVERAL TAIL CONFIGURATIONS ONA MODEL HAVING A 45° SWEPTBACK WING_ William C. Sleeman_Jr._ April 1957 RML57C18 HEAT-TRANSFER ANDPRESSURE DISTRIBUTION ONSIX BLUNT NOSES AT A MACH NUMBER OF 23 HowardS. Carter and Walter E. Bressette_ April RML57D04a MEASUREMENTS OF HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONAN 8-1NCH-DIAMETER HEMISPHERE-CYLINDER IN FREEFLIGHTFORA MACH NUMBER RANGE OF 2.00 TO 3.88_ Benjamine J° Garland and Leo T.

Chauvin_ April 1957 RML57D05 HEATTRANSFER ANDBOUNDARY-LAYER TRANSITION ONA HIGHLY POLISHED HEMISPHERE-CONE IN FREEFLIGHTAT MACHNUMBERS UP TO 3.14 AND REYNOLDS NUMBERS UP TO 24 x i06_ JamesJ.. Buglia_ April 1957 RML57DI8c PRELIMINARY RESULTS FROM A FREE-FLIGHT INVESTIGATION OF BOUNDARY- LAYER TRANSITION ANDHEATTRANSFER ONA HIGHLY POLISHED 8-1NCH- DIAMETER HEMISPHERE-CYLINDER AT MACH NUMBERS UP TO _ ANDREYNOLDS NUMBERS BASED ONA LENGTH OF I FOOT UP TO 17.7 x I0_ JamesR.

Hall_ Katherine C. Speegle_ and Robert O. Piland_ May 1957 RML57DI9 AERODYNAMIC CHARACTERISTICS OFMISSILE CONFIGURATIONS WITHWINGS OFLOW ASPECT RATIOFORVARIOUS COMBINATIONS OF FOREBODIES_ AFTERBODIES_ ANDNOSE SHAPES FORCOMBINED ANGLES OF ATTACK AND SIDESLIPAT A MACH NUMBER OF 2.01_ Ross B. Robinson_ June 1957 RML57DI9a EFFECTS ONADJACENT SURFACES FROM THEFIRING OF ROCKET JETS_ Walter E. Bressette and AbrahamLeiss_ June 1957 RML57DI9c HEATTRANSFER TO BODIES AT ANGLES OFATTACK_ William V. Feller_ June 1957 RML57D22 SOME EFFECTS OF WING HEIGHT ONTHEVERTICAL-TAIL PRESSURE DISTRI- BUTIONS OF A COMPLETE MODEL IN SIDESLIPAT HIGHSUBSONIC SPEEDS_ Albert G. Few_Jr._ and William J. Alford_ Jr._ July 1957 RML57D22c AERODYNAMIC HEATTRANSFER TO WINGSURFACES ANDWINGLEADING EDGES_ Aleck C. Bond_William V. Feller_ and William M. Bland_ Jr._ June RML57D23 HIGH-PRESSURE BLOWING OVER FLAPANDWING LEADING EDGE OF A THIN LARGE-SCALE 49° SWEPT WING-BODY-TAIL CONFIGURATION IN COMBINATION WITHA DROOPED NOSE ANDA NOSE WITHA RADIUSINCREASE_ Marvin P.

Fink and H. Clyde McLemore_ May 1957 THE SINE-COSINE METHOD FOR REDUCING THE INTERFERENCE PRESSURE DRA( RM L57D24 OF SWEPTBACK WINGS_ Maxime A. Faget_ July 1957 RM L57D25b HEAT TRANSFER IN REGIONS OF SEPARATED AND REATTACHED FLOWS_ Davis H. Crawford and Charles B. Rumsey_ June 1957 CHARACTERISTICS OF THE NIKE-CAJUN (CAN) ROCKET SYSTEM AND FLIGHT RM L57D26 INVESTIGATION OF ITS PERFORMANCE_ John F. Royall_ Jr._ and Benjamine J. Garland_ July 1957 EFFECTS OF WING INBOARD PLAN-FORM MODIFICATIONS ON LIFT_ DRAGj RM L57D29 AND LONGITUDINAL STABILITY AT MACH NUMBERS FROM 1.0 TO 2.3 OF A ROCKET-PROPELLED FREE-FLIGHT MODEL WITH A 52.5 ° SWEPTBACK WING OF ASPECT RATIO 3_ Allen B. Henning_ June 1957 EXPERIMENTAL AND THEORETICAL AERODYNAMIC CHARACTERISTICS OF 2 RM L57E02 LOW-ASPECT RATIO DELTA WINGS AT ANGLES OF ATTACK TO 50 ° AT MACH NUMBER OF 4.07_ Fred M° Smith_ July 1957 RM L57E08 LIMITED HEAT-TRANSFER_ DRAG_ AND STABILITY RESULTS FROM INVESTI- GATION AT MACH NUMBERS UP TO 9 OF LARGE ROCKET-PROPELLED i0o CONE_ James R. Hall and Katherine C. Speegle_ July 1957 EXPERIMENTAL INVESTIGATION OF EFFECTS OF MODERATE SIDESLIP ON RM L57EI0 FLOW FIELDS NEAR 45 ° SWEPT-WING FUSELAGE COMBINATION AT LOW SPEED_ William J. Alford_ Jr._ and Thomas J. King_ Jr._ July 1957 THE AERODYNAMIC CHARACTERISTICS OF A BODY IN THE TWO-DIMENSIONAL RM L57E14 FLOW FIELD OF A CIRCULAR-ARC WING AT A MACH NUMBER OF 2.01_ John P. Gapcynski and Harry W. Carlson_ July 1957 AERODYNAMIC HEATING AND BOUNDARY-LAYER TRANSITION ON A 1/10- RM L57EI4a POWER NOSE SHAPE IN FREE FLIGHT AT MACH NUMBERS UP TO 6.7 AND FREE-STREAM REYNOLDS NUMBERS UP TO 16 x 106 Benjamine J Garland_ Andrew G. Swanson_ and Katherine C. Speegle_ June 1957 AERODYNAMIC CHARACTERISTICS OF A SPOILER-SLOT-DEFLECTOR CONTROL RM L57EI6a ON A 45 ° SWEPTBACK WING AT MACH NUMBERS OF 1.61 AND 2.01_ Douglas R. Lord and Robert Moring_ July 1957 ROCKET-MODEL INVESTIGATION OF HINGE MOMENTS ON TRAILING-EDGE RM L57F04 CONTROL ON 52.5 ° SWEPT WING BETWEEN MACH NUMBERS OF 0.70 AND 1.80_ C. William Martz_ August 1957 TWO-DIMENSIONAL AIRFOIL CHARACTERISTICS OF FOUR NACA 6A-SERIES RM L57F05 AIRFOILS AT TRANSONIC MACH NUMBERS UP TO 1.25_ Charles L. Ladson_ August 1957 AERODYNAMIC HEATING OF A THIN_ UNSWEPT_ UNTAPERED 3 MULTIWEB_ RM L57F06 ALUMINUM-ALLOY WING AT MACH NUMBERS UP TO 2.67 AS DETERMINED FROM A FREE-FLIGHT INVESTIGATION OF A ROCKET-PROPELLED MODEL_ H. Kurt Strass and Emily W. Stephens_ August 1957 55O FREE-FLIGHT INVESTIGATION OF COMPARATIVE ZERO-LIFT ROLLING _M L57FI0 EFFECTIVENESS OF A LEADING-EDGE AND A TRAILING-EDGE AIR-JET SPOILER ON AN UNSWEPT WING_ Alan B. Kehlet_ August 1957 EXPLORATORY INVESTIGATION OF TRANSPIRATION COOLING OF A 40 ° RM L57FII DOUBLE WEDGE USING NITROGEN AND HELIUM AS COOLANTS AT STAGNATION TEMPERATURES OF i_295 ° TO 2_910 ° F_ Bernard Rashis_ August 1957 FLIGHT INVESTIGATION OF FACTORS AFFECTING CHOICE OF MINIMUM RM L57FI3 APPROACH SPEED FOR CARRIER-TYPE LANDINGS OF SWEPT-WING JET FIGHTER AIRPLANE_ Lindsay J. Lina, Garland J. Morris_ and Robert A.

Champine_ September 1957 FREE-FLIGHT INVESTIGATION OF JET EFFECTS AT LOW SUPERSONIC MACH RM L57F19 NUMBERS ON A FIGHTER-TYPE CONFIGURATION EMPLOYING A TAIL-BOOM ASSEMBLY. LONGITUDINAL STABILITY AND TRIM_ Bruce G. Jackson and Norman L. Crabill_ August 1957 RM L57F20 HYDRODYNAMIC INVESTIGATION OF MODEL OF SUPERSONIC MULTIJET WATER- BASED AIRCRAFT WITH ENGINES EXHAUSTING FROM STEP_ Ulysse J.

Blanchard_ September 1957 RM L57F27 TEMPERATURE MEASUREMENTS FROM A FLIGHT TEST OF TWO WING-BODY COMBINATIONS AT 7° ANGLE OF ATTACK FOR MACH NUMBERS TO 4.86 AND REYNOLDS NUMBERS TO 19.2 x i06_ Leo T. Chauvin_ September 1957 RM L57G02 AIRPLANE MEASUREMENTS OF ATMOSPHERIC TURBULENCE FOR ALTITUDES BETWEEN 20,000 AND 55_000 FEET OVER WESTERN PART OF UNITED STATES [with list of references]_ Thomas L. Coleman and Emilie C. Coe_ August 1957 EFFECT OF FULL-SPAN TRAILING-EDGE ELEVONS ON THE TRANSONIC LONGI- RM L57G03 TUDINAL AERODYNAMIC CHARACTERISTICS OF A WING-BODY COMBINATION HAVING A 3-PERCENT-THICK TRIANGULAR WING WITH 60 ° LEADING-EDGE SWEEP_ Chris C. Critzos and Willard E. Foss_ Jr._ September 1957 RM L57G05 AERODYNAMIC AND HYDRODYNAMIC CHARACTERISTICS OF A PROPOSED SUPER- SONIC MULTIJET WATER-BASED HYDRO-SKI AIRCRAFT WITH A VARIABLE- INCIDENCE WING_ William W. Petynia_ Dennis F. Hasson_ and Stanley H. Spooner_ October 1957 RM L57G08 AN INVESTIGATION OF SCREENS FOR REMOVING DISTORTIONS IN DUCTED FLOWS AT HIGH SUBSONIC SPEEDS_ Charles C. Wood and Gerald Knip_ Jr._ September 1957 RM L57GO8a WIND-TUNNEL INVESTIGATION OF THE EFFECT OF ASPECT RATIO AND CHORD- WISE LOCATION ON EFFECTIVENESS OF SPOILER-SLOT-DEFLECTOR CONTROLS ON THIN UNTAPERED WINGS AT TRANSONIC SPEEDS_ Alexander D. Hammond and Jarrett K. Huffman_ September 1957 RML57GI0 COMPARISON OF LOW-LIFTDRAG AT MACH NUMBERS FROM 0.74 TO I. 37 OF ROCKET-BOOSTED MODELS HAVING EXTERNALLY BRACED WINGS ANDCANTI- LEVER WINGS_ WaldoL. Dickens and Earl C. Hastings_ Jr._ September RML57GII FREE-FLIGHT INVESTIGATION OF JET EFFECT ONTHELOW-LIFTDRAG AND LONGITUDINAL TRIMOFA SUPERSONIC INTERCEPTOR-TYPE AIRPLANE CON- FIGURATION WITHAN OVERHANGING TAIL BOOM AT MACH NUMBERS FROM 1.09 TO 1.34_ Willard S° Blanchard_ Jr._ September1957 RML57GI2 EFFECTS OF WING WARP ONTHELIFT_ DRAG_ ANDSTATIC LONGITUDINAL STABILITYCHARACTERISTICS OF ANAIRCRAFT CONFIGURATION HAVING AN ARROW WING OF ASPECT RATIO1.86 AT MACH NUMBERS FROM i.I TO 1.7_ Warren Gillespie_ Jr._ August 1957 RML57GI6 EFFECT OF GROUND PROXIMITY ONAERODYNAMIC CHARACTERISTICS OF 2 HORIZONTAL-ALTITUDE JET VERTICAL-TAKE-OFF-AND-LANDING AIRPLANE MODELS_ William A. Newsom_ Jr._ September1957 RML57GI7 TRANSONIC INVESTIGATION OF EFFECTS OF SPANWISE ANDCHORDWISE EX- TERNAL STORE LOCATION ANDBODY CONTOURING ONAERODYNAMIC CHARAC- TERISTICS OF45° SWEPTBACK WING-BODY CONFIGURATIONS_ Albin O.

Pearson_ September 1957 RML57GI8 EFFECT OF CONICAL ANDFLATSTING-MOUNTED WINDSHIELDS ONZERO-LIFT DRAG OFFLARE-STABILIZED BLUFFBODY AT MACH NUMBERS FROM 0.6 TO 1.15_ Willard S. Blanchard_ Jr._ September 1957 PRESSURE MEASUREMENTS AT TRANSONIC ANDLOWSUPERSONIC SPEEDS ON RML57GI9 A THIN CONICAL CAMBERED LOW-ASPECT-RATIO DELTA WINGIN COMBINA- TIONWITHBASICANDINDENTED BODIES_ John P. Mugler_ Jr._ September1957 FREE-FLIGHT INVESTIGATION OF DRAG OFMODEL OF 60° DELTA-WING RML57G29 BOMBER WITHSTRUT-MOUNTED SIAMESE NACELLES ANDINDENTED FUSELAGE AT MACH NUMBERS FROM 0.80 TO 1.35_ SherwoodHoffman_ September RML57G30 FREE-FLIGHT SKIN-TEMPERATURE ANDSURFACE-PRESSUREMEASUREMENTS ON A HIGHLY POLISHED NOSE HAVING A i00 ° TOTAL-ANGLE CONE ANDA i0 ° HALF-ANGLE CONICAL FLARESECTION UP TO A MACH NUMBER OF 4.08_ Bernard Rashis and Aleck C. Bondj August 1957 RML57HI3 BUFFET TESTS OF ATTACK-AIRPLANE MODEL WITHEMPHASIS ONANALYSIS OFDATAFROM WIND-TUNNEL TESTS_ Don D. Davis and DeweyE. Wornom_ February 1958 RML57HI9 TESTS OFAERODYNAMICALLY HEATED MULTI-WEB WING STRUCTURES IN A FREEJET AT MACH NUMBER 2. TWO ALUMINUM-ALLOY MODELS OF 20-1NCH CHORD WITH0.064-1NCH-THICK SKINAT ANGLES OF ATTACK OF0° AND±2°_ GeorgeneH. Miltonberger_ George E. Griffith_ and John R. Davidson_ October 1957 RML57103 PRELIMINARY INDICATIONS OF THECOOLING ACHIEVED BYEJECTING WATER UPSTREAM FROM THESTAGNATION POINTOF HEMISPHERICAL_ 80° CONICAL, ANDFLAT-FACED NOSE SHAPES AT A STAGNATION TEMPERATURE OF 4,000OF, Bernard Rashis, October 1957 RML57104 TRANSONIC WIND-TUNNEL INVESTIGATION OF THELOW-LIFTAERODYNAMIC CHARACTERISTICS_ INCLUDING EFFECTS OF LEADING-EDGE DROOP AND THICKNESS, OF A THIN TRAPEZOIDAL WINGIN COMBINATION WITHBASIC ANDINDENTED BODIES_ ThomasC. Kelly, October 1957 RML57110 AERODYNAMIC CHARACTERISTICS AT A MACH NUMBER OF 4.06 OFA TYPICAL SUPERSONIC AIRPLANE MODEL USINGBODY ANDVERTICAL-TAIL WEDGES TO IMPROVE DIRECTIONAL STABILITY, Robert W. Dunning_ December1957 RML57112 LIMITEDTESTS OFMOLYBDENUM COATED WITHMOLYBDENUM DISILICIDE IN A SUPERSONIC HEATED-AIR JET ANDBRIEFDESCRIPTION OF THECOATING FACILITY_E. M. Fields and N. T. Wakelyn, January 1958 RML57123 NORMAL-FORCE ANDHINGE-MOMENT CHARACTERISTICS AT TRANSONIC SPEEDS OFFLAP-TYPE AILERONS AT THREE SPANWISE LOCATIONS ONA 4-PERCENT- THICKSWEPTBACK-WING - BODY MODEL ANDPRESSURE-DISTRIBUTION MEA- SUREMENTS ONAN INBOARD AILERON_ Jack F. Runckel and Gerald Hieser, December1957 RML57127 AN INITIAL EXPERIMENTAL STUDY OF THEEFFECT OF VARIATIONS IN FREQUENCY ANDIMPULSE ONTHEREDUCTION IN TEMPERATURE RECOVERY FACTOR AFFORDED BYLARGE-SCALE UNSTEADY FLOW_ Robert R. Howell_ January 1958 RML57J04 EFFECT OF HOT-JET EXHAUST ONPRESSURE DISTRIBUTIONS ANDEXTERNAL DRAG OF SEVERAL AFTERBODIES ONSINGLE-ENGINE AIRPLANE MODEL AT TRANSONIC SPEEDS, Harry T. Norton_ Jr., and John M. Swihart, March 1958 RML57JI6 EFFECT OF TARGET-TYPE THRUST REVERSER ONTRANSONIC AERODYNAMIC CHARACTERISTICS OFA SINGLE-ENGINE FIGHTER MODEL, John M.

Swihart, January 1958 RML57J22 TABULATED PRESSURE DATAFORA 60° DELTA-WING-BODY-TAIL MODEL WITHA HOTJET EXHAUSTING FROM A PYLON-MOUNTED NACELLE_ Edwin E. Lee_ Jr., and John M. Swihart_ February 1958 RML57J23a AN INVESTIGATION OF THEDRAG CHARACTERISTICS OF SPEED BRAKES FOR MACH NUMBERS FROM 0.20TO 1.30_ Allen R. Vick_ January 1958 RML57J24 FREE-FLIGHT PRESSURE MEASUREMENTS OVER A FLARE-STABILIZED ROCKET MODEL WITHA MODIFIED VON KARMAN NOSE FORMACH NUMBERS UP TO 4.3_ William M. Bland, Jr., and Ronald Kolenkiewicz, January 1958 EXPERIMENTAL HINGE MOMENTS ONTWO FREELY OSCILLATING TRAILING- RML57J25 EDGE CONTROLS HINGED AT 55 PERCENT CONTROL CHORD_ C. William Martz_ December1957 RML57J31 FREE-FLIGHT TRANSONIC MODEL INVESTIGATION OF JET EFFECTS ONA FIGHTER-TYPE CONFIGURATION EMPLOYING A TAlL BOOM ANDTHREE HORIZONTAL-TAlL POSITIONS_ Bruce G. Jackso% February 1958 RML57KI2 SOME EFFECTS OFFIN LEADING-EDGE SHAPE ONAERODYNAMIC HEATING AT MACH NUMBER 2.0 AT A STAGNATION TEMPERATURE OFABOUT 2_600 ° R_ William M. Bland_ Jr._ January 1958 STUDY OF EXIT PHASE OFFLIGHTOF A VERY HIGHALTITUDE HYPERSONIC RML57K21 AIRPLANE BYMEANS OF A PILOT-CONTROLLED ANALOG COMPUTER_ Windsor L. Sherma% Stanley Faber_ March 1958 FEASIBILITYOFNOSE-CONE COOLING BYTHEUPSTREAM EJECTION OF RML57K22 SOLIDCOOLANTS AT THESTAGNATION POIN%William H. Kinard_ March SURFACE PRESSURE DISTRIBUTIONS ONA LARGE-SCALE 49° SWEPTBACK RML57K25 WING-BODY-TAlL CONFIGURATION WITHBLOWING APPLIED OVER THEFLAPS ANDWING LEADING EDGE_ H. Clyde McLemoreand Marvin P. Fink_ February 1958 FREE-FLIGHT AERODYNAMIC-HEATING DATAATMACH NUMBERS UP TO 10.9 RML57K29 ONFLAT-FACED CYLINDER_ William M. Bland_ Jr._ Andrew G. Swanso% and Ronald Kolenkiewicz_ January 1958 HEAT-TRANSFER MEASUREMENTS IN FREEFLIGHTAT MACH NUMBERS UP TO RML57L03 14.6 ONFLAT-FACED CONICAL NOSE WITHTOTAL ANGLE OF 29% Charles B. Rumseyand Dorothy B. Le% January 1958 RML57L04 FREE-FLIGHT INVESTIGATION AT MACH NUMBERS FROM 0.8 TO 1.5 OF THE EFFECT OF A FUSELAGE INDENTATION ONTHEZERO-LIFTDRAG OF A 52.5° SWEPTBACK-WING - BODY CONFIGURATION WITHSYMMETRICALLY MOUNTED STORES ONTHEFUSELAGE_ SherwoodHoffma% February 1958 RML57L09 MEASUREMENTS OFAERODYNAMIC HEATTRANSFER IN TURBULENT SEPARATED REGIONS AT MACH NUMBER OF 1.8_ Benjamine J. Garland and James R. Hall_ February 1958 RML57LI2 SUMMARY OFLOCATIONS_ EXTENTS_ ANDINTENSITIES OF TURBULENT AREAS ENCOUNTERED DURING FLIGHTINVESTIGATIONS OFJET STREAM 3 JANUARY 7 - APRIL 28_ 1957 [with list of references]_ Martin R. Copp_ March 1958 HEATTRANSFER MEASURED ONA FLAT-FACE CYLINDER-FLARE CONFIGURA- RML58A06 TION IN FREE FLIGHTAT MACH NUMBERS FROM 1.6 TO 2.7_ Dorothy B.

Lee and Andrew G. Swanso%February 1958 RM L58A07 INVESTIGATION OF THE LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A TRAPEZOIDAL-WING AIRPLANE MODEL WITH VARIOUS VERTICAL POSITIONS OF WING AND HORIZONTAL TAIL AT MACH NUMBERS OF 1.41 AND 2.01_ Gerald V. Foster_ March 1958 RML58AI0 EFFECTS OF NOSE AND AFTERBODY MODIFICATIONS ON AERODYNAMIC CHARAC- TERISTICS OF A BODY WITH AND WITHOUT A VERTICAL TAIL AT A MACH NUMBER OF 2.01_ Gerald V. Foster_ April 1958 RM L58AI3 HEAT TRANSFER TO 0 ° AND 75 ° SWEPT BLUNT LEADING EDGES IN FREE FLIGHT AT MACH NUMBERS FROM 1.90 TO 3.07_ Robert L. O'Neal and Aleck C. Bond_ March 1958 RM L58AI7 EFFECT OF DISTRIBUTED GRANULAR-TYPE ROUGHNESS ON BOUNDARY-LAYER TRANSITION AT SUPERSONIC SPEEDS WITH AND WITHOUT SURFACE COOLING [with list of references]_ Albert L. Braslow_ March 1958 RM L58A22 PRELIMINARY INVESTIGATION OF LAND-WATER OPERATION WITH A 1/10- SCALE MODEL OF A JET AIRPLANE EQUIPPED WITH HYDRO-SKIS_ William C. Thompson_ March 1958 RM L58A23 AERODYNAMIC CHARACTERISTICS OVER A MACH NUMBER RANGE OF 1.40 TO 2.78 OF A ROCKET-PROPELLED AIRPLANE CONFIGURATION HAVING A LOW 52.5 ° DELTA WING AND AN UNSWEPT HORIZONTAL TAIL_ Alan B. Kehlet_ March 1958 RM L58A27 JET EFFECTS ON THE BASE DRAG OF A CYLINDRICAL AFTERBODY WITH EXTENDED NOZZLES_ William J. Nelson and William R. Scott_ April RML58A31 EFFECTS OF SHOCK - BOUNDARY-LAYER INTERACTION ON THE PERFORMANCE OF A LONG AND A SHORT SUBSONIC ANNULAR DIFFUSER_ Charles C. Wood and John R. Henry_ April 1958 RM L58B04 FREE-FLIGHT INVESTIGATION TO DETERMINE THE INLET EXTERNAL DRAG OF FOUR INLET MODELS AT MACH NUMBERS FROM 1.50 TO 3.00_ Walter L. Kouyoumjia% April 1958 RM L58B05 LOW-SUBSONIC INVESTIGATION TO DETERMINE CHORDWISE PRESSURE DISTRIBUTION AND EFFECTIVENESS OF SPOILERS ON THIN_ LOW-ASPECT- RATIO_ UNSWEPT_ UNTAPERED_ S_41SPAN WING AND ON WING WITH LEADING- AND TRAILING-EDGE FLAPS [with list of references]_ Delwin R. Croom_ April 1958 RM L58B06 PRELIMINARY STUDY OF AIRPLANE CONFIGURATIONS HAVING TAIL SURFACES OUTBOARD OF THE WING TIPS_ William C. Sleema% Jr._ March 1958 RM L58B07 AERODYNAMIC CHARACTERISTICS OF A CANARD AND AN OUTBOARD-TAIL AIRPLANE MODEL AT A MACH NUMBER OF 2.01_ M. Leroy Spearman and Ross B. Robinson_ March 1958 HEATTRANSFER FORMACH NUMBERS UP TO 2.2 ANDPRESSURE DISTRIBU- RML58BI8 TIONSFORMACH NUMBERS UP TO4.7 FROM FLIGHTINVESTIGATIONS OF FLATFACE-CONE ANDHEMISPHERE-CONE_ Katherine C. Speegle_ Leo T.

Chauvin_ and Jack C. Heberlig_ May 1958 EFFECT OF COMPRESSIBILITY ONTHEHOVERING PERFORMANCE OFTWO RML58BI9 10-FOOT-DIAMETER HELICOPTER ROTORS TESTED IN THELANGLEY FULL- SCALE TUNNEL_ Joseph W. Jewel_ Jr._ and Robert D. Harrington_ April 1958 SOME EFFECTS OF ROUGHNESS ONSTAGNATION-POINT HEATTRANSFER AT A RML58CI0 MACH NUMBER OF 2_ A STAGNATION TEMPERATURE OF 3_530oF_ ANDA REYNOLDS NUMBER OF 2.5 x 106 PERFOOT_ H. Kurt Strass and ThomasW. Tyner_ May 1958 EFFECTS OF EXTERNAL STORE-PYLON CONFIGURATION ANDPOSITION ONTHE RML58C13 AERODYNAMIC CHARACTERISTICS OF A 45° SWEPT WING-FUSELAGE COMBINA- TIONAT A MACH NUMBER OF 1.61_ Odell A. Morris_ May 1958 RML58CI4a HEATTRANSFER ANDPRESSURE MEASUREMENT ONA 5-1NCHHEMISPHERICAL CONCAVE NOSE AT A MACH NUMBER OF 2.0_ J. Thomas Markley_ July 1958 EFFECTS OF VERTICAL LOCATION OFTHEWING ANDHORIZONTAL TAIL ON RML58C18 THESTATIC LATERAL ANDDIRECTIONAL STABILITYOFA TRAPEZOIDAL-WING AIRPLANE MODEL AT MACH NUMBERS OF 1.41 AND2.01_ Ross B. Robinson_ July 1958 RML58C24 TESTS OF AERODYNAMICALLY HEATED MULTI-WEB WINGSTRUCTURES IN A FREEJET AT MACH NUMBER 2. AN ALUMINUM-ALLOY MODEL OF 40-1NCH CHORD WITH0.125-1NCH-THICK SKIN_George E. Griffith and Georgene H. Miltonberger_ June 1958 INVESTIGATION OF THEAERODYNAMIC CHARACTERISTICS OF A MODEL OFA RML58C27 SUPERSONIC BOMBER CONFIGURATION WITHA SWEPT ANDAN UNSWEPT WING AT MACH NUMBERS FROM 1.79 TO 2.67_ H. NormanSilvers and Raymond L. Zedekar_ July 1958 PRESSURE LOADS PRODUCED ONA FLAT-PLATE WING BY ROCKET JETS RML58D09 EXHAUSTING IN A SPANWISE DIRECTION BELOW THEWING ANDPERPENDICU- LAR TOA FREE-STREAM FLOW OFMACH NUMBER 2.0_ Ralph A. Falanga and Joseph J. Janos_ June 1958 SOME FACTORS AFFECTING STABILITYANDPERFORMANCE CHARACTERISTICS RML58DI6 OF CANARD AIRCRAFT CONFIGURATIONS_ M. Leroy Spearmanand Cornelius Driver_ June 1958 AERODYNAMIC CHARACTERISTICS OF SEVERAL JET-SPOILER CONTROLS ONA RML58DI8 45° SWEPTBACK WING AT MACH NUMBERS OF 1.61 AND2.01_ Douglas R.

Lord_ June 1958 RML58E01a HEATTRANSFER TO SURFACES ANDPROTUBERANCES IN A SUPERSONIC TURBU- LENTBOUNDARY LAYER_ Paige B. Burbank and H. Kurt Strass_ July RML58E05 TRANSONIC CHARACTERISTICS OF OUTBOARD AILERONS ONA 4-PERCENT- THICK30° SWEPTBACK WING_INCLUDING SOME EFFECTS OF AILERON TRAILING-EDGE THICKNESS ANDAERODYNAMIC BALANCE_ Charles F.

Whitcomb and Chris C. Critzos_ July 1958 RML58E07a PRELIMINARY STUDIES OFMANNED SATELLITES WINGLESS CONFIGURATION: NONLIFTING_ MaximeA. Faget_ Benjamine J. Garland_ and JamesJ.

Bugli% August 1958 RML58EO8a SIMULATION STUDY OFA HIGH-PERFORMANCE AIRCRAFT INCLUDING THE EFFECT ONPILOT CONTROL OF LARGE ACCELERATIONS DURING EXIT AND REENTRY FLIGHT_C. H. Woodling_ James B. Whitten_ Robert A.

Champin%and Robert E. Andrews_July 1958 RML58E09 WIND-TUNNEL INVESTIGATION OF AERODYNAMIC ANDSTRUCTURAL DEFLEC- TION CHARACTERISTICS OF GOODYEAR INFLATOPLANE_ Bennie W. Cock% Jr._ September1958 RML58EI2 WIND-TUNNEL INVESTIGATION OF WING LOADS DUETO DEFLECTED INBOARD AILERONS ON45° SWEPTBACK WING AT TRANSONIC SPEEDS_ Atwood R.

Heath_ Jr._ and Ann W. Igo% July 1958 RML58EI5a EXPERIMENTAL ABLATION COOLING_ Aleck C. Bond_ Bernard Rashis_ and L. Ross Levin_ July 1958 RML58E21 AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS 2.36 AND2.87 OF AN AIRPLANE CONFIGURATION HAVING A CAMBERED ARROW WING WITHA 75o SWEPT LEADING EDGE_ Joseph M. Hallissy_ Jr._ and Dennis F.

Hasson_August 1958 RML58E22 QUALITATIVE MEASUREMENTS OF THEEFFECTIVE HEATS OF ABLATION OF SEVERAL MATERIALS IN SUPERSONIC AIR JETSAT STAGNATION TEMPERA- TURES UP TO II_000 ° F_ Bernard Rashis_ William G. Witt% and Russell N. Hopko_July 1958 RML58E26 LONGITUDINAL ANDLATERAL AERODYNAMIC CHARACTERISTICS AT COMBINED ANGLES OF ATTACK ANDSIDESLIPOF A GENERALIZED MISSILEMODEL HAVING A RECTANGULAR WING AT A MACH NUMBER OF 4.08_ Fred M. Smith_ EdwardF. Ulmann_and Robert W. Dunning_ August 1958 RML58F24 ANALYSIS OF PRESSURE DATAOBTAINED AT TRANSONIC SPEEDS ONA THIN LOW-ASPECT-RATIO CAMBERED DELTA WING-BODY COMBINATION_ John P.

Mugler_ Jr._ September 1958 RML58F26 INVESTIGATION OF A TILTING-WING VERTICAL-TAKE-OFF-AND-LANDING JET AIRPLANE MODEL IN HOVERING ANDTRANSITION FLIGHT_Robert H. Kirby and JamesL. Hassell_ Jr._ August 1958 RML58G29 ROCKET-MODEL INVESTIGATION TO DETERMINE THELIFT ANDPITCHING EFFECTIVENESS OF SMALL PULSE ROCKETS EXHAUSTED FROM THEFUSELAGE OVER THESURFACE OF ANADJACENT WING AT MACH NUMBERS FROM 0.9 TO 1.8_ C. William Martz_ September1958 Applicable NACA Technical Memoranda TM 961 FLOW AROUND WINGS ACCOMPANIED BY SEPARATION OF VORTICES, C. Schmieden, December 1940 The author considers inviscid flow about a flat plate and about airfoils and constructs a complex velocity potential which accounts for the separation of the flow from the rear side of the plate (airfoil). The flow constructed separates at the trailing edge of the plate (airfoil) on the high pressure side. On the suction side the flow separates tangentially at a point upstream of the trailing edge forming a vortex zone behind the plate. The vortex zone is idealized as two vortex sheets of equal and opposite circulation. The velocities at the edge of the vortex sheets is equal to the free stream velocity and the vortex sheets form a boundary for a dead air region behind the airfoil and therefore become free streamlines.

The condition of constant speed along the free streamlines and of the dead air region disappearing at infinity are sufficient to determine the unique streamlines bounding the dead air region.

The limiting case of pure Helmholtz flow and steady circulation are found as part of the solution.

For the case of a flat plate the solution given is np£V 2 sin_ O0 Lift = P = Y a _ n+_ . _ . 2 l-2sin _ cos _ +sin 2 _ +--_-slnza-sln a In [2(l-sin _)] Drag = P = 0 X where V = free stream velocity OO P = free stream density = length of the plate = angle of attack TM 974 BOUNDARY LAYER REMOVAL BY SUCTION, O. Schrenk, April 1941 A discussion is given of some aspects of boundary layer removal by suction together with a description, and some excellent pictures, of experiments to evaluate the effects of suction on the lift of a small airplane.

It is pointed out that not only does boundary layer suction alter and control the boundary layer directly but the suction has a secondary "sink effect" in which the suction tends to alter the pressure distribution in the vicinity of the suction slots. The altered pressure gradient is more favorable on both sides of the suction slot.

Data are presented to show the effect of suction volume flow and suction pressure on the lift coefficient of both thin and thick airfoils. These data were obtained in wind tunnel tests.

Also presented are someexcellent pictures showing the effect of suction on a deflected and undeflected flap on an airplane modi- fied to have suction on the flap.

TM 988 OBSERVATIONS OFTHEEFFECT OFWING APPENDAGES ANDFLAPSONTHE SPREAD OF SEPARATION OF FLOW OVER THEWING,G. Hartwig, September In tests to observe flow separation over wings, it was found that the wings with the straight leading of trailing edge did not give results as good as those obtained with a tapered wing. Also, adding twist to the wing added overall control at the maximum lift coefficient and reduced the flow separation for any one wing at any one angle of attack.

WIND-TUNNEL INVESTIGATION OF THEHORIZONTAL MOTION OFA WING NEAR TM 1095 THEGROUND, Y. M. Serebrisky and S. A. Biachuev, September 1946 A rectangular wing with Clark Y-H profile was tested with and without flaps. The distance from the trailing edge of the wing to the ground was varied within the limits 0.75 < n/c < 0.25 (n = distance from trailing edge to ground and c =--wing_hord). Mea- surements were madeof the lift, drag, and pitching moment, and the pressure distribution at one section. For a wing without flaps and one with flaps a considerable decrease in the lift force and a drop in the drag was obtained at angles of attack (_) below stalling. The flow separation near the ground occurred at smaller angles of attack than was the case for a great height above the ground. At horizontal steady flight for practical values of the height above the ground, the maximum lift coefficient for the wing without flaps changedlittle, but markedly decrease for the wing with flaps. Analysis of these phenomena involve the investigation of the pressure distribution. The pressure distribution curves showedthat the changes occurring near the ground were not equiva- lent to a change in _. At the lower surface of the section a very strong increase in the pressures was observed. The pressure changes on the upper surface at _'s below stalling were insignifi- cant and lead mainly to an increase in the unfavorable pressure gradient, resulting in the earlier occurrence of separation. For a wing with flaps at large _ for n < 0.5c, the flow between the wing and the ground was retarted so greatly that the pressure co- efficient at the lower surface of the section was very near its limiting value, and any further possibility of increase in the pressure was very small.

TM 1108 FORCE ANDPRESSURE-DISTRIBUTION MEASUREMENTS ONA RECTANGULAR WING WITHA SLOTTED DROOP NOSE ANDWITHEITHERPLAINANDSPLIT FLAPSIN COMBINATION ORA SLOTTED FLAP, H. G. Lemme,March 1947 Force measurementsand pressure distribution measurementson the midsection of a rectangular wing with a slotted droop nose and end plates were made.

For large droop-nose deflections and angles of attack, the air flow resulting from the slot between the droop nose and the wing should retard friction layers on the surface of the airfoil.

The low-pressure points at the droop of the droop nose should also be reduced by the slotted droop nose.

The wind-tunnel measurementsdid not verify these decreases. A slot effect was not recognizable. Incontrast to the simple droop nose, the droop-nose angle most favorable to maximum lift was no longer the samewith and without flap deflection. The low- pressure points at the droop of the droop nose were greater for deflection of the slotted droop nose than for deflection of the simple droop nose and favored rather than'delayed the separation of flow on the surface of the airfoil. For like model configura- tions, the maximum lift obtained for a wing with slotted droop nose was smaller than the one obtained for a wing with simple droop nose. The slotted droop nose had no advantage over the simple droop nose.

TM 1127 RUSSIAN LAMINAR FLOW AIRFOILS3RDPART: MEASUREMENTS ONTHEPRO- FILE NO. 2315 BIS WITHAVA-NOSE FLAP, F. Riegels, September 1947 The tests on the Russian airfoil 2315 Bis were continued. This airfoil shows, according to Moscowtests, good laminar-flow char- acteristics. Several tests were prepared in the large wind tunnel at Gottingen; partial results were obtained. It was believed that an airfoil with a nose flap adjusted itself more readily to the flow pattern at high lift; therefore, the high flow velocities at the nose which usually cause a premature separation on airfoils with pointed noses are avoided. Several measurementswith transi- tion wires of 0.i-, 0.3-, and 0.5-millimeter diameter were taken in order to determine whether for small Ca-Values the laminar effect would be impaired by distrubances on the pressure side; such disturbances would be certain to originate for the nonextend- ed position of the flaps. Wind-tunnel corrections were taken into consideration in the customary manner.

It was indicated that the new AVAnose flap will produce consider- able lift increases for profiles with small nose radii even for small flap chords. The corresponding changes of momentare small and can be tolerated. The more the flight speed approached sound velocity the more the development will lead toward profiles with small radii of the nose; accordingly, a way is shownfor obtaining practically useful maximum lifts for such profiles. Considering the results obtained so far, one may say that transition wires of thicknesses of the sameorder of magnitude as the thickness of the local boundary layer are dangerous. The question whether the dis- turbances originating with the installation of the nose flap will cause the sameeffects as transition wires will have to be inves- tigated further.

Model of flap investigated TM 1129 TEST REPORT ON MEASUREMENTS ON A 4 SERIES OF TAPERED WINGS OF SMALL ASPECT RATIO (TRAPEZOIDAL WING WITH FUSELAGE), Lange/Wacke, July 1947 This is the second of a series of six reports dealing with three- and six-component measurements on the tapering series at small aspect ratio. The present report concerns the trapezoidal wing with fuselage.

It was found that the drag increased with increasing taper, start- ing at alpha = 18 ° , but no expressed drag increase due to the fuselage is observed. The neutral-point position at ca = 0 moves backward with increasing taper in the same way as on the wing alone.

The overhanging fuselage nose caused the neutral point to move forward. Lift and drag were nearly independent of the yawed flow.

At small angles of attack the taper had little effect on the transverse force. The effect of the fuselage on the rolling moments was unimportant. The effect of the fuselage on the pitch- ing moment with respect to beta was zero compared to the wing alone.

This report consisted mainly of results found from testing the trapezoidal wing with and without a fuselage.

TEST REPORT ON THREE- AND SIX-COMPONENT MEASUREMENTS ON A SERIES TM 1146 OF TAPERED WINGS OF SMALL ASPECT RATIO (PARTIAL REPORT: ELLIPTIC WING), Lange/Wacke, June 1947 This report gave the results of a series of elliptic wings. The aspect ratio varied from 1 to 2 with the sweepback. The contour was formed by elliptic arcs. The influence of sweepbackand con- tour upon the neutral point was shown. The airfoil was an NACA 0012 section. The tests were run in the 3 x 2.15mwind-tunnel.

Forces and momentswere measured and presented in the form of graphs and charts.

CALCULATIONS ANDEXPERIMENTAL INVESTIGATIONS ONTHEFEED-POWER TM 1167 REQUIREMENT OFAIRPLANES WITHBOUNDARY-LAYER CONTROL, W. Kruger, September1947 The results of calculations and measurementswith respect to the power requirement of airplanes with Boundary Layer Control (BLC) are given. For this investigation the structurally possible arrangements were: I, Suction in the landing-flap region, blowing in the aileron region.

II.

Blowing over the entire span.

III.

Suction over the entire span.

Arrangement I is superior to the other types of construction. In general, one may for all types of construction, assume that the feeding-capacity coefficient required for a certain CL plays the main part for the power requirement and the pressure loss, re- spectively, whereas the pressure coefficient which covers only the difference of the static pressures at the suction and blowing point is of lesser importance. For all three cases, it is very important for obtaining small feed powers to make the narrowest cross section of the feed apparatus (blower or jet apparatus) as large as possible since the kinetic energy of the flow at this location is lost to a great part. The construction Type I offers the great advantage that the entire arrangement (feed apparatus and air ducts) is installed behind the rear spar of the wing struc- ture whereas for the Type II spar perforations are necessary and for Type IIIa part of the loading space in the fuselage is lost to flow ducts.

SYSTEMATIC INVESTIGATIONS OF THE EFFECTS OF PLAN FORM AND GAP TM 1206 BETWEEN THE FIXED SURFACE AND CONTROL SURFACE ON SIMPLE FLAPPED WINGS, Gothert and Rober, May 1949 Four-component measurements of 12 wings of symmetric profile having flaps with chord ratios tR/t L = 0.2 and 0.3 are treated in this report. As a result of the investigation, the effects of plan form and gap between a fixed surface and a control surface have been clarified. Lift, drag, pitching moment, and hinge moment were measured in the control-surface deflection range of -23 ° to 23 ° and the angle of attack range of -20 ° to 20 ° .

tR/t L is the control-surface chord divided by the total tail- plane chord. Six wings with flaps of small chord (tR/t L less than 0.i) were investigated at large flap settings. The following were investigated: i. Effect of the slot width between fixed surface and control surface for two chord ratios.

2. Effect of the plan form for two chord ratios.

3. Rectangular wing with flaps of small chord at high flap angles.

It was found that with increasing slot width the control-surface effectiveness and also the change in pitching momentwith control- surface angle becomeconsiderably lower. With change of plan form, it is observed that the control-surface effectiveness (a_/aB) and (_c /_ °) decrease considerably the more the plan form departs from L o the rectangular; the lift gradiant ($_ /ac ) is likewise worsened.

a As a result of large settings of flaps of small chord, there is an improvement in (a_O/aca) in the sense of a larger aspect ratio; the increase can amount to 25 percent.

Not Applicable NACA Technical Memoranda TM 921 CONTRIBUTION TO THE AERODYNAMICS OF ROTATING-WING AIRCRAFT, G. Sissingh, December 1939 TM 922 THE BREDA WIND TUNNEL, Mario Pittoni, March 1939 TM 926 DFS DIVE-CONTROL BRAKES FOR GLIDERS AND AIRPLANES, Hans Jacobs and Adolf Wanner, January 1940 TM 929 AERODYNAMICS OF ROTATING-WING AIRCRAFT WITH BLADE-PITCH CONTROL, A. Pfluger, February 1940 THEORETICAL AND EXPERIMENTAL INVESTIGATIONS OF THE DRAG OF IN- TM 932 STALLED AIRCRAFT RADIATORS, W. Barth, February 1940 APPLICATION OF THE METHODS OF GAS DYNAMICS TO WATER FLOWS WITH TM 934 FREE SURFACE. PART I - FLOWS WITH NO ENERGY DISSIPATION, Ernst Preiswerk, March 1940 TM 935 APPLICATION OF THE METHODS OF GAS DYNAMICS TO WATER FLOWS WITH FREE SURFACE. PART II - FLOWS WITH MOMENTUM DISCONTINUITIES (HYDRAULIC JUMPS), Ernst Preiswerk, March 1940 TM 942 ON THE THEORY OF UNSTEADY PLANING AND THE MOTION OF A WING WITH VORTEX SEPARATION, L. Sedov, May 1940 TM 946 EXPERIMENTAL RESULTS WITH AIRFOILS TESTED IN THE HIGH-SPEED TUNNEL AT GUIDONIA, Antonio Ferri, July 1940 TM 951 VARIATION IN VELOCITY _ PROFILE WITH CHANGE IN SURFACE ROUGHNESS OF BOUNDARY, W. Jacobs, September 1940 TM 956 CORRECTIONS ON THE THERMOMETER READING IN AN AIR STREAM, H. J.

Van der Maas and S. Wynla, October 1940 TM 958 GENERAL RELATIONSHIPS BETWEEN THE VARIOUS SYSTEMS OF REFERENCE AXES EMPLOYED IN FLIGHT MECHANICS, H. J. Rautenberg, November TM 959 NOTE ON THE CALCULATION OF BOUNDARY LAYERS, L. Prandtl, November TM 961 FLOW AROUND WINGS ACCOMPANIED BY SEPARATION OF VORTICES, C.

Schmieden, December 1940 TM 962 RECENT WORK ON AIRFOIL THEORY, L. Prandtl, December 1940 TM 967 STAGNATION TEMPERATURE RECORDING, W. Wimmer,January 1941 TM 968 ONTHECALCULATION OF FLOW PASTAN INFINITE SCREEN OF THINAIRFOILS, E. Pistolesi, February 1941 TM 969 EXPERIENCES WITHFLOW-DIRECTION INSTRUMENTS, B. Eckert, March 1941 TM 971 THEELLIPTICWING BASED ONTHEPOTENTIAL THEORY, Klaus Kriennes, March 1941 TM 979 GENERAL AIRFOIL THEORY, H. G. Kussner, June 1941 TM 980 AIR TRANSPORT BY GLIDERS SOME TECHNICAL OBSERVATIONS, W. Stepniewski June 1941 TM 983 TEMPERATURE RECORDING IN HIGH-SPEED GASES, E. Eckert, August 1941 TM 990 CONTRIBUTION TO THEAERODYNAMICS OF ROTATING-WING AIRCRAFT PART II, G. Sissingh, October 1941 TM 991 THEOSCILLATING WING WITHAERODYNAMICALLY BALANCED ELEVATOR, H. G. Kussner and L. Schwarz, October 1941 TM 996 TWO-DIMENSIONAL POTENTIAL FLOW PASTA SMOOTH WALL WITHPARTLY CON- STANT CURVATURE, W. von Koppenfels, November1941 TM 998 INERTIAOFDYNAMIC PRESSURE ARRAYS, Hans Wiedemann,December1941 TM i000 THETEMPERATURE OF UNHEATED BODIES IN A HIGH-SPEED GASSTREAM, E. Eckert and W. Wiese, December1941 TM 1003 THERESISTANCE COEFFICIENT OF COMMERCIAL ROUND WIREGRIDS,B.

Eckert and F. Pfluger, January 1942 TM 1006 ELECTRICAL EQUIPMENT FORTHEEXPERIMENTAL STUDY OFTHEDYNAMICS OF FLUIDS, C. Ferrari, March 1942 TM 1007 NEW METHOD OF EXTRAPOLATION OF THERESISTANCE OF A MODEL PLANING BOAT TO FULLSIZE, W. Sottorf, March 1942 TM 1008 CORRELATION OF DATA ONTHESTATISTICAL THEORY OF TURBULENCE, K. Wieghardt, March 1942 TM 1009 THEORETICAL SOLUTION OF PROFILE DRAG,J. Pretsch, April 1942 TM i011 PRESSURE DISTRIBUTION ONWINGS IN REVERSED FLOW,A. Naumann, April 1942 TM 1013 RECORDING RAPIDLY CHANGING CYLINDER-WALL TEMPERATURES, A. Meier, May 1942 1017 THE STABILITY OF LAMINAR FLOW PAST A SPHERE D J. Pretsch_ June ON THE SYMMETRICAL POTENTIAL FLOW OF COMPRESSIBLE FLUID PAST A TM 1018 CIRCULAR CYLINDER IN THE TUNNEL IN THE SUBCRITICAL ZONE, E.

Lamla, June 1942 TM 1021 PREDICTION OF DOWNWASH AND DYNAMIC PRESSURE AT THE TAIL FROM FREE- FLIGHT MEASUREMENTS_ E. EuJen, July 1942 TM 1022 DIAGRAMS FOR CALCULATION OF AIRFOIL LATTICESp A. Betz, July 1942 TM 1023 TWO-DIMENSIONAL POTENTIAL FLOW PAST AN ORDINARY THICK WING PRO- FILE, F. Keuhe, July 1942 TM 1029 THE NAVIER-STOKES STRESS PRINCIPLE FOR VISCOUS FLUIDS, E. Mohr, September 1942 1030 THE COMPRESSIBLE POTENTIAL FLOW PAST ELLIPTIC SYMMETRICAL CYLINDERS TM AT ZERO ANGLE OF ATTACK AND WITH NO CIRCULATION, W. Hantzsche and H. Wendt, October 1942 HEAT TRANSFER IN THE TURBULENT BOUNDARY LAYER OF A COMPRESSIBLE TM 1032 GAS AT HIGH SPEEDS AND FRICTION IN THE TURBULENT BOUNDARY LAYER OF A COMPRESSIBLE GAS AT HIGH SPEEDS, F. Frankl and V. Voishel, October 1942 TM 1033 WIND-TUNNEL INVESTIGATIONS OF DIVING BRAKES, D. Fuchs, November TM 1036 AERODYNAMICS OF THE FUSELAGE, H. Multhopp, December 1942 TM 1039 PRESSURE DISTRIBUTION IN NONUNIFORM TWO-DIMENSIONAL FLOW, M.

Schwabe, January 1943 TM 1044 HEAT TRANSFER OF AIRFOILS AND PLATES, O. Siebert, April 1943 TM 1045 THE HEAT TRANSFER TO A PLATE IN FLOW AT HIGH SPEED, E. Eckert and O. Drewitz, May 1943 TM 1047 HEAT TRANSFER THROUGH TURBULENT FRICTION LAYERS, H. Reichardt, September 1943 TM 1048 PERIODIC HEAT TRANSFER AT SMALL PRESSURE FLUCTUATIONS, Pfriem, September 1943 TM 1050 HEAT TRANSFER OVER THE CIRCUMFERENCE ON A HEATED CYLINDER IN TRANSVERSE FLOW, E. Schmidt and K. Wenner, October 1943 TM 1053 TURBULENT FRICTION IN THEBOUNDARY LAYER OFA FLATPLATEIN A TWO-DIMENSIONAL COMPRESSIBLE FLOW AT HIGHSPEEDS, F. Frankl and V. Voishel, December1943 TM 1054 HEATTRANSFER ANDHYDRAULIC FLOW RESISTANCE FORSTREAMS OFHIGH VELOCITY, V. L. Lelchuk, December1943 TM 1058 THETHEORY OFA FREEJET OFA COMPRESSIBLE GAS,G. N. Abramovich, March 1944 TM 1060 PROFILE MEASUREMENTS DURING CAVITATION, O. Walchner, January 1944 TM 1061 ANALYSIS OF EXPERIMENTAL INVESTIGATIONS OF THEPLANING PROCESS ON THESURFACE OFWATER, W. Sattorf, March 1944 TM 1065 DVLANGULAR VELOCITY RECORDER, W. Liebe, August 1944 TM 1068 HEAT TRANSFER IN A TURBULENT LIQUID ORGASSTREAM, H. Latzko, October 1944 TM 1070 INTEGRAL METHODS IN THETHEORY OF THEBOUNDARY LAYER,L. G.

Loitsianskii, July 1944 TM 1071 DETERMINATION OF THEACTUAL CONTACT SURFACE OF A BRUSH CONTACT, R. Holm, August 1944 TM 1075 THEWALL INTERFERENCE OFA WINDTUNNEL OF ELLIPTICCROSS SECTION, I. Tani and M. Sanuki, November1944 NEW METHOD OF DETERMINING THEPOLAR CURVE OFAN AIRPLANE IN TM 1076 FLIGHT, B. N. Yegorov, March 1945 TM 1078 EXPERIMENTAL ANDTHEORETICAL INVESTIGATIONS OF CAVITATION IN WATER, J. Ackeret, May 1945 TM 1079 SOME BASICLAWS OF ISOTROPIC TURBULENT FLOW,L. G. Loitsianskii, September 1945 TM 1085 CALCULATION OF TURBULENT EXPENSION PROCESSES, W. Tollmeln, September 1945 TM 1092 ONLAMINAR ANDTURBULENT FRICTION,T. von Karman, September1946 TM 1096 INVESTIGATION OF TURBULENT MIXINGPROCESSES, K. Viktorin, October TM 1098 THEOSCILLATING CIRCULAR AIRFOIL ONTHEBASISOFPOTENTIAL THEORY, T. Schadeand K. Krienes, February 1947 _M ii00 INFINITESIMAL CONICAL SUPERSONIC FLOW, A. Busemann,March 1947 INVESTIGATIONS OF PRESSURE DISTRIBUTION ONFASTFLYINGBODIES, FM ii01 G. Stamm,September 1946 TM 1102 HIGH-SPEED MEASUREMENTS ONA SWEPT-BACK WING,B. Gothert, March TM 1103 CALIBRATION TUNNEL FORHIGHSPEED, J. Pretsch, October 1946 TM 1104 THEINFLUENCE OFTHEJET OF A PROPULSION UNIT ONNEARBY WINGS, H. Falk, September 1946 TM 1105 PLANE ANDTHREE-DIMENSIONAL FLOW AT HIGHSUBSONIC SPEEDS, B.

Gothert, October 1946 SIX-COMPONENT MEASUREMENTS ONA STRAIGHT ANDA 35 ° SWEPT-BACK TM 1107 TRAPEXOIDAL WING WITH AND WITHOUT SPLIT FLAPS, G. Thiel and F. Weissinger, June 1947 TM 1109 FLOW INVESTIGATION WITH THE AID OF THE ULTRAMICROSCOPE, G.

Vogelpohl and D. Mannesmann, October 1946 TM iiii THE MONOPLANE AS A LIFTING VORTEX SURFACE, H. Blenk, February TM 1113 INVESTIGATIONS OF COMPRESSION SHOCKS AND BOUNDARY LAYERS IN GASES MOVING AT HIGH SPEED, J. Ackeret, F. Feldman, and N.

Rott, January 1947 TM 1114 THE CALCULATION OF COMPRESSIBLE FLOWS WITH LOCAL REGIONS OF SUPERSONIC VELOCITY, B. Gothert and K. H. Kawalki, March 1947 TM 1115 PRESSURE DISTRIBUTION MEASUREMENTS AT HIGH SPEED AND OBLIQUE INCIDENCE OF FLOW, A. Lippisch and W. Beuschausen, March 1947 TM 1119 SYSTEMATIC WIND-TUNNEL MEASUREMENTS ON A LAMINAR WING WITH NOSE FLAP, W. Krueger, April 1947 TM 1120 THE LIFT DISTRIBUTION OF SWEPT-BACK WINGS, J. Weissinger, Malch THEORETICAL INVESTIGATION OF DRAG REDUCTION IN MAINTAINING THE TM 1121 LAMINAR BOUNDARY LAYER BY SUCTION, A. Ulrich, June 1947 TM 1122 SYSTEMATIC WIND-TUNNEL MEASUREMENTS ON MISSILES, O. Walchner, March 1947 TM 1130 CALIBRATION AND MEASUREMENT IN TURBULENCE RESEARCH BY THE HOT-WIRE METHOD, L. Kovasznay, June 1947 TM 1133 METHOD OFCHARACTERISTICS FORTHREE-DIMENSIONAL AXIALLYSYMMETRICAl SUPERSONIC FLOWS, R. Sauer, January 1947 TM 1139 PLANING OF WATERCRAFT, H. Wagner, April 1948 TM 1140 PRESSURE RECOVERY FORMISSILESWITHREACTION PROPULSION AT HIGH SUPERSONIC SPEEDS (THEEFFICIENCY OF SHOCK DIFFUSERS), K.

Oswatitsch, June 1947 TM 1148 LIFT INCREASE BYBLOWING OUTAIR, TESTS ONAIRFOIL OF 12 PERCENT THICKNESS, USINGVARIOUS TYPES OFFLAP, W. Schwier, June 1947 TM 1150 COMPRESSION SHOCKS OF DETACHED FLOW, Eggink, June 1947 TM 1151 LIFT ANDDRAG OF WINGS WITHSMALL SPAN,F. Weinig, August 1947 TM 1152 THESEPARATION OF FLOW DUETO COMPRESSIBILITY SHOCK, A. Weise, July 1947 TM 1154 THEORY OFWINGS IN NONSTATIONARY FLOW, A. I. Nekrasov, June 1947 TM 1155 ONTHEPROBLEMS OF CHAPLYGIN FORMIXEDSUB-ANDSUPERSONIC FLOWS, F. Frankl, June 1947 TM 1156 ONTHETHEORY OF THEUNSTEADY MOTION OF ANAIRFOIL, L. I. Sedov, July 1947 TM 1157 CONES IN SUPERSONIC FLOW, W. Hantzsche and H. Wendt, August 1947 TM 1158 SOME AERODYNAMIC RELATIONS FORANAIRFOIL IN OBLIQUE FLOW, F.

Ringleb, June 1947 TM 1159 WIND-TUNNEL MEASUREMENTS ONTHEHENSCHEL MISSILE "ZITTERROCHEN" IN SUBSONIC ANDSUPERSONIC VELOCITIES ANDWIND-TUNNEL MEASUREMENTS ONTHEWING OF THEHENSCHEL MISSILE" ZITTERROCHEN" IN SUBSONIC ANDSUPERSONIC VELOCITIES,Weberand Kehl, April 1948 TM 1160 CONCERNING THEVELOCITY OF EVAPORATION OF SMALL DROPLETS IN GAS ATMOSPHERE, N. Fuchs, August 1947 TM 1161 WIND-TUNNEL TESTS ONVARIOUS TYPES OF DIVE BRAKES MOUNTED IN PROXIMITY OF THELEADING EDGE OF THEWING,B. Lattanzi and E. Bellante, May 1949 TM 1162 TUNNEL CORRECTION FORCOMPRESSIBLE SUBSONIC FLOW, A. V. Baranoff, July 1947 TM 1163 DRAG CORRECTION IN HIGH-SPEED WINDTUNNELS, H. Ludwieg, July 1947 TM 1168 DRAG REDUCTION BY SUCTION OF THE BOUNDARY LAYER SEPARATED BEHIND SHOCK WAVE FORMATION AT HIGH MACH NUMBERS, B. Regenscheit, July TM 1174 ANALYTICAL TREATMENT OF NORMAL CONDENSATION SHOCK, Heybey, July 1947 TM 1175 FUNDAMENTAL AERODYNAMIC INVESTIGATIONS FOR DEVELOPMENT OF ARROW- STABILIZED PROJECTILES, H. Kurzweg, December 1947 TM 1176 TEST REPORT ON THREE AND SIX-COMPONENT MEASUREMENTS ON A SERIES OF TAPERED WINGS OF SMALL ASPECT RATIO (PARTIAL REPORT: TRIANGU- LAR WING), Lange/Wacke, May 1948 TM 1178 INVESTIGATION OF THE OPERATING PROPERTIES OF THE LEAKAGE CURRENT ANEMOMETER, W. Fucks, October 1947 TM 1180 MAINTAINING LAMINAR FLOW IN THE BOUNDARY LAYER USING A SWEPT-BACK WING, Brennecke, February 1948 TM 1181 INVESTIGATIONS ON REDUCTIONS OF FRICTION ON WINGS, IN PARTICULAR BY MEANS OF BOUNDARY LAYER SUCTION, W. Pfenninger, August 1947 TM 1184 DEVELOPMENT AND CONSTRUCTION OF AN INTERFEROMETER FOR OPTICAL MEASUREMENTS OF DENSITY FIELDS, T. Zobel, September 1947 TM 1185 SYSTEMATIC INVESTIGATIONS OF THE INFLUENCE OF THE SHAPE OF THE PROFILE UPON THE POSITION OF THE TRANSITION POINT, K. Bussmann and A. Ulrich, October 1947 TM 1186 COMPARISON OF DROP AND WIND-TUNNEL EXPERIMENTS ON BOMB DRAG AT HIGH SUBSONIC SPEEDS, B. Gothert, May 1948 TM 1187 EQUATIONS FOR ADIABATIC BUT ROTATIONAL STEADY GAS FLOWS WITHOUT FRICTION, M. Schafer, August 1947 TM 1189 THEORETICAL ANALYSIS OF STATIONARY POTENTIAL FLOWS AND BOUNDARY LAYERS AT HIGH SPEED, K. Oswatitsch and K. Wieghardt, April 1948 TM 1191 VENTURI TUBE WITH VARYING MASS FLOW, B. Regenscheit, March 1948 TM 1199 COMPRESSION SHOCKS IN TWO-DIMENSIONAL GAS FLOWS, A. Busemann, February 1949 TM 1203 THE COMPRESSIBLE FLOW PAST VARIOUS PLANE PROFILES NEAR SONIC VELOCITY, B. Gothert and K. H. Kawalki, March 1949 TM 1205 EXACT CALCULATION OF LAMINAR BOUNDARY LAYER IN LONGITUDINAL FLOW OVER A FLAT PLATE WITH HOMOGENEOUS SUCTION, R. Iglisch, April 1949 TM 1211 THECHARACTERISTICS METHOD APPLIED TO STATIONARY TWO-DIMENSIONAL ANDROTATIONALLY SYMMETRICAL GASFLOWS, F. Pfeiffer and W. Meyer- Konig, March 1949 TM 1213 GAS MOTION IN A LOCAL SUPERSONIC REGION ANDCONDITIONS OF POTEN- TIAL FLOW BREAKDOWN, A. A. Nikolskii and G. I. Tagenov, May 1949 TM 1216 AN APPROXIMATE METHOD FORCALCULATION OF THELAMINAR BOUNDARY LAYER WITHSUCTION FORBODIES OFARBITRARY SHAPE, H. Schlichting, March 1949 TM 1217 LECTURE SERIES"BOUNDARY LAYER THEORY". PARTI - LAMINAR FLOWS, H. Schlichting, April 1949 TM 1218 LECTURES SERIES"BOUNDARY LAYER THEORY". PARTII - TURBULENT FLOWS, H. Schlichting, April 1949 TM 1223 SOME EXPERIENCES REGARDING THENONLINEARITY OF HOTWIRES,R.

Betchov and W. Welling, June 1952 TM 1224 LAME'SWAVE FUNCTIONS OF THEELLIPSOID OF REVOLUTION, J. Meixner, April 1949 TM 1225 TESTREPORT ONTHREE- ANDSIX-COMPONENT MEASUREMENTS ONA SERIES OFTAPERED WINGS OF SMALL ASPECT RATIO(PARTIAL REPORT:TRAP- EZOIDAL WIND), Lange/Wacke, May 1949 TM 1227 MOMENTS OF CAMBERED ROUND BODIES,G. Kempf, August 1949 BEHAVIOR OF THELAMINAR BOUNDARY LAYER FORPERIODICALLY OSCILLAT- TM 1228 ING PRESSURE VARIATION, August Wilhelm Quick and K. Schroder, September 1949 TM 1229 HEATTRANSMISSION IN THEBOUNDARY LAYER,L. E. Kalikhman, April TM 1230 EFFECT OF THEACCELERATION OF ELONGATED BODIES OF REVOLUTION UPON THERESISTANCE IN A COMPRESSIBLE FLOW, F. I. Frankl, May 1949 TM 1231 REPORT ONINVESTIGATION OF DEVELOPED TURBULENCE, L. Prandt, September 1949 TM 1232 FLIGHTEXPERIENCES ANDTESTS ONTWO AIRPLANES WITHSUCTION SLOTS, Stuper, January 1950 TM 1233 CONTRIBUTION TO THEPROBLEM OF FLOW AT HIGHSPEED, C. Schmieden and K. H. Kawalki, June 1949 TM 1238 TWO-DIMENSIONAL WING THEORY IN THESUPERSONIC RANGE, H. Honl, June 1949 TM 1239 TWO-DIMENSIONAL MOTION OF A GASAT LARGE SUPERSONIC VELOCITIES, S. V. Falkovich, October 1949 TM 1240 AIRFOILMEASUREMENTS IN THEDVLHIGH-SPEED WIND TUNNEL (2.7 - METER DIAMETER), B. Gothert, June 1949 TM 1243 TWO-DIMENSIONAL POTENTIAL FLOWS, M. Schafer and W. Tollmien, November1949 TM 1244 ROTATIONALLY SYMMETRIC POTENTIAL FLOWS, M. Schafer and W. Tollmien, November1949 TM 1245 LIFT FORCE OFAN ARROW-SHAPED WING,M. I. Gurevich, October 1949 TM 1246 HYDRODYNAMIC PROPERTIES OF PLANING SURFACES ANDFLYINGBOATS, N. A. Sokolov, October 1950 TM 1250 SUBSONIC GASFLOW PASTA WING PROFILE,S. A. Christianovich and I. M. Yariev, July 1950 TM 1251 ONTHEFORMATION OF SHOCK WAVES IN SUBSONIC FLOWS WITHLOCAL SUPERSONIC VELOCITIES,F. I. Frankl, April 1950 TM 1252 SOME STUDIES OF THEFLOW OF A GASIN THEREGION OF TRANSITION THROUGH THEVELOCITY OF SOUND, I. A. Kiebel, April 1950 TM 1253 FLOW MEASUREMENTS BY MEANS OF LIGHTINTERFERENCE, T. Zobel, August 1949 TM 1255 EQUATIONS OFMOTION OF A ROCKET, F. B. Gantmacherand L. M.

Levin, April 1950 TM 1256 THEBOUNDARY LAYERS IN FLUIDSWITHLITTLE FRICTION,H. Blasias, February 1950 TM 1260 EXACT SOLUTIONS OF EQUATIONS OF GASDYNAMICS, I. A. Kiebel, June TM 1262 TURBULENCE ANDHEATSTRATIFICATION, H. Schlichting, October 1950 TM 1265 AMPLITUDE DISTRIBUTION ANDENERGY BALANCE OF SMALL DISTRUBANCES IN PLATEFLOW,H. Schlichting, April 1950 TM 1268 ISENTROPIC PHASE CHANGES IN DISSOCIATING GASES ANDTHEMETHOD OF SOUND DISPERSION FORTHEINVESTIGATION OF HOMOGENEOUS GASREAC- TIONSWITHVERY HIGHSPEED, G. Damkohler, September1950 TM 1269 ISENTROPIC PHASE CHANGES IN DISSOCIATING GASES ANDTHEMETHOD OF SOUND DISPERSION FORTHEINVESTIGATION OF HOMOGENEOUS GASREAC- TIONSWITHVERY HIGHSPEED, G. Damkohler, September 1950 TM 1270 THE GAS KINETICS OF VERY HIGH FLIGHT SPEEDS, E. Sanger, May 1950 TM 1272 CRITICAL VELOCITIES OF ULTRACENTRIFUGES, V. I. Sokolov, March 1951 TM 1275 THE SOLUTION OF THE LAMINAR-BOUNDARY-LAYER EQUATION FOR THE FLAT PLATE FOR VELOCITY AND TEMPERATURE FIELDS FOR VARIABLE PHYSICAL PROPERTIES AND FOR THE DIFFUSION FIELD AT HIGH CONCENTRATION, H.

Schuh, May 1950 TM 1276 SIDESLIP IN A VISCOUS COMPRESSIBLE GAS, V. V. Struminsky, April TM 1277 PRESENT STATE OF DEVELOPMENT IN NONSTEADY MOTION OF A LIFTING SURFACE, P. Cicala, October 1951 TM 1278 GENERAL SOLUTION OF PRANDTL'S BOUNDARY-LAYER EQUATION, W. Mangler, June 1950 TM 1280 GRAPHICAL DETERMINATION OF WALL TEMPERATURES FOR HEAT TRANSFERS THORUGH WALLS OF ARBITRARY SHAPE, O. Lutz, April 1950 UNSTABLE CAPILLARY WAVES ON SURFACE OF SEPARATION OF TWO VISCOUS TM 1281 FLUIDS, V. Ao Borodin and Y. F. Dityakin, April 1951 TM 1283 RESISTANCE OF A DELTA WING IN A SUPERSONIC FLOW, E. A. Karpovich and F. I. Frankl, April 1951 TM 1284 INSTRUMENT FOR MEASURING THE WALL SHEARING STRESS OF TURBULENT BOUNDARY LAYERS, H. Ludwieg, May 1950 INVESTIGATIONS OF THE WALL-SHEARING STRESS IN TURBULENT BOUNDARY TM 1285 LAYERS, H. Ludwieg and W. Tillman, May 1950 TM 1286 METHOD OF SUCCESSIVE APPROXIMATIONS FOR THE SOLUTION OF CERTAIN PROBLEMS IN AERODYNAMICS, M. E. Shvets, April 1951 TM 1288 THE DIFFUSION OF A HOT AIR JET IN AIR IN MOTION, W. Szablewski, December 1950 TM 1291 ON STABILITY AND TURBULENCE OF FLUID FLOWS, W. Heisenberg, June APPROXIMATE METHOD OF INTEGRATION OF LAMINAR BOUNDARY LAYER IN TM 1293 INCOMPRESSIBLE FLUID, L. G. Loitsianskii, July 1951 TM 1295 GAS FLOW WITH STRAIGHT TRANSITION LINE, L. V. Ovsiannikov, May ADDITIONAL MEASUREMENTS OF THE DRAG OF SURFACE IRREGULARITIES IN TM 1299 TURBULENT BOUNDARY LAYERS, W. Tillman, January 1951 WIND-TUNNEL CORRECTIONS AT HIGHSUBSONIC SPEEDS PARTICULARLY FOR TM 1300 AN ENCLOSED CIRCULAR TUNNEL, B. Gothert, February 1952 Applicable NASA Technical Translations There were no applicable aerodynamics reports in the NASA Technical Translation series.

Not Applicable NASA Technical Translations ON THE TEMPERATURE DISTRIBUTION BEHIND CYLINDERS IN A FLOW, TT F Jakob Ackeret, August 1959 PIECEMEAL SOLUTIONS IN THE PROGRAMMING OF OPTIMAL FLIGHT TRA- TT F JECTORIES, Placido Cicala, October 1959 TT F OPTIMUM AIRPLANE FLIGHT PATHS, Placido Cicala, October 1959 TT F THE AIRPLANE AS AN OBJECT OF CONTROL. (BLOCK DIAGRAMS OF THE EQUATIONS OF PERTURBED AIRPLANE MOTION.), V. S. Vedrov, G. L.

Romanov, and V. N. Surina, October 1959 TT F THE THEORY OF MOMENTLESS SHELLS OF REVOLUTION, V. Z. Vlasov, April 1960 TT F SOME RESULTS OF THE MEASUREMENTS OF THE SPECTRUM MASS OF POSI- TIVE IONS BY THE 3RD ARTIFICIAL EARTH SATELLITE, V. G. Istomin, April 1960 TT F "ARTIFICIAL EARTH SATELLITES" NO 3, 1959_ April 1960 TT F THE CAPTURE PROBLEM IN THE THREE-BODY RESTRICTED ORBITAL PROBLEM, V. A. Yegorov, April 1960 TT F i0 THE LIBRATION OF A SATELLITE, V. V. Beletskiy, May 1960 TT F ii OPTICAL OBSERVATION OF ARTIFICIAL EARTH SATELLITES, February 1961 TT F 12 INTERNATIONAL GEOPHYSICAL YEAR BIBLIOGRAPHY OF LITERATURE IN THE RUSSIAN LANGUAGE FOR 1958, R. F. Zatrutina and Z. M. Mikhaylova, May 1960 TT F 13 SOME RESULTS OF THE DETERMINATION OF THE STRUCTURAL PARAMETERS OF THE ATMOSPHERE USING THE THIRD SOVIET ARTIFICIAL EARTH SATEL- LITE, V. V. Mikhnevich, B. S. Danilin, A. I. Repnev, and V. A.

Sokolov, May 1960 TT F 14 THE MANOMETER ERROR CAUSED BY SMALL LEAKS IN THE CASING OF A SATELLITE, S. A. Kuchay, April 1960 TT F 15 THE DETERMINATION OF THE DENSITY OF THE ATMOSPHERE AT AN ALTITUDE OF 430 KILOMETERS BY THE SODIUM VAPOR DIFFUSION METHOD, I. S.

Shklovskiy and V. G. Kurt, April 1960 TT F 16 METHODS FOR THE CONTROL OF INTERFERING CURRENTS ORIGINATING AT THE INPUT OF AN ELECTROSTATIC FLUXMETER DURING ITS OPERATION IN A CONDUCTING MEDIUM, I. M. Imyanitov and Ya. M. Shvarts, May 1960 TT F 19 BULLETIN OF STATIONS FOROPTICAL OBSERVATIONS OF ARTIFICIAL EARTH SATELLITES, May 1960 TT F 20 DRIFTSANDIRREGULARITIES IN THEIONOSPHERE, S. F. Mirkotan, A. D.

Podol'skiy, and V. V. Bruzgul', June 1960 TT F 22 AN APPROXIMATION METHOD FORTHEINTEGRATION OF THEEQUATIONS OF A NONSTATIONARY LAMINAR BOUNDARY LAYER IN AN INCOMPRESSIBLE FLUID, L. A. Rozin, May 1960 TT F 23 SURFACE DISTURBANCES IN MAGNETOHYDRODYNAMICS, S. I. Syrovatskiy, May 1960 TT F 26 ONTHERELATION BETWEEN THEGENERATION OF A LIFT FORCE ONA WING ANDTHECHARACTER OF THEFLOW IN THEBOUNDARY LAYER,I. V.

Ostoslavskii and T. A. Grumondz,May 1960 TT F 28 BOUNDARY-LAYER EQUATIONS ANDTHEIRBOUNDARY CONDITIONS IN THE CASE OFMOTION AT SUPERSONIC VELOCITIES IN A MODERATELY RAREFIED GAS,Yu N. Lunkin, May 1960 TT F 29 ONTHECALCULATION OF STEADY BOUNDARY LAYERS FORCONTINUOUS SUC- TION, WITHDISCONTINUOUSLY VARIABLE SUCTION VELOCITY, Werner Rheinboldt, March 1961 TT F "SIMILAR" THREE-DIMENSIONAL BOUNDARY LAYERS, Theo Geis, March 1961 TT F 31 ONTHECOMPUTATION OF THECIRCULATION OF A GLIDINGWING OF LARGE SPAN,N. M. Monakhov, June 1960 TT F SOME PROBLEMS IN FLANGING ANDBEADING MEMBRANES, B. V. Grigoryev, June 1960 TT F 33 THEORY OF THEMOTION OFA BODY WITHCAVITIESPARTLY FILLED WITH LIQUID, D. E. Okhotsimskii, May 1960 TT F 35 EFFECT OF SLIGHTBLUNTING OFLEADING EDGE OFAN IMMERSED BODY ON THEFLOW AROUND IT AT HYPERSONIC SPEEDS, G. G. Chernyi, June 1960 TT F 36 RELATIVISTIC ROCKET MECHANICS, H. G. L. Krause, October 1960 TT F 37 ONTHEPROBLEM OF THEINTERACTION BETWEEN A SATELLITE ANDTHE EARTH'S MAGNETIC FIELD, Yu. V. Zonov, May 1960 TT F 38 AN EXPERIMENTAL DETERMINATION OF THEABSOLUTE OSCILLATOR STRENGTHS OFTHELINES OF TWO NII SUPERMULTIPLETS, Frithjof Mastrup, May TT F 39 DISCOVERY OF ELECTRONS WITHAN ENERGY OF ABOUT I0 KEVIN THEUPPER ATMOSPHERE WITHTHEAID OF THETHIRDEARTH SATELLITE, V. I.

Krasovskiy, I. S. Shklovskiy, Yu. I. Gal'perin and Ye. M.

Svetlitskiy, June 1960 TT F 40 THEPROBLEM OF PIERCING AT COSMIC VELOCITIES,M. A. Lavrent'yev, May 1960 TT F 42 PRESENT-DAY IDEASCONCERNING THEMECHANISM OF ELECTRICAL BREAKDOWN IN HIGHVACUUM, L. V. Tarasova, October 1960 TT F 44 THEATTAINABILITY OF HEAVENLY BODIES,Walter Hohmann,November1960 TT F 45 FIRST-ORDER PERTURBATIONS IN THEMOTION OF EARTH SATELLITES DUETO OBLATENESS OF THEEARTH,V. F. Proskurin and Yu. V. Batrakov, November1960 TT F 46 PERTURBATIONS OF ORBITS OF ARTIFICIAL SATELLITES DUETOAIR RESIST- ANCE,Yu. V. Batrakov and V. F. Proskurin, November1960 TT F 47 DEPENDENCE OF SECULAR VARIATIONS OF ORBITELEMENTS ONTHEAIR RESISTANCE, P. E. Ei'yasberg, November1960 TT F 48 OBSERVATION OFAN ARTIFICIAL SATELLITE BY THEEXPECTATION METHOD, V. M. Vakhnin and V. V. Beletskiy, November1960 TT F 49 MAGNETIC ANDIONOSPHERIC DISTURBANCES, Yu. D. Kalinin, January TT F 50 INTERNATIONAL GEOPHYSICAL YEARINFORMATION BULLETIN,NO. 7, November1960 TT F 51 EXPERIMENTAL ELECTRONIC EQUIPMENT FORMEDICAL TELEMETRY, T. Matsuo, November1960 TT F 53 RADIO-FREQUENCY MASS SPECTROMETER FORTHEINVESTIGATION OF THE IONIC COMPOSITION OF THEUPPER ATMOSPHERE, V. G. Istomin, January TT F 54 CONCERNING A METHOD FORTHEMEASUREMENT OF VERY HIGHTEMPERATURES IN NEARLY TRANSPARENT ARCCOLUMNS, Rudolf Wilhelm Larenz, December TT F 56 THEAUTOIONIZATION EFFECT ANDITS INFLUENCE ONTHEINTENSITY OF CERTAIN STARSPECTRA LINES, A. A. Nikitin, December1960 TT F 57 GEOPHYSICAL RESEARCH WITHTHEAID OFROCKETS ANDARTIFICIAL SATEL- LITES, A. A. Blagonravov and M. G. Kroshkin, February 1961 COMMUNICATION CONCERNING SCIENTIFIC WORKS IN THE FIELD OF GEOMAG- TT F 60 NETISM AND AERONOMY DURING 1957-1959, March 1961 EFFECT OF PERIODIC OSCILLATIONS OF VELOCITY AND DENSITY OF A TT F 63 MEDIUM ON DISINTERGATION OF LIQUID JETS, I. F. Dityakin and V. I.

Yagodkin, April 1961 TT F 65 MODEL EXPERIMENTS ON ATOMIZATION OF LIQUIDS, Mintscho Popov, July 1961 TT F 66 EXPERIMENTAL DETERMINATION OF POTASSIUM VAPOR PRESSURE IN THE 550 ° TO 1,280 ° C TEMPERATURE RANGE, N. S. Grachev and P. L. Kirilov, July 1961 TT F 67 VARIATIONS OF COSMIC RAY INTENSITY, Yu. G. Shafer, August 1961 TT F 68 RADAR OBSERVATIONS OF METEORS ACCORDING TO THE INTERNATIONAL GEOPHYSICAL YEAR PROGRAM, B. L. Kashcheyev, August 1961 TT F 69 MAGNESIUM AND CALCIUM IONS IN THE EARTH'S UPPER ATMOSPHERE, V. G.

Istomin, September 1961 TT F 70 AERODYNAMIC EFFECTS OF METEORITIES. A SPECIFIC CASE, K. P.

Stanyukovich, August 1961 THE LAMINAR BOUNDARY LAYER AT HYPERSONIC SPEEDS, Carlo Ferrari, TT F 71 September 1961 SOLAR RADIO PHENOMENA AND THEIR PHYSICAL INTERPRETATION, J. F.

TT F 72 Denisse, September 1961 TT F 73 ELECTRON AND ION EMISSION, L. N. Dobretsov, November 1963 TT F 74 PAPERS ON ANALYSIS OF ORBITS, Yu. V. Batrakov, March 1962 SELECTED ARTICLES ON LIGHT SCATTERING AND PHOTOMETRIC RELIEF OF TT F 75 THE LUNAR SURFACE, N. S. Orlova, September 1962 TT F 76 SPECTRAL, ELECTROPHOTOMETRICAL AND RADAR RESEARCHES OF AURORAE AND AIRGLOW, V. I. Karsovskiy, April 1962 TT F 78 THE NATURE OF THE PLANETS, V. V. Sharonov, April 1963 TT F 80 PHYSICAL CHARACTERISTICS OF COMETS, S. K. Vsekhsvyatskii, 1964 TT F 83 THE NIGHT LAYER E ACCORDING TO OBSERVATIONS AT THE OBSERVATORY ON DIKSON ISLAND, Ya. I. Fel'dshteyn, March 1962 TT F 84 SELECTED PAPERS ON NOCTILUCENT CLOUDS, V. A. Bronshten, November Applicable NASA Technical Memorandum There were no applicable aerodynamics reports in the NASA X series of Technical Memorandum.

Not Applicable NASA Technical Memoranda AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS FROM 1.6 TO 2.8 OF TMX 74 ° SWEPT ARROW WINGS WITH AND WITHOUT CAMBER AND TWIST, Dennis F. Hasson, Ann B. Fichter, and Norman Wong, September 1959 INVESTIGATION OF 0.05-SCALE MODEL OF XSM-64A NAVAHO MISSILE AND TM X 16 BOOSTER AT SUPERSONIC MACH NUMBERS: PT. i, FORCE STUDY, James D. Church and Nancy L. Taylor, September 1959 INVESTIGATION OF 0.05-SCALE MODEL OF XSM-64A NAVAHO MISSILE AND TM X 17 BOOSTER AT SUPERSONIC MACH NUMBERS: PT. 2, PRESSURE STUDY, James D. Church and Nancy L. Taylor, September 1959 HEAT-TRANSFER AND PRESSURE MEASUREMENTS ON FLAT-FACE CYLINDER AT TM X 19 MACH NUMBER RANGE OF 2.40 TO 4.4, Paige B. Burbank and Robert L.

Stallings, Jr., August 1959 TM X 22 LIFT, DRAG, AND PITCHING MOMENTS OF AN ARROW WING HAVING 80 ° OF SWEEPBACK AT MACH NUMBERS FROM 2.48 TO 3.51 AND REYNOLDS NUMBERS UP TO ii.0 MILLION, Edward J. Hopkins, Don W. Jillie, and Alan D.

Levin, August 1959 CHARACTERISTICS OF FIVE EJECTOR CONFIGURATIONS AT FREE-STREAM MACH TM X 23 NUMBERS FROM 0 TO 2.0, John L. Klann and Ronald G. Huff, August AERODYNAMIC CHARACTERISTICS OF A 0.0667-SCALE MODEL OF THE NORTH TM X 24 AMERICAN X-15 RESEARCH AIRPLANE AT TRANSONIC SPEEDS, Robert S.

Osborne, September 1959 EFFECTS OF OUTBOARD THICKENED AND BLUNTED LEADING EDGES ON THE TM X 27 WAVE DRAG OF A 45 ° SWEPT-WING AND BODY COMBINATION, George H.

Holdaway, Frank A. Lazzeroni, and Elaine W. Hatfield, August 1959 APPROACH AND LANDING INVESTIGATION AT LIFT-DRAG RATIOS OF 2 TO 4 TM X 31 UTILIZING A STRAIGHT-WING FIGHTER AIRPLANE, Gene J. Matranga and Neil A. Armstrong, August 1959 FLIGHT INVESTIGATION OF THE EFFECT OF DISTRIBUTED ROUGHNESS ON TM X 36 SKIN DRAG OF A FULL-SCALE AIRPLANE, Edwin J. Saltzman, September AN INVESTIGATION OF THE PITCHING-MOMENT CONTRIBUTION OF A HIGH TM X 43 HORIZONTAL TAIL ON AN UNSWEPT-WIND AND BODY COMBINATION AT MACH NUMBERS FROM 0.80 TO 1.40, Garth W. Lippmann, August 1959 EXPERIMENTAL INVESTIGATION OF SEVERAL COPPER AND BERYLLIUM HEMI- TM X 55 SPHERICAL MODELS IN AIR AT STAGNATION TEMPERATURES OF 2,000°F TO 3,600°F, Otto F. Trout, Jr., September 1959 UPWASH CHARACTERISTICS AT SEVERAL STATIONS ON A BLUNTED CONE- YM X 59 FRUSTUM-CYLINDER MODEL AT MACH NUMBERS FROM 1.60 TO 4.65, James D. Church and Joseph W. Cremin, September 1959 62 MODEL INVESTIGATION OF WATER LANDINGS OF WINGED REENTRY CONFIGU- TM X RATION HAVING OUTBOARD FOLDING WING PANELS, William W. Petynia, December 1959 65 STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF SEVERAL WING TM X AND BLUNT-BODY SHAPES APPLICABLE FOR USE AS REENTRY CONFIGURATIONS AT MACH NUMBER OF 6.8 AND ANGLES OF ATTACK UP TO 90 ° , Jim A.

Penland and William O. Armstrong, October 1959 TM X 105 INVESTIGATION AT MACH NUMBERS OF 0.20 TO 3.50 OF A BLENDED DIAMOND WING AND BODY COMBINATION OF SONIC DESIGN BUT WITH LOW WAVE-DRAG INCREASE WITH INCREASING MACH NUMBER, George H. Holdaway, Jack A.

Mellenthin, and Elaine W. Hatfield, October 1959 TM X 106 TRANSONIC STATIC AERODYNAMIC CHARACTERISTICS OF BLUNT CONE-CYLINDER BODY WITH FLARED AFTERBODIES OF VARIOUS ANGLES AND BASE AREAS, Roy M. Wakefield, Earl D. Knecthel, and Stuart I. Treon, December 1959 TM X 115 AERODYNAMIC CHARACTERISTICS AT MACH NUMBER 2.01 OF AN AIRPLANE CON- FIGURATION HAVING A CAMBERED AND TWISTED ARROW WING DESIGNED FOR A MACH NUMBER OF 3.0, Odell A. Morris and A. Warner Robins, September TM X 125 APPROACH AND LANDING INVESTIGATION AT LIFT-DRAG RATIOS OF 3 TO 4 UTILIZING DELTA-WING INTERCEPTOR AIRPLANE, Gene J. Matranga and Joseph A. Menard, October 1959 LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A WING-BODY-TAIL MODEL TM X 130 HAVING A HIGHLY TAPERED, CAMBERED 45 ° SWEPT WING OF ASPECT RATIO 4 AT TRANSONIC SPEEDS, F. E. West, Jr., November 1959 TMX 137 FLIGHT BEHAVIOR OF THE X-2 RESEARCH AIRPLANE TO A MACH NIIMBER OF 3.20 AND A GEOMETRIC ALTITUDE OF 126,200 FEET, Richard E. Day and Donald Reisert, September 1959 TM X 138 EFFECTS OF TWIST AND CAMBER AND THICKNESS ON THE AERODYNAMIC CHARAC- TERISTICS OF A 75 ° SWEPT ARROW WING AT A MACH BRIMBER OF 2.91, James N. Mueller and John E. Grimaud, December 1959 TM X 147 FRICTION AND PRESSURE DRAG OF BOUNDARY-LAYER DIVERTER SYSTEMS AT MACH NUMBER OF 3.0 (WITH LIST OF REFERENCES), Leonard E. Stitt and Bernhard H. Anderson, January 1960 TM X 151 MIXING CHARACTERISTICS DOWNSTREAM OF CORE RECION OF HIGH TEMPERATURE AXISYMMETRIC JETS EXHAUSTING INTO TRANSONIC AND SUPERSONIC STREAMS (WITH LIST OF REFERENCES), Ronald G. Huff and Kaleel L. Abdalla, March 1960 TMX 169 OBSERVATIONS ONFLOWS PASTBLUNT BODIES AT TRANSONIC SPEEDS, Philip E. Everhart and Walter F. Lindsey, June 1960 TMX 172 AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS OF 1.41 AND2.01 OFA SERIES OF CRANKED WINGS RANGING IN ASPECT RATIOFROM 4.00 TO 1.74 IN COMBINATION WITHA BODY,John R. Sevier, Jr., January 1960 TMX 191 HYDRODYNAMIC ANDAERODYNAMIC CHARACTERISTICS OFA MODEL OF A SUPER- SONIC MULTIJET WATER-BASED AIRCRAFT EQUIPPED WITHSUPERCAVITATING HYDROFOILS, Robert E. McKann,Ulysse J. Blanchard, and Albin O.

Pearson, February 1960 TMX 195 LAUNCH, LOW-SPEED, ANDLANDING CHARACTERISTICS DETERMINED FROM THE FIRST FLIGHTOF THENORTH AMERICAN X-15 RESEARCH AIRPLANE, Thomas W. Finch and GeneJ. Matranga, September 1959 TMX 205 AERODYNAMIC CHARACTERISTICS OF A SPOILER-SLOT-DEFLECTOR CONTROL ONA 45 ° SWEPTBACK-WING-FUSELAGE MODEL AT HIGH SUBSONIC SPEEDS, Alexander D. Hammond, January 1960 TMX 207 MEASUREMENTS OBTAINED DURING THE FIRST LANDING OF THE NORTH AMERICAN X-15 RESEARCH AIRPLANE, James M. McKay, October 1959 TMX 208 HEAT TRANSFER TO 36.75 ° SWEPT BLUNT LEADING EDGES IN FREE FLIGHT AT MACH NUMBERS FROM 1.70 TO 2.99 AND FROM 2.50 TO 4.05 ( WITH LIST OF REFERENCES), Robert L. O'Neal, March 1960 THE AERODYNAMIC CHARACTERISTICS OF A BODY IN THE FLOW FIELD NEAR TMX 211 THE TIP OF A CIRCULAR-ARC WING OF RECTANGULAR PLAN FORM AT A MACH NUMBER OF 2.01, John P. Gapcynski, January 1960 TMX 215 EFFECT OF AFTERBODY TERMINAL FAIRINGS ON THE PERFORMANCE OF A PYLON- MOUNTED TURBOJET-NACELLE MODEL, Conrad M. Willis and Charles E.

Mercer, March 1960 TMX 218 INTERFERENCE EFFECTS AT TRANSONIC SPEEDS OF JETS EXHAUSTING FROM THE HULL STEP OF A MODEL OF A LARGE, WATER-BASED AIRPLANE, Beverly Z. Henry, Jr., January 1960 A CONCEPT OF A MANNED SATELLITE REENTRY WHICH IS COMPLETED WITH A TMX 226 GLIDE LANDING, Compiled by Donald C. Cheatham, December 1959 TMX 235 EXPERIMENTAL INVESTIGATION AND CORRELATION OF HEAT REDUCTION TO NONPOROUS SURFACES BEHIND POROUS LEADING EDGE THROUGH WHICH COOLANT IS EJECTED(WITH LIST OF REFERENCES), William G. Witte and Bernard Rashis, March 1960 TMX 246 TRANSONIC AERODYNAMIC CHARACTERISTICS OF A MODEL OF A PROPOSED SIX- ENGINE HULL-TYPE SEAPLANE DESIGNED FOR SUPERSONIC FLIGHT, Dewey E.

Wornom, March 1960 TMX 390 INVESTIGATION AT MACH NUMBERS OF 0.60 TO 3.50 OF BLENDED WING- BODY COMBINATIONS WITH CAMBERED AND TWISTED WINGS WITH DIAMOND, DELTA, AND ARROW PLAN FORMS, George H. Holdaway and Jack A.

Mellenthin, October 1960 TM X 391 HEAT TRANSFER TO BLUNT AXIALLY SYMMETRIC BODIES, John O. Reller, Jr., September 1960 TM X 394 AMES ATMOSPHERE ENTRY SIMULATOR AND ITS APPLICATION TO DETERMINA- TION OF ABLATIVE PROPERTIES OF MATERIALS FOR BALLISTIC MISSILES, Frank M. Hamaker, October 1960 TM X 398 WIND-TUNNEL INVESTIGATION AT SUBSONIC AND LOW SUPERSONIC SPEEDS OF RENETRY VEHICLE WITH RETRACTABLE WINGS, Wil]ard G. Smith, February 1961 TM X 423 STATIC LONGITUDINAL AERODYNAMIC CHARACTERISTICS AT TRANSONIC SPEEDS OF LENTICULAR-SHAPED REENTRY VEHICLE, John P. Mugler, Jr.

and Walter B. Olstad, December 1960 TM X 427 AN INVESTIGATION OF THE INFLUENCE OF BODYSIZE AND INDENTATION ASYMMETRY ON THE EFFECTIVENESS OF BODY INDENTATION IN COMBINATION WITH A CAMBERED WING, James C. Patterson, Jr. and Donald L. Loving, February 1961 TM X 430 PRELIMINARY FULL-SCALE POWER-OFF DRAG OF THE X-15 AIRPLANE FOR MACH NUMBERS FROM 0.7 TO 3.1, Edwin J. Saltzman, December 1960 TM X 440 INVESTIGATION AT SUBSONIC SPEEDS OF LONGITUDINAL AERODYNAMIC CHARACTERISTICS AT ANGLES OF ATTACK FROM -4 ° TO i00 ° OF DELTA- WING REENTRY CONFIGURATIONS HAVING VERTICALLY DISPLACED AND CAMBERED WING-TIP PANELS, Bernard Spencer, Jr., February 1961 TM X 449 EFFECT OF LONGITUDINAL AND LATERAL CONTROL ON AERODYNAMIC CHARAC- TERISTICS OF WINGED REENTRY CONFIGURATION AT MACH NUMBER OF 1.97 AND ANGLES OF ATTACK UP TO APPROXIMATELY 90 °, Gerald V. Foster, February 1963 TM X 467 INVESTIGATION OF NORMAL-FORCE, AXIAL-FORCE AND PITCHING MOMENT CHARACTERISTICS OF BLUNT LOW-FINENESS-RATIO BODIES OF REVOLUTION AT MACH NUMBER OF 3.55, Russel W. McDearmon and Warren A. Lawson, April 1961 TMX 468 SKIN AND STRUCTURAL TEMPERATUES MEASURED ON X-15 AIRPLANE DURING FLIGHT TO MACH NUMBER OF 3.3, Robert D. Reed and Joe D. Watts, January 1961 TM X 507 FREE-FLIGHT MEASUREMENTS OF DRAG AND STATIC STABILITY FOR BLUNT- NOSED i0 ° HALF-ANGLE CONE AT MACH NUMBER 15, Dale L. Compton, April 1961 TMX 249 AERODYNAMIC ANDHYDRODYNAMIC CHARACTERISTICS OF PROPOSED SUPER- SONIC MULTIJET WATER-BASED HULL-TYPE AIRPLANE WITHVARIABLE- INCIDENCE WING( WITHLIST OF REFERENCES), William W. Petynia, Albion O. Pearson and Roger H. Fournier, April 1960 TMX 269 AERODYNAMIC ANDLANDING MEASUREMENTS OBTAINED DURING THEFIRST POWERED FLIGHTOF THENORTH AMERICAN X-15 RESEARCH AIRPLANE, Flight Research Center, January 1960 TMX 271 AERODYNAMIC CHARACTERISTICS OFMODEL OF PROPOSED 6-ENGINE HULL- TYPESEAPLANE AT MACH NUMBERS OF 1.57, 1.87, AND2.16 ( WITHLIST OF REFERENCES), JamesR. Morgan and Ann B. Fichter, April 1960 TMX 273 EFFECTS OF SPOILER-SLOT DEFLECTOR CONTROL ONAERODYNAMIC CHARAC- TERISTICS AT MACH NUMBER OF 2.01 OFVARIABLE-WING-SWEEP CONFIGURA- TIONWITHOUTER WING PANELS SWEPT BACK75° ( WITHLIST OFREFER- ENCES),Gerald V. Foster, April 1960 TMX 283 SUBSONIC FLIGHTTESTS OFA 1/17-SCALERADIO-CONTROLLED MODEL OF THENORTH AMERICAN X-15 AIRPLANE WITHPARTICULAR REFERENCE TO HIGHANGLE-OF-ATTACK CONDITIONS, Donald E. Hewesand JamesL.

Hassell, Jr., June 1960 TMX 292 WIND-TUNNEL INVESTIGATION AT MACH NI_BERS FROM 0.50 TO 1.14 OF STATICAERODYNAMICS CHARACTERISTICS OFMODEL OF PROJECT MERCURY CAPSULE, Albion O. Pearson, July 1960 TMX 299 AERODYNAMIC HEATING TESTS OFMISSILE STABILIZERS IN FREE JET AT MACH NUMBER 2, Louis F. Vosteen, September 1960 TMX 300 ANALYTICAL INVESTIGATION OFABLATION,Bernard Rashis and Russell N. Hopko, July 1960 TMX 332 AERODYNAMIC CHARACTERISTICS AT MACH NUMBER 2.05 OFA SERIES OF HIGHLY SWEPT ARROW WINGS EMPLOYING VARIOUS DEGREES OFTWISTAND CAMBER, Harry W. Carlson, October 1960 TMX 338 SOME AERODYNAMIC ANDCONTROL STUDIES OFLIFTING REENTRY CONFIGU- RATIONS AT ANGLES OF ATTACK UP TO 90° AT MACH NUMBER OF 2.91, Frank L. Clark and Joanna M. Evans, November1960 TMX 372 INVESTIGATION AT MACH NUMBERS OF 0.20 TO 3.50 OF BLENDED WING- BODY COMBINATIONS OF SONIC DESIGN WITHDIAMOND, DELTA,ANDARROW PLANFORMS, GeorgeH. Holdaway and Jack A. Mellenthin, August 1960 TMX 379 EVALUATION OF BLENDED WING-BODY COMBINATIONS WITHCURVED PLANFORMS AT MACH NUMBERS UP TO 3.50, George H. Holdaway and Jack A. Mellen- thin, October 1960 A PRELIMINARY STUDY OF SOME ABORT TRAJECTORIES INITIATED DURING TMX 530 LAUNCH OFA LUNAR MISSION VEHICLE,John M. Eggleston and William A. McGowan, April 1961 TMX 566 SUBSONIC AERODYNAMIC CHARACTERISTICS OF DISK REENTRY CONFIGURA- TIONSWITHELLIPTICCROSS SECTIONS ANDTHICKNESS-DIAMETER RATIOS OF 0.225 AND0.325, Fred A. Demeleand Jack J. Brownson, May 1961 SUBSONIC AERODYNAMIC CHARACTERISTICS OF SOME BLUNT DELTA CONFIGU- TMX 581 RATIONS WITH75° SWEEPBACK, George G. Edwards and HowardF. Savage, October 1961 TMX 652 EXPERIMENTAL INVESTIGATION OF DISK SHAPED REENTRY CONFIGURATION AT TRANSONIC ANDLOWSUPERSONIC SPEEDS, Frank A. Lazzeroni, May 1962 PARTII A STUDY OFNACA ANDNASA LITERATURE ONTHECALCULATION OFAERODYNAMIC LOADS HAVING APPLICATION TO LIGHTAIRCRAFT DESIGN by John N. Perkins The purpose of this study was to review existing NACA and NASAreports to determine if sufficient information was available to enable a design engineer to predict the load forces on a light airplane in both flight and landing. To facilitate the discussion, the loadings have been divided into the following seven types: pressure distributions, wing span loads, verti- cal and horizontal tail loads, control surface loads, gust loads, landing gear loads, and loads due to flutter. The results found for each of these load types is discussed briefly below and then a listing of the reports dealing with each type is given. Titles, authors, and brief summariesare given in the appendix for each report listed under the seven different types.

In order to avoid duplication with the aerodynamics portion of the investigation, the reports reviewed concerning pressure distributions were confined primarily to experimental measurementsobtained from both actual flight and wind tunnel tests. The reports reveiwed and found applicable deal with measuredpressure distributions on plain airfoils, airfoils with plain flaps, split flaps and ailerons, and airfoils with leading edge slots.

The effects of varying angle of attack, flap or aileron deflection, sweep angle, taper angle, and contour are discussed both from their effect on actual performance and their effect on existing idealized theoretical calculation methods. In general, it was found that most theoretical methods are inaccurate for large angles, such as those of sweep or flap deflection.

In addition to airfoil pressure distributions, reports concerning pres- sure distributions on fuselages alone and on wing-fuselage combinations were also reviewed. It was concluded that the effect of wing-body inter- ference must be accounted for if meaningful pressure distributions over fuselages are to be obtained. The reports listed below are indicative of the reports dealing with pressure distributions.

Pressure Distributions NACA Technical Notes: 817, 890, 1016, 1144, 1539, 1967 732, 1364 NACA Technical Reports: NACA Wartime Reports: L-205, L-264, L-434, L-439, L-553, L-676, L-700 NACA Technical Memoranda: 1117, 1126, 1164, 1177, 1194, 1220 It should be pointed out that the small number of reports reviewed here is not indicative of the total existing amountof information available concerning pressure distributions and that a more complete review of this subject is contained in the aerodynamics section of this report.

Reports dealing with the theoretical determination of the spanwise load distribution all dealt with variations of either the lifting line or lifting surface theories. Almost all of the report reviewed were written before the present day high-speed digital computers were available, and hence, much emphasis was placed on simple methods amenableto hand computations. For example, in TN 1476 in which 3 theoretical methods for calculating spanwise load distributions were compared, it was concluded that the least accurate but quickest methodwas the best. It would appear that with present day computing capabilities that this conclusion is no longer valid. In general then, it can be concluded that while the basic theoretical methods for cal- culating spanwise loads are well known and understood, the actual numerical methods should be updated to makeuse of available high-speed computers.

For example, while methods are available which allow for variations in sweep, taper, twist, plan form, and aspect ratio, most of these were purposely kept simple, and hence inaccurate, in order that the results could be ob- tained with a reasonable amount of manpowerexpenditure. Such simplifying assumptions should no longer be necessary. Consequently, there is some question as to the usefulness of the reports dealing with theoretical cal- culations other than to provide a starting point for new investigations and for any experimental data which maybe given.

However, several reports do give charts for determining preliminary values of spanwise loads for a wide range of wing configurations; examples of the charts may be found in RML8A26 and TR 921. While most of these results are based on approximate theories, the results are applicable in preliminary design work and should be useful.

In addition to the above reports, a number of reports dealt with the effect of fairing engine nacelles, fuel tanks, etc. on the wing loading.

As would be expected, it was concluded that streamlining can produce sig- nificant changes in the load distribution both from lift and drag considera- tions. Several of these reports are reviewed as a matter of general interest and to illustrate the methods of investigation. Other reports which were considered applicable to light aircraft or to the subject of wing loads and fairing problems are listed below.

Spanwise Win S Loads NACA Technical Notes: 834, 1064, 1491, 1729, 1839, 1862, 1876, 1884, _73, 2140, 2222, 2249, 2282, 2284, 2298, 2751, 2901, 3014, NASA Technical Notes: D-1501, D-1521 NACA Technical Reports: 885, 910, 969, i000, 1056, 1071, 1140, 1146, 1228, 1269, 1322, 1327 NACA Wartime Reports: L-108, L-221, L-426 NACA Technical Memorandum: 948 Reports dealing with horizontal and vertical tail loads dealt mainly with experimental results obtained from both flight tests and wind tunnel tests. While, as in the case of wing loads, most of the theoretical methods reviewed need to be brought up to date, a considerable amount of useful experimental data has been put in useable form. For example, in TN 1483 numerous graphs are presented for determining aerodynamic loads on hori- zontal tail surfaces. Similar information is also presented in the form of charts in WR L 488. Design charts for the vertical tail loads are given in TN 1122. Thus, it appears that there is possibly enough experimental infor- mation available in the form of graphs and charts to develop a design manual for tail surfaces. However, more sophisticated theoretical methods making use of high-speed computers need to be developed. The following reports dealt with loads and were thought to be valuable.

Vertical and Horizontal Tail Loads NACA Technical Notes: 1048, 1065, 1394, 1504, 2078 NACA Technical Reports: 1007, 1136 NACA Wartime Reports: L-93, L-181, L-193, L-227, L-443, L-496 As expected, the majority of reports concerning control force loads dealt with hinge moment data. In particular, most of the reports dealt with methods for reducing hinge moments at high speeds and, as a result, were not applicable to this study. However, several reports did give summaries of existing hinge moment data and theoretical methods for computing hinge moments. Two of the better reports in this respect are WR L 169 and TN 2288.

WR L 169 gives a resume of experimentally determined hinge moment data for unshielded horn balanced control surfaces and discusses means for data cor- relation. TN 2288 gives a summary of theoretical methods for computing low- speed lift and hinge moment parameters for full span trailing edge flaps and compares the accuracy of each method. Some other reports which discussed control force loads and hinge moment data can be seen below.

Control Surface Loads NACA Technical Notes: 1113, 1333, 1400, 1473, 1506, 1801 NACA Technical Reports: 911, 1034 NACA Wartime Reports: L-52, L-53, L-124, L-129, L-174, L-289, L-318, L-350, L-467 From the review of reports concerning hinge momentsit can be concluded that all methods for theoretically predicting control surface hinge moments are subject to rather large errors and are quite unreliable. The only re- liable methods for determining hinge momentsappear to be either from flight tests or large scale wind tunnel tests. It is doubtful if sufficient experi- mental evidence is available in existing NASA reports to produce reliable design charts.

The reports dealing with gust loading can be divided into two cate- gories; those concerned with the response of the airplane to gusts and those concerned with the statistical prediction of the occurrence of gusts and maximum velocities within the gusts. Most of the data found was reason- ably old (late 1940's) and would appear to need updating. As an example, TN 1976 gives a summaryof information known in 1949 relating to gust struc- ture, airplane reactions and pertinent operating statistics. Reports which were indicative of those reports discussing gust loads are listed below.

Gust Loads NACA Technical Notes: 802, 1320, 1632, 1753, 2575, 2660, 2853, 3880, 3954 NACA Technical Reports: 805, 991, 997, I010, 1172, 1272, 1285, 1345 Although very few reports dealing with landing gear loads were found, it appears that there is sufficient data available for the design of landing gear for light aircraft. In particular, TR 1154 gives charts for rapidly estimating landing-gear performance in preliminary design as well as giving a more generalized method for obtaining "exact" answers in the final design stages. Other reports on which the subject, landing gear loads, was discussed were reviewed and the reports are listed below.

Landin$ Gear Loads NACA Technical Notes: 1995, 2596, 2645, 2743 NACA Technical Reports: 1248, 1278 Applicable reports dealing with flutter were quite limited in number.

However, several reports did give fairly comprehensive compilations of exist- ing flutter information. One of the more useful reports of this type is RM L53K02a which gives salient results of much of the postwar experimental research on flutter. In order to give an indication of the theoretical state of the art, reports using methods ranging from simple to sophisticated have been reviewed and are summarized in the bibliography below. Those reports which were classified as flutter reports are shown below.

Loads Due to Flutter NACA Technical Notes: 926, 1594, 1848, 1989, 2121, 2346, 2375, 2396, 3686, 4240 NACA Technical Report: 1305 NACA Research Memoranda: L7GI8, L9EI7 Thus, a brief listing of each of the reports dealing with loads which were found applicable to the design of a light airplane is given above. Examina- tion of this material shows that while there is much useful information and data available, there does not appear to be sufficient coverage to produce a design manual for loads without using material from sources other than NACA and NASA reports.

The appendix contains student-written report reviews of those reports found applicable to loads as well as a title listing with authors and dates of those reports found "not applicable". In each group, the reports are listed chronologically by series. The table below gives the initial and final number of the reports in each group by series.

Not Applicable Applicable First NACA Technical Note 802 757 Last NACA Technical Note 4240 4409 First NASA Memorandum (Memo) 5-26-59L I0-17-58L Last NASA Memorandum (Memo) 5-26-59L 6-I-59L First NASA Technical Note D-1501 D-3 Last NASA Technical NOte D-1521 D-2604 First NACA Technical Report 732 685 Last NACA Technical Report 1364 1390 None R-20 First NASA Technical Report None R-150 Last NASA Technical Report None A-13 First NACA Wartime Report L-52 L-39 None W-41 None A-81 Last NACA Wartime Report L-700 L-743 None W-I06 First NACA Research Memorandum L7GI8 A7C28 Last NACA Research Memorandum L53K02a L58F25 Applicable Not Applicable First NACA Technical Memorandum 948 963 Last NACA Technical Memorandum 1220 1257 First NASA Technical Translation None F-25 Last NASA Technical Translation None F-81 None X-53 First NASA Technical Memorandum Last NASA Technical Memorandum None X-639 It should be noted that some applicable reports were assigned to the "not applicable" list because of similar information found in other reports. It is hoped that the subject listing and the student reviews will enable the reader to identify any aerodynamics loads report in which he may be interested.

APPENDIX Applicable NACA Technical Notes TN 802 TEST OF A GUST-ALLEVIATING WING IN THE GUST TUNNEL, C. C.

Shufflebarger, April 1941 The purpose of this report was to determine the effectiveness of a torsionally flexible wing with the torsion axis ahead of the locus of the section aerodynamic centers in reducing airplane accelerations due to atmospheric gusts. Both a torsionally flexible wing and a rigid wing were tested.

It was concluded that the method of alleviating gust loads by torsional deflection is not feasible.

TN 817 CORRECTION OF THE LIFTING-LINE THEORY FOR THE EFFECT OF THE CHORD, Robert T. Jones, July 1941 The report showed that a simple correction for the chord of a finite wing can be deduced from the three dimensional flow around an elliptic plate. It was found that this correction brings the lifting line theory into closer agreement with experiments. The correction also accounts for losses in lift attributed to viscosity effects.

TN 834 THE CALCULATIONS OF SPAN LOAD DISTRIBUTIONS ON SWEPT-BACK WINGS, William Mutterperl, December 1941 Object: To calculate span load distributions of sweptback wings of various sweep angles, taper ratios.

Method: Modified bound vortex theory, extension of Wieghardt's work with flat plates. Replace the wing with a bound vortex at the quarter-chord line, then require downwash due to system of bound and trailing vortices to conform at the 3/4 chord line to the slope of the flat plate wing surface. Assume that wing thick- ness is not great enough to displace vortex from horizontal plane, thus flat plate theory can be used. Analysis is done for com- plete wing, thus in practice, it does not hold at center because of fuselage. Theory does not hold at trips either because strong trailing vortices are present and theory is based on 2-dimensional flow.

Induced downwash velocity is calculated from Biot-Savart law.

Only induced drag can be computed by this method.

TN 890 PRESSURE DISTRIBUTION ON THE FUSELAGE OF A MIDWING AIRPLANE MODEL AT HIGH SPEEDS, James B. Delano, February 1943 The purpose was to determine the air pressure distribution on various parts of the fuselage for use in structural design. The highest negative pressures occurred near the location where the wing and fuselage were joined. These low pressures were more dependent on the wing than the fuselage. The critical speed of the fuselage will be decreased because of velocities induced by the wing. Also the critical speed of the wing will be decreased.

At high speed the magnitude of the pressure coefficients as pre- dicted by the application of the theoretical factor i/_l-m z to pressure coefficients measuredat low speeds may misrepresent the actual. At points of macimum negative pressure, the variation of the pressure coefficient with speed was in good agreementwith the factor i/ _, at least up to m = 0.5 at 590F.

THEINFLUENCE OFTHEAERODYNAMIC SPAN EFFECT ONTHEMAGNITUDE OF TN 926 THETORSIONAL-DIVERGENCE VELOCITY ANDONTHESHAPE OF THECOR- RESPONDING DEFLECTION MODE,Francis B. Hildebrand and Eric Reissner, February 1944 This paper deals with the limiting case of the bending-torsion flutter problem which occurs when the flutter frequency has the value zero. This procedure accounts for the aerodynamic span effect for the determination of the torslonal-divergence veloci- ties. The developments were based on the theory of torsion of straight rods and on lifting line theory for the spanwise dis- tribution of lift.

PRESSURE DISTRIBUTIONS FORREPRESENTATIVE AIRFOILSANDRELATED TN 1016 PROFILES, Theodore Theodorsen and Irven Naimen, February 1946 This report tabulates plots of airfoil shapes and pressure distri- butions at various CL'S and angles of attack. The airfoils are NACA22-, 44-, and 230-series, Clark Y family, circular arc air- foils and synthetic airfoils based on _ = _o + AI cos (_-6) and harmonics. Plots are for C L = 0, 0.i, 0.2, 0.3, 0.5, 1.0, 1.5 and ideal CL. The descriptions of airfoil shapes are given in NACA Report No. 460, 1933, and NACA Report No. 669, 1939. All Clark Y's are based on station-relative thickness and camber table, with maximum thickness and cambergiven in airfoil desig- nation (CY(c)-t). The Clark Y-M airfoil has a flat bottom with constant camber.

Circular-arc airfoils were based on the Karmann-Trefftz transfor- mation.

Synthetic airfoils were previously defined. The phase angle of 45 ° appears to give the best airfoil shape based on one harmonic.

Generating function containing ist and 2nd. Harmonics were chosen to give a zero moment coefficient, as was done for series based on ist, 2nd, and 4th harmonic. The 4th harmonic has no effect on moment, but does affect pressure distribution.

6OO TN 1048 TWO-DIMENSIONAL WIND-TUNNEL INVESTIGATION OF LOW-DRAG VERTICAL TALL, HORIZONTAL TALL, ANDWINGSECTIONS EQUIPPED WITHSEALED INTERNALLY BALANCED CONTROL SURFACES, Albert L. Braslow, April I. Airfoils A.

Vertical Tail - c = 24", .155c thick, symmetrical NACA 64-series, .40c rudder, hinge axis at .412 c (c = chord of rudder).

B. Horizontal Tail - c = _4", r 13c thick NACA 64 series profile, .35c elevator, hinge axis at .43 c e (ce = chord of elevator).

C Wing - c = 24", .17c thick, NACA 7-series profile, .22 cw aileron, c I = 0.266 (design section lift coefficient).

II. Tests A. RN = 3,6,9xi06 for lift and drag tests on tail sections B. RN 6x106 for control surface hinge moment and balance pressure C. RN = 6x106 roughness applied to vertical tail III. Vertical Tail Section _Cl _Cl 9_o effectiveness A. Lift _=_o 0.107,_-_-=r 0.062, _-_-=r 0.58 parameter TN LIFTING-SURFACE-THEORY RESULTS FOR THIN ELLIPTIC WINGS OF ASPECT RATIO 3 WITH CHORDWISE LOADINGS CORRESPONDING TO 0.5-CHORD PLAIN FLAP AND TO PARABOLIC-ARC CAMBER, Stewart M. Crandall, May 1946 The electromagnetic-analogy method was used to provide lifting- surface-theory solutions to determine the aspect-ratio corrections for the slope of the lift and hinge-moment coefficients against flap deflection. The results were obtained for unswept elliptic wings having an aspect ratio of 3. The lifting-surface-theory results for hinge-moment coefficient vs angle of attack agreed well with experiment for thin unswept elliptic wings. The lifting line theory results did not agree with experiment.

In order to use the electromagnetic-analogy model the vortex patterns and their wakes were first determined from the lifting- surface-theory for a (i) elliptic wing with 0.5-chord-flap chord loading, and (2) elliptic wing with a parabolic-arc-camber chord.

The electromagnetic analogy is found in the following reference: Swanson, Robert S. and Stewart M. Crandall, An Electromagnetic- Analogy Method for Solving Lifting-Surface-Theory Problems.

NACA ARR No. L5D23, 1945.

1065 CONSIDERATION OFDYNAMIC LOADS ONTHEVERTICAL TAIL BYTHETHEORY TN OF FLATYAWING MANEUVERS, John Boshar and Philip Davis, June 1946 Dynamic yawing effects on vertical-tail loads are considered by a theory of yawing maneuvers. With the restriction of flat yawing maneuvers the loads on the vertical tail that arise from abrupt deflections of the rudder or suddenly imposed momentsfrom any source may be determined. It was assumedthat the only motion resulting from a rudder deflection is restricted to the plane of yaw. This implies a low effective dihedral. Other assumptions are: (I) the plane is initially in steady, power-off flight, (2) no changes occur in speed during the maneuver, (3) no changes in altitude, (4) no rolling or pitching, (5) the lateral stability derivations are linear functions of the angle of sideslip.

The results on a fighter aircraft of both experimental and theoretical methods are compared.

COLLECTION ANDANALYSIS OFHINGEMOMENT DATAONCONTROL SURFACE TN 1113 TABS, Paul E. Purser and Charles B. Cook, April 1947 Equations are presented for tab hinge momentcoefficients. The equations were derived from flap hinge momentequations, and when comparedwith experiments, found to be applicable.

SIDESLIPANGLES ANDVERTICAL-TAIL LOADS IN ROLLING PULL-OUT TN 1122 MANEUVERS, Maurice D. White, Harvard Lomaxand HowardL. Turner, April 1947 This report shows that it is possible to develop angles of sideslip which may cause critical vertical-tail loads in rudder fixed rolls. A method for determining the side-slip anlges is devel- oped. A simplified method for determining these side-slip angles is comparedwith flight charts and was found to be fairly depend- able as a first approximation to the problem of predicting side- slip angles and vertical tail loads. Design charts were con- structed in order to compare the actual flight results with results from present theory. It was shown that, in general, agreementwith experiment was very good. However, the results are valid only for conventional airplanes.

1144 MEASUREMENT OF THEPRESSURE DISTRIBUTION ONTHEHORIZONTAL-TAIL TN SURFACE OF A TYPICAL PROPELLER-DRIVEN PURSUIT AIRPLANE IN FLIGHT, Melvin Sadoff, William N. Turner and LawrenceA. Clousing, July The purpose was to makean investigation of the pressure distribu- tion on the horizontal-tail surface of a representative pursuit- type airplane during maneuverswhich might cause critical loading on the tail surface.

The test airplane was a single-place, single-engine, interceptor- pursuit, low-wing monoplane driven by a tractor propeller and equipped with a tricycle landing gear. The pressure distribution was measuredat four stations along each tail on both top and bottom.

The horizontal tail loads were also calculated using the measured values of the pressure coefficient. For accelerated flight the horizontal tail load was as high as 2000 ibs. The measuredpres- sures were comparedto the formerly calculated pressures and were found to compare quite well.

TN 1320 INVESTIGATION OF THEDYNAMIC RESPONSE OFAIRPLANE WINGS TO GUSTS, Harold B. Pierce, August 1947 The report presents a method of analysis for predicting the dynamic response of airplane wings to gusts by considering only the fundamental bending mode. The tests were conducted in a wind tunnel and used to evaluate the analytical method. It was found that the analytical method is sufficiently accurate to predict the ratio of the maximum dynamic wing tip deflection increment to the maximum fuselage acceleration increment for a conventional airplane. The report also indicates that simplification of the methodby omitting parts of the damping is not feasible.

TN 1333 ESTIMATION OF CONTROL FORCES OF SPRING-TAB AILERONS FROM WIND- TUNNEL DATA, OwenJ. Deters, June 1947 A method is presented for estimating the control forces of spring- tab ailerons. The application of a spring tab to the ailerons has the advantage of reducing the difference between the control force at high and low speeds for a stated value of wing-tip helix angle.

The spring-tab tends to reduce the hinge momentcaused by the ailerons.

The basic assumptions involved in the method are: (I) the rolling motion of the airplane is steady, (2) the effects of aileron and horn deflections on the linkages are negligible, (3) the effects of wing deflection and friction on the control forces are negli- gible.

TN 1394 FLIGHTINVESTIGATION ONA FIGHTER-TYPE AIRPLANE OF FACTORS WHICH AFFECT THELOADS ANDLOAD DISTRIBUTIONS ONTHEVERTICAL TAIL SURFACES DURING RUDDER KICKANDFISHTAILS, John Boshar, August Results are presented on a flight investigation conducted on a fighter-type airplane to determine the factors which affect the loads and load distributions on the vertical tail during maneuvers.

The investigation was conducted on a Curtiss P-40K airplane-- low-wing fighter, weight ~ 8200 Ibs, engine rated at i000 HP at a pressure altitude of 10,800 ft.

HINGE-MOMENT CHARACTERISTICS OF BALANCED ELEVATOR ANDRUDDER FOR TN 1400 A SPECIFICTAlL CONFIGURATION ONA FUSELAGE IN SPINNING ATTITUDES, Ralph W. Stone, Jr., and Sanger M. Burk, Jr., August 1947 Hinge-momentmeasurementsare presented for a balanced elevator equipped with trim tabs and for a balanced rudder. The measure- ments were taken in attitudes simulating spin conditions without regard to the effectiveness of the control surfaces in producing a recovery.

TN 1473 HIGH-SPEED WINDTUNNEL INVESTIGATION OFHIGHLIFT ANDAILERON CONTROL CHARACTERISTICS OF AN NACA 65-210 SEMISPAN WING,Jack Fischel and Leslie E. Schneiter, November1947 An investigation of characteristics of NACA65-210 semispanwing, at velocities M = 0.13 to M = 0.71, equipped with a .25c full span slotted flap and a .38c, 20%span straight sided aileron was made.

1476 A COMPARISON OF 3 THEORETICAL METHODS FORCALCULATING SPAN LOAD TN DISTRIBUTION ONSWEPT WINGS, Nicolas H. Van Dorn and John DeYoung, November1947 The report compared(i) Falkner Method (R. and M. No. 1910, British A.B.C., 1943), (2) Mutterperl Method (NACA TN 834), (3) Weissenger Method (NACA TM1120).

Falkner - 24 to 32 hrs Time: Mutterperl - 20 to 28 hrs Weissenger - 2-1/2 to 3 hrs i. Falkner Accuracy: 2. Mutterperl 3. Weissenger Conclusion: The Weissenger method was best unless extreme accuracy needed. Then go to Falkner. Mutterperl was not applicable to forward-swept wings. The Weissenger method allows pretabulation of many constants and application to any plan form; thus it takes much less time. (Tabulation in book) The report contains 70 pages of information and directions for use of each method. The object was to present material in such a way that a computing staff can do the work unsupervised.

TN 1483 FLIGHT MEASUREMENTS OFAERODYNAMIC LOADS ONTHEHORIZONTAL TAIL SURFACE OFA FIGHTER TYPEAIRPLANE, John B. Garuin, November The purpose of this report was to determine the load applied to the horizontal tail surface of a fighter type aircraft. Airspeed ranged from 125 to 300 mph and accelerations went up to 6g. The differential-pressure-distributions methods were employed to ob- tain the value of the loads. The tests verify that changes in tail load due to changes in tail load parameters are those which would be expected due to engineering considerations.

TN 1491 THEORETICAL ADDITIONAL SPAN LOADING CHARACTERISTICS OF WINGS WITH ARBITRARY SWEEP ASPECT RATIO, ANDTAPER,John DeYoung,December The Weissenger method for determining additional span loading was used to find the lift-curve slope, spanwise center of pressure, aerodynamic center location, and spanwise loading coefficient of untwisted and uncamberedwings having a wide variety of plan forms.

Although the Weissenger theory of the lifting line method is limited, the comparison between the theory and experimental data is very close.

TN SIDESLIPANGLES ANDVERTICAL TAIL LOADS DEVELOPED BY PERIODIC CONTROL DEFLECTIONS, Harvard Lomax, January 1947 The report develops equations for determining tail loads due to the 3 basic maneuvers, with rudder exhibiting a periodic oscillation and aileron movementssuperimposed.

Dynamic maneuversconsisting of periodic rudder and aileron con- trol deflections were considered with respect to the maximum sideslip angles developed and the position of the rudder at the time of maximum sideslip. The sideslip obtained from the oscil- lating rudder, the rudder kick and the rolling-pull-out are compared.

Also for all configurations one cycle of rudder motion is suffi- cient to produce more sideslip than that obtained from the rudder kick.

TN 1506 AN APPLICATION OF FALKNER'S SURFACE-LOADING METHOD TO PREDICTIONS OF HINGE-MOMENT PARAMETERS FORSWEPT-BACK WINGS,Arthur L. Jones and LomaSluder, February 1948 An application of the Falkner lifting-surface theory to the predic- tion of hinge-moment for swept back plan forms in order to de- velop an analog to the unswept plan forms was made.

The predicted values of Ch_ (variation of hinge-moment coeffi- cient with angle of attack) did not agree with the experimental results but the lifting surface theory proved to be more accu- rate than the lifting line theory. The fact that the Falkner theory did not agree with experiment was probably due to viscous effects which were not considered.

TN MEASUREMENTS OF THEPRESSURE DISTRIBUTION ONTHEHORIZONTAL TAlL SURFACE OFA TYPICAL PROPELLER DRIVEN PURSUIT AIRPLANE IN FLIGHT.

III - TAlL LOADS IN ABRUPT PULL-UP PUSH-DOWN MANEUVERS, Melvin Sadoff and LawrenceA. Clousing, February 1948 The total horizontal-tail load and the root bending-momentincre- ments calculated by the use of existing rational procedures are comparedwith experimental values obtained in pull-up push-down maneuvers on a representative propeller driven, pursuit plane (P-39 - 213 sq ft, 7600 ibs, 34 ft span, CGat 30.3%chord) for six different combinations of power, indicated airspeed, and pres- sure altitude.

It was found that methods currently available for predicting maxi- mummaneuvering tail loads from prescribed elevator motions are valid and can be used with assurance, provided _hat the aerodynamic parameters are accurately known. Computations of tail load based on linear elevator motion in a pull-up push-down maneuverwith a 0.2 second elevator reversal may be expected to give very nearly the samevalues of maneuveringtail load as those that would be measured in actual pull-up push-downmaneuversat identical values of g-forces, provided aerodynamic parameters used in the computation are accurate.

The maximum tail-load increments computedby the use of the methods in the report were in fairly good agreement with actual values and would be sufficiently accurate for preliminary design studies.

TN EXPERIMENTAL INVESTIGATION OF THEEFFECTS OF CONCENTRATED WEIGHTS 1594] ONFLUTTER CHARACTERISTICS OFA STRAIGHT CANTILEVER WING,Harry L. Runyanand John L. Sewall, June 1948 An investigation was madeto determine the effects of concentrated weights of 38, 60, 90, and 100%of wing weight on a rigid canti- lever wing with varied momentsof inertia, and spanwise and chordwise positions of the weight.

TN 1632 GUST-TUNNEL TESTS TO DETERMINE INFLUENCE OFAIRFOIL SECTION CHARACTERISTICS ONGUST LOAD FACTORS, Harold B. Pierce and Mitchell Trauring, July 1948 Gust tunnel tests were conducted to determine if gust-load factors for airplanes with low-drag wing sections should be higher than those for airplanes with conventional wing sections.

A model having a wing with a low-drag section was used with smooth surfaces and with roughness applied to the leading edge to simu- late the flow conditions for a conventional section.

Gust loads may be different from regular loads because of a time lag required for the boundary layer to respond to the change in angle-of-attack.

TN FLIGHTDETERMINATION OFWING ANDTAIL LOADS ONA FIGHTER-TYPE AIRPLANE BYMEANS OF STRAIN-GAGE MEASUREMENTS, William S. Aiken, Jr., October 1948 A flight investigation was conducted to determine the contribution of wing, tail, and fuselage to the total airplane lift of a propeller-driven fighter-type airplane. The Machnumber ranged from 0.2 to 0.8. The loads on the airplane componentswere measuredby the use of calibrated strain gage installations. The flight test data was the result of 34 abrupt push-down and pull- up maneuvers.

TN 1753 EVALUATION OF A FIXED SPOILER AS A GUST ALLEVIATOR, Harry C.

Mickelboro, November1948 This report attempts to determine whether a fixed spoiler will alleviate maximum acceleration on aircraft entering gusts. Steady state theory indicates such is true. Experiments were performed in a gust tunnel for a sharp edge gust (about 1/2 chord distance) and a gradual gust (about 12-14 chord distances). The results show a long lag between entering gust and alleviation. A fixed spoiler slightly increases maximum acceleration encountered in entering sharp edge gust. The reason for this is that the spoiler has the effect of increasing effective camber, which causes flow breakdown. After maximum acceleration is passed, the spoiler begins to alleviate acceleration. Whenentering gradual gust, the spoiler does reduce maximum acceleration.

TN 1801 WIND-TUNNEL INVESTIGATION OF THESPINNING CHARACTERISTICS OF A MODEL OFA TWIN-TAlLLOW-WING PERSONAL-OWNER-TYPE AIRPLANE WITH LINKEDANDUNLINKED RUDDER ANDAILERON CONTROLS, Walter J.

Klinar and Lawrence J. Gale, January 1949 A test was madeon a I/Ii scale model based on light military aircraft tested per title in the Langley 20' free spin tunnel without propeller or power. Tested with ballast to simulate 5000' altitude with 4 types of loading: (i) Normal, (2) Extra mass along fuselage, (3) Extra mass along wings, (4) density doubled.

TN 1839 SOME THEORETICAL LOW-SPEED SPAN LOADING CHARACTERISTICS OF SWEPT WINGS IN ROLLANDSIDESLIP, John D.Bird, March 1949 The Weissenger method was used to determine the additional span loading for incompressible flow which in turn was used to deter- mine the dampingin roll, the lateral center of pressure of the rolling load, and the span loading coefficient caused by rolling for wing plan forms of various aspect ratios, taper ratios, and sweep angles.

The experimental results showedthat the Weissenger method was quite accurate.

TN 1848 FLUTTER OF A UNIFORM WING WITHANARBITRARILY PLACED MASS ACCORD- ING TOA DIFFERENTIAL-EQUATION ANALYSIS ANDA COMPARISON WITH EXPERIMENT, Harry L. Runyan and Charles E. Watkins, March 1949 A method is presented for the calculation of the flutter speed of a uniform wing carrying an arbitrarily placed concentrated mass.

The method involves the solution of the differential equations of motion of the wings at flutter speed and does not require the assumptions of specific normal modesof vibration.

The method used is not limited to a uniform cantilevered wing with a single weight. Changing the boundary conditions correctly will correct for different applied loads on the wing.

For wings which are not unifrom the equations reduce to ordinary differential equations with variable coefficients. Thus the solution would be more difficult to obtain.

It was found that the location of the concentrated masseson the wing could be used to advantage in increasing the flutter speed of a given wing.

The comparison between experimental and theoretical results was good.

TN 1862 A SIMPLE METHOD FORESTIMATING THESUBSONIC LIFT ANDDAMPING IN ROLLOF SWEPT BACK WINGS,Edward C. Polhamus, April 1949 The report develops simple lifting line equations for lift and roll damping of wings at low speeds, where aspect ratio is not too low.

TN 1876 CALCULATION OFTHEAERODYNAMIC LOADING OF FLEXIBLE WINGS OFARBI- TRARY PLANFORM ANDSTIFFNESS, Franklin W. Diederich, April 1949 A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of wings and tail surfaces of arbitrary plan form and stiffness.

TN 1976 SUMMARY OF INFORMATION RELATING TO GUST LOADS ON AIRPLANES, Philip Donely, November 1949 Available information on gust structure, airplane reactions, and pertinent operating statistics was examined. The assumptions made in the analysis are as follows: (i) The gust is sharp-edged in the direction of flight. (2) The gust velocity is uniform across the span. (3) The gust direction is normal to the lateral axis. (4) The primary effect of the gust is to change the lift on the airplane. (5) The lift increment on the horizontal tail is negligible as compared to the wing lift increment.

TN 1989 SOME EFFECTS OF DENSITY AND MACH NUMBER ON THE FLUTTER SPEED OF TWO UNIFORM WINGS, George E. Castile and Robert W. Herr, December Results of 66 flutter tests were presented to show some effects of density and Mach number upon flutter speed. Two uniform, cantilever wing models, one having a small amount of sweep, were fluttered through a range of Mach numbers up to 0.82. The mass ratio, k, for those models ranged from 0.00375 to 0.ii, while RN varied from 0.266 x 106 to 3.000 x 106 . Two testing mediums, having different velocities of sound, were used to obtain flutter at two Mach numbers at the same density.

TN INFLUENCE OF WING FLEXIBILITY ON FORCE-TIME RELATION IN SHOCK STRUT FOLLOWING VERTICAL LANDING IMPACT, Albert E. McPherson, J. Evans, Jr., and Samuel Levy, November 1949 Analysis indicates an experiment proves that wing flexibiltiy can reduce shock strut by as much as 25%. If time of impact is less than natural period of wing and the generalized mass of the wing is less than 5 times the actual mass, the reduction is not significant.

For reduction is 5% TI/T N -- 1 5 < -- < 15 M o Where: duration impact.

T I = natural period of fundamental flexure mode of wing.

T N = generalized mass in fundamental mode.

M I = S total mass.

O The method uses matrix methods.

TN 1884 NOTE ONTHEACCURACY OF A METHOD FORRAPIDLY CALCULATING THE INCREMENTS IN VELOCITY ABOUT AN AIRFOIL DUETOANGLE OFATTACK, Laurence K. Loftin, Jr., June 1949 The exact method is given in NACA Report No. 452.

The rapid method is given in NACA Report No. 824.

The report proves the error in rapid method to be in error by a factor of less than cos _ (_ = section angle of attack). Thus error due to the use of the rapid method is less than the dif- ference between theory given in Report No. 452 and the actual be- havior of airfoil.

TN 1967 A COMPARISON OFWING LOADS MEASURED IN FLIGHTONA FIGHTER-TYPE AIRPLANE BY STRAIN-GAGE ANDPRESSURE-DISTRIBUTION METHODS, W. S.

Aiken, Jr., and Donald A. Howard, November1949 Pressure-distribution measurementswere madeon the wing of a fighter-type airplane to determine the span loading and to compare the center-of-pressure results with those obtained by strain-gage measurements. The Machnumbers ranged from 0.35 to 0.81. The air- plane used was the sameone used in TN 1729 and TN 1719. The following conclusions were noted: (I) The agreementbetween pressure-distribution measurementsand strain-gage measurementsof the wing root shear and bending momentwas good.

(2) Buffeting had no serious effect on span loading for the condi- tions investigated.

(3) The spanwise center of pressure shifted farther outboard dur- ing low-speed stalls than during buffeting at Mach numbers near 0.8.

TN 1973 THEORETICAL SPANWISE LIFT DISTRIBUTIONS OFLOW-ASPECT-RATIO WINGS AT SPEEDS BELOW ANDABOVE THESPEED OF SOUND, Franklin W.

Diederich and Martin Zlotnick, October 1949 The spanwise lift distributions of wings of low aspect ratio but of arbitrary plan form and angle of attack were analyzed.

Two different methods gave the same:result for the spanwise lift distributions. The two methods were the virtual-mass concept and the Weissenger method. With certain limitations these lift distributions are independent of plan form.

The lift distributions were graphed as functions of span and angle of attack.

Equations and tables are included to calculate reduction. It is apparent that it is unlikely that light aircraft could be affected significantly.

HORIZONTAL TAlL LOADS IN MANEUVERING FLIGHT,Henry A. Pearson, TN 2078 William A. McGowan, JamesJ. Donegan,April 1950 A method is given for determining the horizontal tail loads in maneuvering flight. The method is based upon the assignment of a load factor variation with time and the determination of a minimum time to reach peak load factor.

The assumptions madein the method are as follows: (i) The change in load factor due to flight path change is small.

(2) The aerodynamic derivatives are linear with angle of attack and elevator angle.

(3) The variation of speed during the maneuvermay be neglected.

(4) Unsteady lift effects can be neglected.

STUDY OF EFFECTS OF SWEEP ONTHEFLUTTER OF CANTILEVER WINGS TN (Supersededby Report 1014), J. G. Barmby, H. J. Cunningham,and I. E. Garrick, June 1950 This report was done to provide data on the effect of sweep on the flutter of a cantilever beam, to formulate a method of analytically finding the force and momentcaused by the flutter, and to comparethe experimental and the analytical results.

The experimental and analytical data comparesvery well. The coupling between bending and torsion lowers the flutter speed while the fact that only part of the forward velocity is aero- dynamically effective increases the flutter speed. The location of the section of center of gravity, the length-to-cord ratio_ and the tip shape all had an important effect on flutter. In general it was observed that the greater the angle of sweep the higher the flutter speed.

THEORETICAL SPAN LOADING FORWINGS OF ARBITRARY PLANFORM AT TN 2140 SUBSONIC SPEEDS, John DeYoung,July 1950 Simplified lifting-surface theory, which includes effects of compressibility and spanwise variation of lift curve slope, is used to develop equations and charts for antisymmetric loading of wings with symmetric plan forms with constant spanwise sweep angle at 1/4 chord line. Makes allowances for rolling, aileron deflection, sideslip of wings with ailerons. Includes solutions for straight-tapered wings.

Accuracy of method was good up to large angles where flow separates.

TN 2222 A METHOD FORTHEDETERMINATION OF THESPANWISE LOAD DISTRIBUTION OFA FLEXIBLESWEPT WING AT SUBSONIC SPEEDS, Richard B. Skoog and Harvey H. Brown, March 1951 A method is presented for the determination of spanwise load distribution of a flexible swept wing at subsonic speeds. The method is based on a relaxation approach utilizing aerodynamic loadings obtained from previously published work (NACA Reports 921, 948) based on Weissenger's simplified lifting-surface theory together with simple beamtheory. The solution is expressed in a convenient form such that the amount of detailed computing in- volved when extensive aeroelastic calculations for many flight conditions are desired is reduced to that for a single set of flight conditions.

TN 2249 THESPANWISE DISTRIBUTION OF LIFT FORMINIMUM INDUCED DRAG OF WINGS HAVING A GIVENLIFT ANDGIVENBENDING MOMENT, Robert T.

Jones, December1950 In this report the problem of the minimuminduced drag of wings having a given lift and a given span is extended to include cases in which the bending momentto be supported by the wing is also given. As in the classical problem of induced drag, the theory is limited to lifting surfaces traveling at subsonic speeds.

Expressions for the minimumdrag and the corresponding spanwise load distributions are also given for the case "in which the lift and the bending momentabout the wing root are fixed while the span is allowed to vary.

General formulas are given for lift, drag, and bending moment.

TN 2282 AN IMPROVED APPROXIMATE METHOD FORCALCULATING LIFT DISTRIBUTIONS DUETO TWIST,JamesC. Sivells, January 1951 The report gives a method of finding lift distribution due to twist, based on lifting line theory making use of aspect ratio. Twist may be due to washout, aeroelastic deformations, deflected flaps or ailerons, or of downwash induced by another lifting surface or by jet boundary of a wind tunnel. The twist can be symmetrical, antisymmetrical, continuous, or discontinuous. The method gives good results even for swept wings.

Discontinuities When discontinuities in the twist are encountered, as in the case of deflected ailerons, the portions of the curve on each side of the discontinuity must be "patched" or faired to give a continuous twist function. In the case of the report, this was done using ellipses to patch the discontinuous portion of the curve.

N 2284 LIFT, PITCHING MOMENT, ANDSPAN LOAD CHARACTERISTICS OF WINGS AT LOW SPEED AS AFFECTED BYVARIATIONS OF SWEEP ANDASPECT RATIO, Edward J. Hopkins, January 1951 The report consisted of taking experimental data on airfoils with aspect ratios of 6.8, 5.3, 4.2, 3.4, 2.8 with corresponding taper ratios of approximately 0.4 to 0.7 to find lift-curve slope, the span load distributions, the aerodynamic-center, and the spanwise center of pressure locations as comparedwith calcula- tions madeusing the Weissenger method.

Data was taken in the Ames7- by 10-foot tunnel at low speed with corrections madefor tunnel wall interference. Previous experience proved these corrections to be sufficient to make the error negligible.

The report gave no mathematics but gave many results.

TN 2288 ESTIMATION OF LOW-SPEED LIFT ANDHINGE-MOMENT PARAMETERS FORFULL SPAN TRAILING-EDGE FLAPSONLIFTING SURFACES WITHANDWITHOUT SWEEPBACK, Jules B. Dods, Jr., February 1951 The report uses methods given in references to calculate full-span parameters from section data, then commentson the accuracy of each.

Method i Method i is a modified version of the procedure used in reference 4 (Jones, Arthur L. and Loma Sluder: An Application of Falkner's Surface Loading Method to Predictions of Hinge-Moment Parameters for Swept-Back Wings. NACA TN 1506, 1948). Computed values of the lift-curve slopes of the unswept models still were consis- tently high. The aspect ratio range from 2 to 6 investigated.

Correlation is satisfactory, but not good enough for final design.

Method 2 Method 2 consists of a combination of the methods presented by Falkner and Weissenger. Falkner's method is used throughout, including correction for induced-camber. Weissenger was used to correct for induced-angle-of attack. This method was found to be the best method of those tested.

Method 3 Method 3 combines the induced angle-of-attack corrections of method 2 and the induced-camber correction to Ch_ and Chdelta as given in Toll, Thomas A. and Leslie E. Schneiter: Approximate Relations for Hinge-Moment Parameters of Control Surfaces on Swept Wings at LowMachNumbers. NACA TN 1711, 1948. This method is included to prove that the method given by this reference is not satisfactory.

Method 4 Method 4 is an approximate way of accounting for the effects of sweep by applying modified lifting-line theory to the equations for the hinge-moment parameters of unswept airfoils. The method explained in same reference as Method 3. Use of this method is recommended only for rough approximation.

Method 5 This method is completely explained in Swanson, Robert S. and Stewart M. Crandall: Lifting-Surface-Theory Aspect Ratio Correc- tions to the Lift and Hinge-Moment Parameters for Full-Span Eleva- tors on Horizontal Tail Surfaces. NACA TN 1275, 1947. Method 2 gives much better results except for Cldelta.

TN 2298 A MODIFICATION TO THIN-AIRFOIL-SECTION THEORY, APPLICABLE TO ARBITRARY AIRFOIL SECTIONS, TO ACCOUNT FOR THE EFFECTS OF THICK- NESS ON THE LIFT DISTRIBUTION, David Graham, February 1951 The report investigated NACA Report Nos. 452, 411, 833, 824, 722, and NACA ARRL4K22a and found that Report No. 833 gives the best accuracy of the methods which give reasonably rapid answers. How- ever, there is something lacking in accuracy in the area of camber and angle of attack effects. This report increases the accuracy of the method in those areas. Briefly the change in- troduced by this report is to adjust the vorticity for the local velocity induced by the airfoil thickness distribution.

AN ITERATIVE TRANSFORMATION PROCEDURE FOR NUMERICAL SOLUTION OF TN 2346 FLUTTER AND SIMILAR CHARACTERISTICS-VALUE PROBLEMS, Myron L.

Gossard, May 1951 An iterative transformation procedure suggested by H. Wielandt for numerical solution of flutter and similar characteristic-value problems is presented.

ON THE USE OF COUPLED MODAL FUNCTIONS IN FLUTTER ANALYSIS, TN 2375 Donald S. Woolston and Harry L. Runyan, June 1951 An investigation of the flutter characteristics of a uniform, unswept, cantilever wing of high aspect ratio and under condi- tions of high mass coupling was made by means of an analysis of the Rayleigh type based on coupled modal functions. The re- sults were as follows: i. Whencomparedwith experiment, the results of flutter analysis were high.

2. Increasing the number of modesin the coupled-modeanalyses of these cases did not usually cause the result to converge toward the experimental results.

SINGLE-DEGREE-OF-FREEDOM-FLUTTER CALCULATIONS FORA WINGIN FN 2396 SUBSONIC POTENTIAL FLOW ANDCOMPARISON WITHAN EXPERIMENT, Harry L. Runyan, July 1951 A study of single-degree-of-freedom pitching oscillations of a wing was presented. It includes the effects of Machnumber and structural damping. The actual existence of single-degree-of- freedom flutter was demonstrated by somelow-speed tests of a wing, pivoted a short distance ahead of the leading edge with a geometric A.R. of 5.87.

TN 2575 A FLIGHTINVESTIGATION OF THEEFFECT OF CENTER-OF-GRAVITY LOCATION ONGUST LOADS, Jack Funk and Earle T. Binckley, December1951 Experimental and theoretical investigations showedthat forward movementof c.g. location reduces gust loads.

TN 2596 AN IMPULSE MOMENTUM METHOD FORCALCULATING LANDING GEAR CONTACT CONDITIONS IN ECCENTRIC LANDINGS, Robert T. Untemaand Benjamin Milwitzky, January 1953 An impulse-momentum method for determining impact conditions for landing gears in eccentric landings is presented. The analysis is mainly concerned with the determination of contact velocities for impacts subsequent to initial touchdown in eccentric landings and with the determination of the effective mass acting on each landing gear.

Changesin airplane angular and linear velocities and the magni- tude of landing-gear vertical, drag, and side impulses resulting from a landing impact are determined by meansof impulse-momentum relationships. The effective mass acting on each landing gear is also determined from the calculated landing gear impulses.

General equations applicable to any type of eccentric landing are written and solutions are obtained for the cases of impact on one gear, a simultaneous impact on any two gears, and a sym- metrical impact. In addition a solution is presented for a simplified two degree of freedom system which allows rapid quali- tative evaluation of the effects of certain principal parameters.

The general analysis permits evaluation of the importance of such initial conditions at ground contact as vertical, horizontal, and side drift velocities, wing lift, roll, and pitch angles, and rolling and pitching velocities.

TN 2645 EFFECTS OF WING LIFT ANDWEIGHT ONLANDING GEAR LOADS,Dean C.

Lindquist, March 1952 Drop tests were madewith a small landing gear in the Langley impact basin. Wing lift was simulated by mechanical application of a constant lift force to the test specimen throughout each impact. The results of these investigations show the variations of maximum landing-gear load, landlng-gear load factor, and max- imumupper-mass acceleration with changes in lift force and dropping weight at various vertical contact velocities.

TN 2660 AN APPROACH TOTHEPREDICTION OFTHEFREQUENCY DISTRIBUTION OF GUST LOADS ONAIRPLANES IN NORMAL OPERATION, Harry Press, April The statistical concepts of randomvariables and probability distributions are applied to the "sharp edge gust" formula.

Expressions are derived for the frequency distribution of gust loads in terms of distributions of the related variables such as effective gust velocity and airspeed. Solutions are obtained under assumptions that appear reasonable on the basis of present practices in gust research. The results _rom the theoretical method comparedfavorably with those of experiment.

TN 2743 LANDING GEAR IMPACT,W. Flugge, October 1952 Both the landing impact and the taxying impact were considered, but drag forces were excluded in an investigation of landing gear impact. The differential equations are developed and their numerical integration is shown, considering the non-linear pro- perties of the oleo shock strut. It is shownhow the dimensions of the metering pin may be determined from a given load-time diagram.

TN 2751 A SIMPLE APPROXIMATE METHOD FORCALCULATING SPANWISE LIFT DISTRI- BUTION ANDAERODYNAMIC INFLUENCE COEFFICIENTS AT SUBSONIC SPEED, Franklin W. Diederich, August 1952 Several approximate methods for calculating lift distributions at subsonic speeds are combined and extended to form a simple step- by-step procedure for calculated symmetric and antisymmetric lift distributions for arbitrary angle-of-attack conditions on swept and unswept conditions. The extension of the method to the cal- culation of dynamic influence coefficients and of spanwise moment distributions is indicated. The results obtained comparefavor- ably with those obtained by more time-consuming theories.

TN 2853 A STUDY OFTHEAPPLICATION OFPOWER SPECTRAL METHODS OF GENERAL- IZED HARMONIC ANALYSIS TO GUST LOADS ONAIRPLANES, Harry Press and Berhard Mazelsky, January 1953 The applicability of someresults from the theory of generalized harmonic analysis (or power-spectral analysis) to the analysis of gust loads on airplanes in continuous rough air is examined. The general relations for linear systems between power spectrums of a random input disturbance and an output response are used to re- late the spectrum of airplane load in rough air to the spectrum of atmospheric gust velocity. The power spectrum of loads is shown to provide a measure of the load intensity in terms of the standard deviations (root meansquare) of the load distribution for an airplane in flight through continuous rough air.

TN 2901 AN ANALYSIS OFTHEFACTORS AFFECTING THELOSSIN LIFT ANDSHIFT IN AERODYNAMIC CENTER PRODUCED BY THEDISTORTION OFA SWEPT WING UNDER AERODYNAMIC LOAD,Charles W. Matthews and Max C. Kurbjun, March 1953 An analysis was madeof factors affecting the loss in lift and the shift in aerodynamic center of a wing produced by the wing bending under aerodynamic loads. The analysis was applied to shell-wing structures in which the spanwise variation in skin thickness is of a character to give a constant spanwise stress under a uniformly distributed load.

TN 3014 CALCULATED SPANWISE LIPT DISTRIBUTIONS ANDAERODYNAMIC INFLUENCE COEFFICIENTS FORUNSWEPT WINGS IN SUBSONIC FLOW, Franklin W.

Diederich and Martin Zlotnick, September 1953 Spanwiselift distributions were calculated for nineteen unswept wings with various aspect ratios and with a variety of angle of attack or twist distributions, including flap and aileron deflec- tions, by meansof the Weissenger method with 8 control points on the semispan. Also calculated were aerodynamic influence co- efficients which pertain to a certain definite set of stations along the span, and several methods were presented for calcula- ting aerodynamic influence coefficients for stations other than those stipulated.

TN 3057 A SIMPLIFIEDMATHEMATICAL MODEL FORCALCULATING AERODYNAMIC LOADING ANDDOWNWASH FORWING-FUSELAGE COMBINATIONS WITHWINGS OF ARBITRARY PLANFORM, Martin Zlotnick add SamuelW. Robinson, Jr., January 1954 For the purpose of calculating the longitudinal loads on the fuselage in subsonic flow, a midwing wlng-fuselage combination with a fuselage of circular cross-section was represented by a system of discrete horseshoe vortices and images. By using this simplified mathematical model_ or the extension of it, given in an appendix for non-midwing configurations with fuselages of arbitrary cross-section, a method was derived for calculating the lift on the fuselage induced by the wing. The method was illustrated by a numerical example. This "induced lift" can be added to the lift on the part of the wing outboard of the fuselage and the lift on the fuselage due to the upwashinduced by the wing to get the total loading on the wing-fuselage combination.

In addition to the method for calculating the induced lift, which is theoretically rigorous, methods for calculating the downwash far behind the wing and for calculating the spanwise lift dis- tribution on the wing for midwing configurations with axisym- metric fuselages were outlined. In calculating the spanwise lift distribution on the wing, approximations were madeto account for the effect of the "additional potential, so that the method was not so rigorous. However, the effect of the additional potantial may easily be incorporated into the method when necessary.

TN 3686 EXPERIMENTAL MEASUREMENTS OF FORCES AND MOMENTS ON A TWO- DIMENSIONAL OSCILLATING WING AT SUBSONIC SPEEDS, Sherman A.

Clevenson and Edward Widmayer, Jr., June 1956 This paper deals with some experiments at subsonic speeds in which a two-dimensional wing was oscillated about the quarter- chord position in a reduced frequency range from 0.15 to 0.35.

The wing used had a span of 24" and a chord of 8" with a 65-010 airfoil section. It was of fabricated construction, having a steel spar with duralumin skin and was mass balanced about the quarter chord to eliminate any mass-inertia force. The only freedom allowed was freed to pitch about the quarter chord. The wing oscillated about a mean _ = 0 ° with maximum amplitude = 2.30 ° .

The experimental tests and results obtained here for lifts and moments about c 1/4 of an oscillating wing in the subsonic region were conducted with the intention of refining experimental tech- niques for use with transonic techniques.

Good agreement of the experimental magnitude of the oscillating lift vector was obtained with the magnitude of the theoretical oscillating lift vectors of Dietze (AAF Translation Reports No.

F-TS-506-RE and F-TS-948-RE, Air Material Cormnand, USAF, March 1947).

A comparison of the experimental damping-moment coefficients with the theoretical values showed the experimental values to be consistently low.

TN 3880 MEASUREMENTS OF LIFT FLUCTUATIONS DUE TO TURBULENCE, P. Lamson, March 1957 For a rigid wing configuration, fluctuations in lift and drag are due to turbulence which may be present in the atmosphere or produced by the airplane itself. In this report the aerodynamic admittance of a wing was obtained from measurements of the lift power spectrum and turbulence spectrum.

If end plates are used so that the fluctuations are correlated across the effective span of the wing, the physical situation can be madeto approximate Lipmann's I-D study. It was found that the aerodynamic admittance approaches Sears' theoretical curve for reduced frequencies higher than about 0.8. Hence, the assumption madein the theory that the influence of the wing on the turbu- lence can be neglected was verified by the measurements.

The smoothing effect of a wing span which was large comparedwith the scale of turbulence was demonstrated. The aerodynamic admit- tance for the airfoil measuredwas less by a large factor than for the case with end plates.

TN 3954 A THEORY FORTHELATERAL RESPONSE OF AIRPLANES TO RANDOM ATMOS- PHERIC TURBULENCE, John M. Eggleston, May 1957 This report presents a method of utilizing the statistical forces and momentsderived in NACA TN 3805 and NACA TN 3964 by John M.

Eggleston for the calculation of the lateral motion of the air- plane in any lateral degree of freedom due to atmospheric turbu- lence. The governing equations were derived and the power spectra solutions of the motions were given in terms of linear airplane transfer functions, statistical force and momentcoefficients, and power spectra of the three orthogonal componentsof atmos- pheric gust velocity. Solutions for three airplanes were shown with trends and possible simplifications noted. These were heavy rather than light aircraft. The theory in this report was comparedwith earlier theory.

TN 4240 SOME MEASUREMENTS OFAERODYNAMIC FORCES ANDMOMENTS AT SUBSONIC SPEEDS ONA RECTANGULAR WINGOF ASPECT RATIO2 OSCILLATING ABOUT THEMIDCHORD, EdwardWidmayer, Jr., ShermanA. Clevenson and SumnerA. Leadbetter, May 1958 This paper presents someexperimental measurementsof the oscillatory aerodynamic forces and momentsacting on a rectangular wing of AR 2 which was oscillated about the midchord. These co- efficients are presented for a range of reduced frequency from 0.15 to 1.32 and for a range of Machnumbers from 0.15 to 0.81.

The Re for these tests were from 0.60 x 106 to 9.21 x 106. This testing program is aimed at filling the need for experimental measurementsof oscillating air forces because of their signifi- cance in flutter. Tests were conducted in the NACA2 x 4 foot flutter research tunnel.

The experimental results for the measured aerodynamic forces and momentsare presented in tabular form as well as in the form of graphs. This study indicated that the aerodynamic coefficient possibly was infuenced to someextent by Machnumber and Re but the effect was not first order and was probably within the accu- racy of the experiment. Graphs are shownwith the followiDg parameters in terms of k (k-reduced frequency parameter, wc/2v) or l/k; negative damping-moment coefficient, theoretical and ex- perimental lift coefficient, lift phase angles, theoretical and experimental in-phase momentcomponentcoefficients, damping momentcoefficients.

Comparisonsof the experimental data obtained here showsgood agreementwith published experimental data. Two dimensional flow theory yielded inadequate results while coefficients given by AR theories was in generally good agreement.

NACA Technical Notes Dealing with Aerodynamic Loads But Not Judged Applicable to Light Aircraft TN 757 A STUDY OF UNSYMMETRICAL-LOADING CONDITIONS_ Henry A. Pearson_ April 1940 TN 758 MEASUREMENTS AND ANALYSIS OF THE MOTION OF A CANARD AIRPLANE MODEL IN GUSTS_ Philip Donely_ Harold B. Pierce_ and Philip W. Pepoon_ April 1940 TN 1008 ANALYSIS AND MODIFICATION OF THEORY FOR IMPACT OF SEAPLANES ON WATER_ Wilbur L. Mayo 3 December 1945 TN 1034 BENDING-TORSION FLUTTER CALCULATIONS MODIFIED BY SUBSONIC COMPRES- SIBILITY CORRECTIONS_ J. E. Garrick_ May 1946 TN 1057 GENERAL TANK TEST OF A i/I0 SIZE MODEL OF THE HULL OF THE BOEING XPBB-I FLYING BOAT LANGLEY TANK MODEL 175_ Douglas A. King and Mary B. Hill_ July 1946 TN 1140 MEASUREMENTS OF LANDING-GEAR FORCES AND HORIZONTAL-TAlL LOADS IN LANDING TESTS OF A LARGE BOMBER-TYPE AIRPLANE_ John R. Westfall_ September 1946 TN 1152 FLIGHT INVESTIGATION OF THE EFFECT OF A LOCAL CHANGE IN WING CON- TOUR ON CHORDWISE PRESSURE DISTRIBUTION AT HIGH SPEEDS_ Richard E.

Adams and Norman S. Silsby_ September 1946 TN 1158 FLUTTER AND OSCILLATING AIR-FORCE CALCULATIONS FOR AN AIRFOIL IN TWO-DIMENSIONAL SUPERSONIC FLOW_ I. E. Garrick and S. I. Rubinow 3 October 1946 TN 1166 VARIATION OF HYDRODYNAMIC IMPACT LOADS WITH FLIGHT-PATH ANGLE FOR A PRISMATIC FLOAT AT 0 ° AND -3 ° TRIM AND WITH A 22½ ° ANGLE OF DEAD RISE_ Sidney A. Batterson_ April 1947 TN 1181 WING PRESSURE-DISTRIBUTION MEASU_ENTS UP TO 0.866 MACH NUMBER IN FLIGHT ON A JET-PROPELLED AIRPLANE, Harvey H. Brown and Lawrence A. Clousing 3 March 1947 TN 1202 MEASUREMENTS OF THE PRESSURE DISTRIBUTION ON THE HORIZONTAL TAlL SURFACE OF A TYPICAL PROPELLER-DRIVEN PURSUIT AIRPLANE IN FLIGHT.

II - THE EFFECT OF ANGLE OF SIDESLIP AND PROPELLER OPERATION, Melvin Sadoff and Lawrence A. Clousing, May 1947 TN 1268 AN APPLICATION OF STATISTICAL DATA IN THE DEVELOPMENT OF GUST-LOAD CRITERIONS_ Reginald B. Bland and T. D. Reisert, April 1947 TN 1295 WIND-TUNNEL INVESTIGATION OF THEAIR LOAD DISTRIBUTION ONTWO COMBINATIONS OFLIFTING SURFACE ANDFUSELAGE_ Carl A. Sandahl and SamuelD. Vollo_ May 1947 TN 1321 AN IMPROVED METHOD FORCALCULATING THEDYNAMIC RESPONSE OF FLEXI- BLEAIRPLANES TO GUSTS_ Abbott A. Putnam_May 1947 HYDRODYNAMIC IMPACT LOADS IN SMOOTH WATER FORA PRISMATIC FLOAT TN 1325 HAVING AN ANGLE OFDEAD RISE OF 30°_ Robert W. Miller and Samuel Leshnover_ June 1947 EFFECT OF CRITICAL MACHNUMBERAND FLUTTER ONMAXIMUM POWER LOADING TN 1330 OFDUCTED FANS_ Arthur A. Regier_ John G. Barmby_and Harvey H.

Hubbard_June 1947 TN 1351 COMPARISON BETWEEN THEMEASURED ANDTHEORETICAL SPAN LOADINGS ONA MODERATELY SWEPT-FORWARD ANDA MODERATELY SWEPT-BACK SEMISPAN WING_ Robert A. Mendelsohn and Jack D. Brewer3 July 1947 TN 1363 A THEORETICAL INVESTIGATION OF HYDRODYNAMIC IMPACT LOADS ON SCALLOPED-BOTTOM SEAPLANES ANDCOMPARISON WITHEXPERIMENT_ Benjamin Milwitzky_ July 1947 TN 1398 SOLUTIONS FORHYDRODYNAMIC IMPACT FORCE ANDRESPONSE OF A TWO-MASS SYSTEM WITHAN APPLICATION TOAN ELASTIC AIRFRAME_ Wilbur L. Mayo_ August 1947 TN 1437 IMPACT THEORY FORSEAPLANE LANDINGS_ Stanley U. Benscoter_ October TN 1484 THEORETICAL LIFT DISTRIBUTION ANDUPWASH VELOCITIES FORTHINWINGS AT SUPERSONIC SPEEDS_ John C. Evvard and Richard Turner_ November THEINFLUENCE OFVERYHEAVY FUSELAGE MASS LOADINGS ANDLONG NOSE TN 1510 LENGTHS UPON OSCILLATIONS IN THESPIN_Ralph W. Stone_ Jr._ and Walter J. Klinar 3 January 1948 TN 1528 TESTS OFA 45° SWEPTBACK-WING MODEL IN THELANGLEY GUST TUNNEL_ Harold B. Pierce_ February 1948 TN 1563 EFFECT OFPARTIALWING LIFT IN SEAPLANE LANDING IMPACT_ Stanley U.

Benscoter_ April 1948 TN 1569 A METEOROLOGICAL MEASURE OFMAXIMUM GUST VELOCITIES IN CLOUDS_ I. I.

Gringorten and H. Press_ April 1948 TN 1584 AN EVALUATION OF SOME APPROXIMATE METHODS OF COMPUTING LANDING STRESSES IN AIRCRAFT_ Elbridge Z. Stowell_ John C. Houbolt_ and S. B. Batdorf_ May 1948 AN ANALYSIS OF THEVARIATION WITHALTITUDE OF EFFECTIVE GUST TN 1628 VELOCITY IN CONVECTIVE-TYPE CLOUDS_ H. B. Tolefson_ June 1948 A STATISTICAL ANALYSIS OF GUST-VELOCITY MEASUREMENTS AS AFFECTED TN 1645 BYPILOTSANDAIRPLANES_ Harry Press_ June 1948 CHORDWISE ANDSPANWISE LOADINGS MEASURED AT LOW SPEEDS ONA TRIANG- TN 1650 ULARWING HAVING AN ASPECT RATIOOF 2 ANDA_N NACA 0012 AIRFOIL SECTION_ Bradford H. Wickj June 1948 METHOD FORCALCULATION OF PRESSURE DISTRIBUTIONS ONTHIN CONICAL TN 1659 BODIES OF ARBITRARY CROSS SECTION IN SUPERSONIC STREAM_ Stephen H. Malsen_ July 1948 LOAD DISTRIBUTIONS DUETO STEADY ROLLANDPITCHFORTHINWINGS AT TN 1689 SUPERSONIC SPEEDS_ W. E. Moeckel and J. C. Evvard_ August 1948 THEORETICAL ANDEXPERIMENTAL WING-TIPS ACCELERATIONS OF A SMALL TN 1690 FLYINGBOAT DURING LANDING IMPACTS_ Daniel Savitsky_ September 1948 ANALYSIS OFPLANING DATA FORUSE IN PREDICTING HYDRODYNAMIC IMPACT TN 1694 LOADS_ Margaret F. Steiner_ August 1948 GUST-TUNNEL INVESTIGATION OF A 45° SWEPTFORWARD-WING MODEL_ Harold TN 1717 B. Pierce_ October 1948 FLIGHTMEASUR_ENTS OF BUFFETING FLIGHTLOADS_ Allen R. Stokke and TN 1719 William S. Aiken_ Jr._ October 1948 THEORETICAL METHOD FOR SOLUTION OF AERODYNAMIC FORCES ON THIN TN 1736 WINGS IN NONUNIFORM SUPERSONIC STREAM WITH AN APPLICATION TO TAIL SURFACES_ Harold Mirels_ November 1948 A RAPID GRAPHICAL METHOD FOR COMPUTING THE PRESSURE DISTRIBUTION AT TN 1768 SUPERSONIC SPEEDS ON A SLENDER ARBITRARY BODY OF REVOLUTION_ Jim Rodgers Thompson_ January 1949 THEORETICAL BASIC SPAN LOADING CHARACTERISTICS OF WINGS WITH ARBI- TN 1772 TRARY SWEEP_ ASPECT RATIO AND TAPER RATIO (Superseded by Report 921)_ Victor I. Stevens_ December 1948 HYDRODYNAMIC IMPACT LOADS IN SMOOTH WATER FOR A PRISMATIC FLOAT TN 1775 HAVING AN ANGLE OF DEAD RISE OF 40°_ Philip M. Edge 3 Jr._ January HYDRODYNAMIC IMPACT LOADS IN ROUGH WATER FOR A PRISMATIC FLOAT TN 1776 HAVING AN ANGLE OF DEAD RISE OF 30°_ Robert W. Miller_ December 1948 COMPARISON OF OVER-ALL IMPACT LOADS OBTAINED DURING SEAPLANE LAND- TN 1781 ING TESTS WITH LOADS PREDICTED BY HYDRODYNAMIC THEORY_ Margaret F.

Steiner_ January 1949 TN 1794 GUST-TIYNNEL INVESTIGATION OFA WING MODEL WITHSEMICHORD LINE SWEPT BACK 30°_ ThomasD. Reisert_ January 1949 TN 1881 COMPARISON OFPITCHING MOMENTS OBTAINED DURING SEAPLANE LANDINGS WITHVALUES PREDICTED BY HYDRODYNAMIC IMPACT THEORY_ Gilbert A.

Haines_ May 1949 TN 1893 EFFECT OF CENTRIFUGAL FORCE ONFLUTTER OFUNIFORM CANTILEVER BEAM AT SUBSONIC SPEEDS WITHAPPLICATION TOCOMPRESSOR ANDTURBINE BLADES_ Alexander Mendelson_ June 1949 TN 1917 AN ANALYSIS OF THERELATION BETWEEN HORIZONTAL TI_MPERATURE VARIA- TIONSANDMAXIMVM EFFECTIVE GUST VELOCITIES IN THUNDERSTORMS_ H.

Press and J. K. Thompson_ July 1949 TN 1926 THEAPPLICATION OFTHESTATISTICAL THEORY OF EXTREME VALUES TO GUST-LOAD PROBLEMS (Superseded by Technical Report 991)_ Harry Press_ November1949 TN 1937 A FLIGHTINVESTIGATION OF THEEFFECTS OF COMPRESSIBILITY ONAPPLIED GUST LOADS_ E. T. Binckley and Jack Funk_ August 1949 TN 1973 THEORETICAL SPANWISE LIFT DISTRIBUTIONS OFLOW-ASPECT-RATIO WINGS AT SPEEDS BELOW ANDABOVE THESPEED OF SOUND_ Franklin W. Diederich and Martin Zlotnick_ October 1949 TN 1991 THEORETICAL LOADING AT SUPERSONIC SPEEDS OF FLAT SWEPT-BACK WINGS WITHINTERACTING TRAILINGLEADING ANDLEADING EDGES_ Doris Cohen_ December1949 TN 2007 THELOAD DISTRIBUTION DUETO SIDESLIPONTRIANGULAR_ TRAPEZOIDAL_ ANDRELATED PLANFORMS IN SUPERSONIC FLOW_ Arthur L. Jones and Alberta Alksne_ January 1950 TN 2011 SPANWISE LOADING FORWINGS ANDCONTROL SURFACES OFLOW ASPECT RATIO_ John DeYoung_ January 1950 TN 2015 WATER LANDING INVESTIGATION OFMODEL HAVING A HEAVY BEAM LOADING ANDA 30° ANGLE OF DEAD RISE_ Sidney A. Batterson and A. Ethelda McArver_ February 1950 TN 2035 A METHOD OFDETERMINING THEEFFECT OF AIRPLANE STABILITYONTHE GUST LOAD FACTOR_ Bernard Mazelsky and Franklin W. Diederich_ February 1950 TN 2036 CHARTS OF AIRPLANE ACCELERATION RATIOFORGUSTS OF ARBITRARY SHAPE_ Bernard Mazelsky_ February 1950 TN 2060 A RECURRENCE MATRIXSOLUTION FORTHEDYNAMIC RESPONSE OFAIRCRAFT IN GUSTS_ John C. Houbolt_ March 1950 A COMPARISON OF THEORETICAL ANDEXPERIMENTAL WING BENDING MOMENTS TN 2063 DURING SEAPLANE LANDINGS_ Kenneth F. Merten_ Jose L. Rodriguez_ and Edgar B. Beck 3 April 1950 TN 2121 STUDY OF THEEFFECTS OF SWEEP ONTHEFLUTTER OF CANTILEVER WINGS_ J. G. Barmby_H. J. Cunningham_ and I. E. Garrick_ June 1950 TN 2194 THENACA OIL-DAMPED V-G RECORDER_ Israel Taback_ October 1950 GUST-TUNNEL INVESTIGATION OF A WING MODEL WITHSEMICHORD LINE TN 2204 SWEPT BACK 60°_ Harold B. Pierce_ October 1950 TN 2265 NACAVGH RECORDER_ NormanR. Richardson_ February 1951 THEORETICAL SYMMETRIC SPAN LOADING DUETOFLAPDEFLECTION FORWINGS TN 2278 OF ARBITRARY PLANFORMATSUBSONIC SPEEDS (Superseded by TR i071)_ John DeYoung_ January 1951 TN 2330 WATER-LANDING INVESTIGATION OF A MODEL HAVING HEAVY BEAM LOADINGS AND0° ANGLE OFDEAD RISE_ A. Ethelda McArver_ April 1951 THEORETICAL STUDY OF SOME METHODS FORINCREASING THESMOOTHNESS TN 2416 OFFLIGHTTHROUGH ROUGH AIR_ William H. Phillips and Christopher C. Kraft_ Jr._ July 1951 ANALYSIS OF PURE-BENDING FLUTTER OFA CANTILEVER SWEPT WING AND TN 2461 ITS RELATION TO BENDING-TORSION FLUTTER_ H. J. Cunningham_ September INVESTIGATION OF THEAIR-COMPRESSION PROCESS DURING DROP TESTS OF TN 2477 AN OLEO-PNEUMATIC LANDING GEAR_ JamesH. Walls_ September 1951 TN 2490 FLIGHTINVESTIGATION OF SOME FACTORS AFFECTING THECRITICALTAIL LOADS ONLARGE AIRPLANES_ Harvey H. Brown_ September 1951 FLIGHTINVESTIGATION OF THEEFFECT OF ATMOSPHERIC TURBULENCE ONTHE TN 2498 CLIMBPERFORMANCE OF AN AIRPLANE_ Harry Press and Herbert C.

McClanahan 3 Jr._ October 1951 A FLIGHTINVESTIGATION OF THEEFFECT OF CENTER-OF-GRAVITY LOCATION TN 2575 ONGUST LOADSjJack Funk and Earle T. Binckley_ December1951 SUMMARY OFACCELERATION ANDAIRSPEED DATAFROM COMMERCIAL TRANSPORT TN 2625 AIRPLANES DURING THEPERIOD FROM 1933 TO 1945_ Walter G. Walker and Roy Steimer_ February 1952 ESTIMATION OF THEMAXIMUMANGLE OF SIDESLIPFORDETERMINATION OF TN 2633 VERTICAL TAlL LOADS IN ROLLING MANEUVERS (Superseded by TR i136)_ Ralph W. Stone_ Jr._ February 1952 TN 2643 SPAN LOAD DISTRIBUTIONS RESULTING FROM ANGLE OF ATTACK_ ROLLING_ AND PITCHING FOR TAPERED SWEPTBACK WINGS WITH STREAMWISE TIPS_ SUPERSONIC LEADING AND TRAILING EDGES_ John C. Martin and Isabella Jeffreys_ July 1952 TN 2657 SOME EFFECTS OF FREQUENCY ON THE CONTRIBUTION OF A VERTICAL TAlL TO THE FREE AERODYNAMIC DAMPING OF A MODEL OSCILLATING IN YAW_ J. D. Bird_ L. R. Fisher_ and S. M. Hubbard_ April 1952 TN 2663 THE GUST AND GUST-LOAD EXPERIENCE OF A TWIN-ENGINE LOW-ALTITUDE TRANSPORT AIRPLANE IN OPERATION ON A NORTHERN TRANSCONTINENTAL ROUTE_ Harry Press and Robert L. McDougal_ April 1952 TN 2735 AN ANALYSIS OF THE NORMAL ACCELERATIONS AND AIRSPEEDS OF A TWO ENGINE TYPE OF TRANSPORT AIRPLANE IN COMMERCIAL OPERATIONS ON ROUTES IN THE CENTRAL UNITED STATES FROM 1948 TO 1950_ Walter G.

Walker and Paul W. J. Schumacher_ July 1952 TN 2755 ANALYSIS OF LANDING-GEAR BEHAVIOR (Been Replacad by TR I154)_ Benjamin Milwitzky and Francis E. Cook_ August 1952 TN 2757 EXPERIMENTAL STUDIES OF NOISE FROM SUBSONIC JETS IN STILL AIR_ Leslie W. Lassiter and Harvey H. Hubbard_ August 1952 TN 2763 GUST-RESPONSE ANALYSIS OF AN AIRPLANE INCLUDING WING BENDING FLEXIBILITY (Superseded by Report I181)_ John C. Houbolt and Eldon E. Kordes_ August 1952 TN 2780 FLIGHT INVESTIGATION OF TRANSIENT WING RESPONSE ON A FOUR ENGINE BOMBER AIRPLANE IN ROUGH AIR WITH RESPECT TO CENTER OF GRAVITY ACCELERATIONS_ Harry C. Mickleboro_ Richard B. Fahrer_ and C. C.

Shufflebarger_ September 1952 TN 2798 THEORETICAL ANALYSIS OF HYDRODYNAMIC IMPACT OF A PRISMATIC FLOAT HAVING FREEDOM IN TRIM_ Herbert F. Hardrath and Elmer C. Utley_ Jr._ October 1952 TN 2813 THEORY AND PROCEDURE FOR DETERMINING LOADS AND MOTIONS IN CHINE- IMMERSED HYDRODYNAMIC IMPACTS OF PRISMATIC BODIES_ Emanuel Schnit- zer_ November 1952 TN 2814 THE APPLICATION OF PLANING CHARACTERISTICS TO THE CALCULATION OF THE WATER LANDING LOADS AND MOTIONS OF SEAPLANES OF ARBITRARY CONSTANT CROSS SECTION_ Robert F. Smiley_ November 1952 TN 2815 A THEORETICAL INVESTIGATION OF THE EFFECT OF PARTIAL WING LIFT ON HYDRODYNAMIC LANDING CHARACTERISTICS OF V-BOTTOM SEAPLANES IN STEP IMPACTS_ Joseph L. Sims and Emanuel Schnitzer_ November 1952 WATER PRESSURE DISTRIBUTIONS DURING LANDINGS OF A PRISMATIC TN 2816 MODEL HAVING AN ANGLE OF DEAD RISE OF 22-1/2 ° ANDBEAM LOADING COEFFICIENTS OF 0.48 AND0.97_ Robert F. Smiley_ November1952 TN 2831 SPAN LOAD DISTRIBUTIONS RESULTING FROM CONSTANT ANGLE OF ATTACK_ STEADY ROLLING VELOCITY_ STEADY PITCHING VELOCITY_ ANDCONSTANT VERTICAL ACCELERATION FORTAPERED SWEPTBACK WINGS WITHSTREAMWISE TIPS_ Margery E. Hannahand Kenneth Margolis_ December1952 AN ANALYSIS OF NORMAL ACCELERATIONS ANDAIRSPEEDS OF ONETYPEOF TN 2833 TWINENGINE TRANSPORT AIRPLANE IN COMMERCIAL OPERATIONS OVER A NORTHERN TRANSCONTINENTAL ROUTE_ Roy Steiner_ November1952 TN 2877 ONTHEUSEOFA DAMPED SINE-WAVE ELEVATOR MOTION FORCOMPUTING THE DESIGN MANEUVERING HORIZONTAL-TAlL LOAD_ Melvin-Sadoff_ January TN 2889 ESTIMATION OF GYRODYNAMIC IMPACT LOADS ANDPRESSURE DISTRIBUTIONS ONBODIES APPROXIMATING ELLIPTICALCYLINDERS WITHSPECIAL REFERENCE TO WATER LANDINGS OF HELICOPTERS_ EmanuelSchnitzer and Melvin E. Hathaway_April 1953 TN 2897 EVALUATION OF GUST RESPONSE CHARACTERISTICS OF SOME EXISTINGAIR- CRAFT WITHWINGBENDING FLEXIBILITY INCLUDED_ Eldon E. Kordes and John C. Houbolt_ February 1953 TN 2898 THEORETICAL CALCULATION OF PRESSURE DISTRIBUTION_ SPAN LOADING_ AND ROLLING MOMENT DUETO SIDESLIPAT SUPERSONIC SPEEDS FORTHIN SWEPT- BACK TAPERED WINGS WITHSUPERSONIC TRAILINGEDGES ANDWING TIPS PARALLEL TO THEAXIS OFWINGSYMMETRY_ Kenneth Margolis_ Windsoner L. Sherman_and Margery E. Hannah_February 1953 TN 2900 THECALCULATION OF PRESSURE ONSLENDER AIRPLANES IN SUBSONIC AND SUPERSONIC FLOW_ Max. A. Heaslet and Harvard Lomax_March 1953 TN 2925 LIFT DEVELOPED ONUNRESTRAINED RECTANGULAR WINGS ENTERING GUSTS AT SUBSONIC ANDSUPERSONIC SPEEDS_ Harvard Lomax_April 1953 TN 2926 STATICFORCE DEFLECTION CHARACTERISTICS OF SIX AIRCRAFT TIRES UNDER COMBINED LOADING_ Walter B. Horne 3 May 1953 TN 2927 DEFLECTION OF DELTA WINGS HAVING A CARRY THROUGH BAYCHORD SMALLER THAN THEWING ROOT CHORD_ Roger W. Peters and Manuel Stein_ May 1953 TN 2932 WATER LANDING INVESTIGATION OF A FLAT BOTTOM V-STEPMODEL AND COMPARISON WITHA THEORY INCORPORATING PLANING DATA_ Robert W.

Miller_ May 1953 TN 2953 AN INVESTIGATION OF THEEXPERIMENTAL AERODYNAMIC LOADING ONA MODEL HELICOPTER ROTOR BLADE_ John R. Mayer and GaetanoFalabella_ Jr._ May 1953 TN 2990 FLIGHTMEASUREMENTS ANDANALYSIS OF HELICOPTER NORMAL LOAD FACTORS IN MANEUVERS_ F. B. Gustafson and Almer D. Crim_ August 1953 TN 2991 ACCELERATIONS ANDPASSENGER HARNESS LOADS MEASURED IN FULLSCALE LIGHTAIRPLANE CRASHES_ A. Martin Eiband_ Scott H. Simpkinso_and Dugald D. Black_ August 1953 TN 2993 CALIBRATION OF STRAIN GAGE INSTALLATIONS IN AIRCRAFT STRUCTURES FOR THEMEASUREMENT OFFLIGHTLOADS_ T. H. Skopinski_ William S. Aiken_ Jr._ and Wilber B. Huston_ August 1953 TN 3030 A METHOD FORCALCULATING THESUBSONIC STEADY-STATE LOADING ONAN AIRPLANE WITHA WING OFARBITRARY PLANFORM ANDSTIFFNESS_ W. L.

Grey and K. M. Schenk_December1953 TN 3037 COUNTING METHODS ANDEQUIPMENT FORMEAN-VALUE MEASUREMENTS IN TURBULENCE RESEARCH_ H. W. Liepmann and M. S. Robinson_ October USEOF TWO-DIMENSIONAL DATAIN ESTIMATING LOADS ONA 45° SWEPTBACK TN 3040 WING WITHSLATS ANDPARTIAL-SPAN FLAPS_ Lynn U. Hunton and Harry A. James_November1953 TN 3041 SUMMARY OF REVISED GUST-VELOCITY DATAOBTAINED FROM V-G RECORDS TAKEN ONCIVIL TRANSPORT AIRPLANES FROM 1933 TO 1950_ Walter G.

Walker_ November1953 TN 3046 THEORETICAL CALCULATIONS OF THEEFFECTS OFFINITE SIDESLIPAT SUPERSONIC SPEEDS ONTHESPAN LOADING ANDROLLING MOMENT FOR FAMILIESOF THIN SWEPTBACK TAPERED WINGS AT AN ANGLE OF ATTACK_ Windsor L. Shermanand Kenneth Margolis# November1953 TN 3051 GUST LOADS ANDOPERATING AIRSPEEDS OF ONETYPEOFFOUR-ENGINE TRANSPORT AIRPLANE ONTHREE ROUTES FROM 1949 TO 1953_ Walter G.

Walker_ November1953 TN 3080 MEASUREMENT ANDANALYSIS OFWING ANDTAlL BUFFETING LOADS ONA FIGHTER-TYPE AIRPLANE_ Wilber B. Huston and T. H. Skopinski_ May TN 3096 THEORETICAL PREDICTION OF PRESSURE DISTRIBUTIONS ONNONLIFTING AIR- FOILS AT HIGHSUBSONIC SPEEDS_ John R. Spreiter and Alberta Alksne_ March 1954 TN 3116 CORRELATIONS INVOLVING PRESSURE FLUCTUATIONS IN HOMOGENEOUS TURBU- LENCE_ Mahinder S. Uberoi_ January 1954 TN 3120 SPAN LOAD DISTRIBUTIONS RESULTING FROM CONSTANT VERTICAL ACCELERA- TION FORTHIN SWEPTBACK TAPERED WINGS WITHSTREAMWISE TIPS SUPER- SONIC LEADING ANDTRAILINGEDGES_ Isabella J. Cole and Kenneth Margolis_ January 1954 TN 3131 ON THE KERNEL FUNCTION OF THE INTEGRAL EQUATION RELATING THE LEFT AND DOWNWASH DISTRIBUTIONS OF OSCILLATING FINITE WINGS IN SUBSONIC FLOW_ C. E. Watkins_ H. L. Runyan_ and D. S. Woolston_ January 1954 TN 3160 A CALCULATION STUDY OF WING-AILERON FLUTTER IN TWO DEGREES OF FREEDOM FOR TWO-DIMENSIONAL SUPERSONIC FLOW_ Donald S. Woolston and Vera Huckel_ April 1954 TN 3161 AN INVESTIGATION OF THE USE OF ROCKET-POWERED MODELS FOR GUST-LOAD STUDIES WITH AN APPLICATION TO A TAILLESS SWEPTWING MODEL AT TRAN- SONIC SPEEDS_ A. James Vital% H. Press_ and C. C. Shufflebarger_ June 1954 TN 3194 STATISTICAL MEASUR_ENTS OF CONTACT CONDITIONS OF 478 TRANSPORT- AIRPLANE LANDINGS DURING ROUTINE DAYTIME OPERATIONS_ Norman S.

Silsby_ June 1954 TN 3220 AERODYNAMIC LOADS ON A LEADING-EDGE FLAP AND A LEADING-EDGE SLAT ON THE NACA 64A010 AIRFOIL SECTION_ John A. Kelly and George B.

McCullough_ June 1954 TN 3246 AN EXPERIMENTAL INVESTIGATION OF WHEEL SPIN-UP DRAG LOADS_ Dean C.

Lindquist and Dexter M. Potter_ September 1954 TN 3250 AN EXPERIMENTAL INVESTIGATION OF THE EFFECT OF WHEEL PREROTATION ON LANDING-GEAR DRAG LOADS_ Dexter M. Potter_ October 1954 TN 3290 ON THE MINIMIZATION OF AIRPLANE RESPONSES TO RANDOM GUSTS_ Murray Tobak_ October 1957 TN 3301 COMPARISON OF FLUTTER CALCULATIONS USING VARIOUS AERODYNAMIC COEFFICIENTS WITH EXPERIMENTAL RESULTS FOR SOME RECTANGULAR CANTI- LEVER WINGS AT MACH NUMBER 1.3_ Herbert C. Nelson and Rubby A.

Rainey_ November 1954 TN 3312 INITIAL EXPERIMENTS ON FLUTTER OF UNSWEPT CANTILEVER WINGS AT MACH NUMBER 1.3_ W. J. Tuorila_ John E. Baker_ and Arthur A. Regier_ November 1954 TN 3319 OPERATING CHARACTERISTICS OF AN ACCELERATION RESTRICTOR AS DETER- MINED BY MEANS OF A SlMULATOR_ Arthur Assadourian_ December 1954 TN 3354 GUST EXPERIENCE OF A HELICOPTER AND AN AIRPLANE IN FORMATION FLIGHT_ Almer D. Crim_ December 1954 TN 3358 GUST-LOAD AND AIRSPEED DATA FROM ONE TYPE OF FOUR-ENGINE AIRPLANE ON FIVE ROUTES FROM 1947 TO 1954_ Walter G. Walker_ January 1955 TN 3362 ESTIMATES OF PROBABILITY DISTRIBUTION OF ROOT-MEAN-SQUARE GUST VELOCITY OF ATMOSPHERIC TURBULENCE FROM OPERATIONAL GUST-LOAD DATA BY RANDOM-PROCESS THEORY_ Harry Press_ May T. Meadows_ and Ivan Hadlock_ March 1955 TN 3365 AN ANALYSIS OF ACCELERATIONS_ AIRSPEED AND GUST VELOCITIES FROM THREE COMMERCIAL OPERATIONS OF ONE ]_PE OF MEDIUM-ALTITUDE TRANS- PORT AIRPLANE_ T. L. Colema% M. R. Copp_ W. G. Walker_ and Jerome N. Engel_ March 1955 TN 3366 A METHOD FOR STUDYING THE TRANSIENT BLADE-FLAPPING BEHAVIOR OF LIFTING ROTORS AT EXTREME OPERATING CONDITIONS_ Alfred Gessow and Almer D. Crim_ January 1955 TN 3370 A SIMPLIFIED METHOD FOR CALCULATING AEROELASTIC EFFECTS ON THE ROLL OF AIRCRAFT_ J. M. Hedgepath_ P. G. Waner_ Jr._ and R. J.

Kell_ March 1955 TN 3376 THE EFFECT OF CONTROL STIFFNESS AND FORWARD SPEED ON THE FLUTTER OF A 1/10-SCALE DYNAMIC MODEL OF A TWO-BLADE JET-DRIVEN HELICOPTER ROTOR_ George W. Brooks and Maurice A. Sylvester_ April 1955 TN 3395 ON THE CALCULATION OF THE I.P OSCILLATING AERODYNAMIC LOADS ON SIN- GLE-ROTATION PROPELLERS IN PITCH ON TRACTOR AIRPLANES_ Vernon L.

Rogallo and Paul F. Yaggy_ May 1955 TN 3426 AN EXPERIMENTAL STUDY OF ORIFICE COEFFICIENTS_ INTERNAL STRUT PRESSURES_ AND LOADS ON A SMALL OLEO-PNEI_MATIC SHOCK STRUT_ James H. Walls_ April 1955 TN 3434 A STUDY OF NORMAL ACCELERATIONS AND OPERATING CONDITIONS EXPERIENCED BY HELICOPTERS IN COMMERCIAL AND MILITARY OPERATIONS_ Marlin E.

Haze% April 1955 TN 3465 THEORETICAL INVESTIGATION OF FLUTTER OF TWO-DIMENSIONAL FLAT PANELS WITH ONE SURFACE EXPOSED TO SUPERSONIC POTENTIAL FLOW_ Herbert C. Nelson and Herbert J. Cunningham_ July 1955 TN 3467 EFFECT OF INTERACTION ON LANDING-GEAR BEHAVIOR AND DYNAMIC LOADS IN A FLEXIBLE AIRPLANE STRUCTURE_ Francis E. Cook and Benjamin Milwitzky_ August 1955 TN 3475 AN ANALYSIS OF ACCELERATION_ AIRSPEED_ AND GUST-VELOCITY DATA FROM ONE TYPE OF FOUR-ENGINE TRANSPORT AIRPLANE OPERATED OVER TWO DOMESTIC ROUTES_ Martin R. Corp and Thomas L. Coleman_ October TN 3479 ANALYSIS OF THE HORIZONTAL-TAIL LOADS MEASURED IN FLIGHT ON A MULTIENGINE JET BOMBER_ William S. Aiken_ Jr._ and Bernard Wiener_ September 1955 TN 3484 ON SPECTRAL ANALYSIS OF RUNWAY ROUGHNESS AND LOADS DEVELOPED DURING TAXIING_John C. Houbolt_ JamesH. Walls_ and Robert T. Smiley_ July 1955 TN 3492 DETERMINATION OF INFLOW DISTRIBUTIONS FROM EXPERIMENTAL AERODYNAMIC LOADING ANDBLADE-MOTION DATA ONA MODEL HELICOPTER ROTOR IN HOVER- ING ANDFORWARD FLIGHT_GaetanoFalabella_ Jr._ and John R. Meyer_ Jr._ November1955 TN 3500 CORRECTION OF ADDITIONAL SPAN LOADINGS COMPUTED BYTHEWEISSINGER SEVEN-POINT METHOD FORMODERATELY TAPERED WINGS OF HIGHASPECT RATIO_ John DeYoungand Walter H. Barling_ Jr._ July 1955 THEPROPER COMBINATION OF LIFT LOADING FORLEASTDRAG ONA SUPER- TN 3533 SONIC WING_ Frederick C. Grant_ October 1955 FLIGHTINVESTIGATION OF THESURFACE-PRESSURE DISTRIBUTION ANDTHE TN 3535 FLOW FIELD AROUND A CONICAL ANDTWO SPHERICAL NON-ROTATING FULL- SCALE PROPELLER SPINNERS_ Jerome B. Hammack_ Milton L. Windler_ and Elwood F. Scheithauer_ September 1955 TN 3538 SUMMARY OFDERIVED GUST VELOCITIES OBTAINED FROM MEASUREMENTS WITH- IN THUNDERSTORMS_ Harold B. Tolefson_ October 1955 SOME EFFECTS OF SYSTEM NONLINEARITIES IN THEPROBLEM OFAIRCRAFT TN 3539 FLUTTER_ D. S. Woolston_ H. L. Runyan_and T. A. Byrdsong_ October A REEVALUATION OF GUST-LOAD STATISTICS FORAPPLICATIONS IN SPECTRAL TN 3540 CALCULATIONS_ Harry Press and May T. Meadows_ August 1955 TN 3541 A METHOD FOROBTAINING STATISTICAL DATAONAIRPLANE VERTICAL VELOCITY AT GROUND CONTACT FROM MEASUREMENTS OF CENTER-OF-GRAVITY ACCELERATION_ Robert C. Dreher_ February 1956 TN 3597 ANALYSIS OF A VANE-CONTROLLED GUST-ALLEVIATION SYSTEM_ Robert W.

Boucher and Christopher C. Kraft_ Jr._ April 1956 THEORETICAL SPAN LOAD DISTRIBUTIONS ANDROLLING MOMENTS FORSIDE- TN 3605 SLIPPINGWINGS OF ARBITRARY PLANFORM IN INCOMPRESSIBLE FLOW_ M. J. Queijo_ December1955 TN 3608 HYDRODYNAMIC IMPACT LOADS IN SMOOTH WATER FORA PRISMATIC FLOAT HAVING ANANGLE OF DEAD RISE OF i0°_ Philip M. Edge_Jr._ January TN 3610 COMPARISON OF LANDING-IMPACT VELOCITIES OFFIRST ANDSECOND WHEEL TO CONTACT FROM STATISTICAL MEASUREMENTS OF TRANSPORT AIRPLANE LANDINGS_ Eziaslav N. Harrin_ February 1956 TN 3612 INITIAL RESULTS OF A FLIGHTINVESTIGATION OFA GUST-ALLEVIATION SYSTEM_ Christopher C. Kraft_ Jr._ April 1956 TN 3616 CHARTS FOR ESTIMATING ROTOR-BLADE FLAPPING MOTION OF HIGH- PERFORMANCE HELICOPTERS_ Robert Jo Tapscott and Alfred Gessow_ March 1956 TN 3619 EFFECT OF CARRIAGE MASS UPON THE LOADS AND MOTIONS OF A PRISMATIC BODY DURING HYDRODYNAMIC IMPACT_ Melvin F. Markey_ March 1956 TN 3621 GUST-LOAD AND AIRSPEED DATA FROM ONE TYPE OF TWO-ENGINE AIRPLANE ON SIX CIVIL AIRLINE ROUTES FROM 1947 TO 1955_ Walter G. Walker_ February 1956 TN 3622 PRELIMINARY STUDY OF SOME FACTORS WHICH AFFECT THE STALL-FLUTTER CHARACTERISTICS OF THIN WINGS_ A. Gerald Rainey_ March 1956 TN 3632 CORRELATION_ EVALUATIONj AND EXTENSION OF LINEARIZED THEORIES FOR TIRE MOTION AND WHEEL SHIMMY_ Robert F. Smiley_ June 1956 TN 3687 SOME WIND-TUNNEL EXPERIMENTS ON SINGLE-DEGREE-OF-FREEDOM FLUTTER OF AILERONS IN THE HIGH SUBSONIC SPEED RANGE_ R. E. Maringerj L. L.

Marsh_ and G. K. Manning_ June 1956 TN 3688 STATIC-THRUST MEASUREMENTS OF THE AERODYNAMIC LOADING ON A HELl- COPTER ROTOR BLADE_ John P. Rabbott_ Jr._ july 1956 TN 3690 NORMAL COMPONENT OF INDUCED VELOCITY IN THE VICINITY OF A LIFTING ROTOR WITH A NON-UNIFORM DISK LOADING_ William Hewitt Phillips and Robert F. Thompson_ April 1956 TN 3698 PRELIMINARY INVESTIGATION OF SELF-EXCITED VIBRATIONS OF SINGLE PLAN- ING SURFACES_ Elmo J. Mottard_ June 1956 TN 3705 AN INVESTIGATION OF FORWARD-LOCATED FIXED SPOILERS AND DEFLECTORS AS GUST ALLEVIATORS ON AN UNSWEPT-WING MODEL_ D. R. Croom_ Co C.

Shufflebarger_ and J. K. Huffman_ June 1956 COMPARISON OF EXPERIMENTAL AND THEORETICAL NORMAL-FORCE DISTRIBU- TN 3716 TIONS (INCLUDING REYNOLDS NUMBER EFFECTS) ON AN OGIVE-CYLINDER BODY AT MACH NUMBER 1.98_ Edward W. Perkins and Leland H. Jorgensen_ May 1956 THE INTERFERENCE EFFECTS OF A BODY ON THE SPANWISE LOAD DISTRIBUTIONS TN 3730 OF TWO 45 ° SWEPTBACK WINGS OF ASPECT RATIO 8.02 FROM LOW-SPEED TESTS_ Albert P. Martina_ August 1956 TN 3733 PROBABILITY AND FREQUENCY CHARACTERISTICS OF SOME FLIGHT BUFFET LOADS_ Wilber B. Huston and T. H. Skopinski_ August 1956 TN 3741 AN INVESTIGATION OF THE LOADS ON THE VERTICAL TAlL OF A JET-BOMBER AIRPLANE RESULTING FROM FLIGHT THROUGH ROUGH AIR_ Jack Funk and Richard H. Rhyne_ October 1956 TN 3746 INITIAL RESULTS OF A FLIGHTINVESTIGATION OF THEWING ANDTAIL LOADS ONAN AIRPLANE EQUIPPED WITHA VANE-CONTROLLED GUST-ALLEVIATION SYSTEM_ T. V. Cooneyand Russell L. Schott_ September 1956 TN 3748 CALCULATION ANDCOMPILATION OF THEUNSTEADY-LIFT FUNCTIONS FORA RIGID WINGSUBJECTED TO SINUSOIDAL GUSTS ANDTO SINUSOIDAL SINKING OSCILLATIONS_ Joseph A. Drischler_ October 1956 TN 3780 INCOMPRESSIBLE FLUTTER CHARACTERISTICS OF REPRESENTATIVE AIRCRAFT WINGS_ C. H. Wilts_ April 1957 TN 3803 BAND-PASS SHOCK ANDVIBRATION ABSORBERS FORAPPLICATION TOAIR- CRAFT LANDING GEAR_ Emanuel Schnitzer_ October 1956 TN 3805 CALCULATION OF THEFORCES ANDMOMENTS ONA SLENDER FUSELAGE AND VERTICAL FIN PENETRATING LATERAL GUSTS_ John M. Eggleston_ October MEASUREMENT OF THE LONGITUDINAL MOMENT OF INERTIA OF A FLEXIBLE AIRPLANE_ Henry A. Cole_ Jr._ and Frances L. Bennion_ November THEORETICAL AND EXPERIMENTAL INVESTIGATION OF RANDOM GUST LOADS.

PART I - AERODYNAMIC TRANSFER FUNCTION OF A SIMPLE WING CONFIGURA- TION IN INCOMPRESSIBLE FLOW_ Raimo J. Hakkinen and A. S. Richard- son_ Jr._ May 1957 TN 3879 THEORETICAL AND EXPERIMENTAL INVESTIGATION OF RANDOM GUST LOADS.

PART II - THEORETICAL FORMULATION OF ATMOSPHERIC GUST RESPONSE PROBLEM_ A. S. Richardson_ Jr._ May 1957 TN 3902 RESULTS OF TWO FREE-FALL EXPERIMENTS ON FLUTTER OF THIN UNSWEPT WINGS IN THE TRANSONIC SPEED RANGE_ William T. Lauten_ Jr._ and Herbert C. Nelson_ January 1957 TN 3910 THE RESPONSE OF AN AIRPLANE TO RANDOM ATMOSPHERIC DISTURBANCES_ Franklin W. Diederich_ April 1957 TN 3914 SOME EXPERIMENTAL STUDIES OF PANEL FLUTTER AT MACH NUMBER 1.3_ Maurice A. Sylvester and John E. Baker 3 February 1957 TN 3920 EFFECT OF SPANWISE VARIATIONS IN GUST INTENSITY ON THE LIFT DUE TO ATMOSPHERIC TURBULENCE_ Franklin W. Diederich and Joseph A. Drisch- ler, April 1957 TN 3940 IMPACT-LOADS INVESTIGATION OF CHINE-IMMERSED MODELS HAVING CONCAVE- CONVEX TRANSVERSE SHAPE AND STRAIGHT OR CURVED KEEL LINESj Philip M. Edge_ Jr._ February 1957 TN 3941 COMPARISON OF CALCULATED AND EXPERIMENTAL LOAD DISTRIBUTIONS ON THIN WINGS AT HIGH SUBSONIC AND SONIC SPEEDS_ John L. Crigler_ January 1957 TN 3956 LIFT ANDMOMENT _RESPONSES TOPENETRATION OF SHARP-EDGED TRAVELING GUSTS, WITHAPPLICATION TOPENETRATION OF WEAK BLAST WAVES, Joseph A. Drischler and Franklin Diederich_ May 1957 TN 4008 A SUMMARY OF GROUND-LOADS STATISTICS_ John R. Westfall_ Benjamin Milwitzky_ NormanS. Silsby_ and Robert C. Dreher_ May 1957 TN 40i0 EXPERIMEqqTALLY DETERMINED NATURAL VIBRATION MODES OF SOME CANTI- LEVER-WING FLUTTER MODELS BYUSINGANACCELERATION METHOD_ Pery W.

Hansonand W. J. Tuovila_ April 1957 TN 4015 THEORETICAL ANDEXPERIMENTAL INVESTIGATIONS OF DELTA-WING VIBRA- TIONS_Edwin T° Kruszeweki_ DeeneJ. Weidman_and Eldon E. Kordes_ June 1957 TN 4055 EFFECTS OFAIRPLANE FLEXIBILITY ONWINGBENDING STRAINS IN ROUGH AIR_ R. L. Coleman_Harry Press_ and C. C. Shufflebarger_ July 1957 TN 4056 LOADS IMPLICATIONS OF GUST-ALLEVIATION SYSTEMS_ William H. Phillips_ June 1957 TN4071 A CORRELATION OFRESULTS OF A FLIGHTINVESTIGATION WITHRESULTS OF AN ANALYTICAL STUDY OF EFFECTS OFWING FLEXIBILITY ONWING STRAINS DUETO GUSTS_ C. C. Shufflebarger_ C. B. Payne_ and G. L. Cahen_ August 1957 TN4103 IMPACT-LOADS INVESTIGATION OF CHINE-IMMERSED MODEL HAVING A CIRCULAR-ARC TRANSVERSE SHAPE_ Philip M. Edge_Jr._ September 1957 TN 4106 IMPACT-LOADS INVESTIGATION OFA CHINE-IMMERSED MODEL HAVING A LONGITUDINALLY CURVED BOW ANDA V-BOTTOM WITHA DEAD-RISE ANGLE OF 30o_ Philip M. Edge_ Jr._ and John S. Mixson_ September 1957 TN 4113 STUDY OF PRESSURE DISTRIBUTIONS ONSIMPLESHARP-NOSED MODELS AT MACH NUMBERS FROM 16 TO 18 IN HELIUM FLOW_ WayneD. Erickson_ October 1957 TN 4148 THEORETICAL PRESSURE DISTRIBUTIONS FORSEVERAL RELATED NON-LIFTING AIRFOILSAT HIGHSUBSONIC SPEEDS_ John R. Spreiter_ Alberta Y.

Alkson_ and B. Jeanne Hyett_ January 1958 TN 4166 AN EXPERIMENTAL ANDTHEORETICAL STUDY OFTHEEFFECT OFFUELON PITCHING-TRANSLATION FLUTTER_ John L. Sewall_ December1957 TN 4173 AN ANALYTICAL INVESTIGATION OF THEGUST-ALLEVIATING PROPERTIES OF A SIMPLE PITCHDAMPER_ NormanL. Crabill_ December1957 TN 4175 INVESTIGATION OF DEFLECTORS AS GUST ALLEVIATORS ONA 0.09-SCALE MODEL OF THEBELLX-5 AIRPLANE WITHVARIOUS WING SWEEP ANGLES FROM 20° TO 60° AT MACH NUMBERS FROM 0.40 TO 0.90_ Delwin R. Croomand Jarrett K. Huffman_ November1957 TN 4191 ANALYSIS OF HORIZONTAL-TAlL LOADS IN PITCHING MANEUVERS ONA FLEXIBLESWEPT-WING JET BOMBER_ William S. Aiken_ Jr._ December TN 4197 SUMMARY OFFLUTTER EXPERIENCES AS A GUIDETOTHEPRELIMINARY DESIGN OF LIFTING SURFACES ONMISSILES_Dennis J. Martin_ February 1958 TN4234 PRESSURE DISTRIBUTIONS AT TRANSONIC SPEEDS FORPARABOLIC-ARC BODIES OF REVOLUTION HAVING FINENESS RATIOS OF i0_ 12_ AND14_ Robert A. Taylor and John B. McDevitt_ March 1958 TN 4245 FLUTTER ANALYSIS OF RECTANGULAR WINGS OF VERY LOW ASPECT RATIO_ Robert W. Fralich and John M. Hedgepeth_June 1958 STUDY OF GROUND-REACTION FORCES MEASURED DURING LANDING IMPACTS TN 4247 OF A LARGE AIRPLANE_ Albert W. Hall_ Richard H. Sawyer_and James M. McKay_May 1958 TN 4256 WATER-IMPACT THEORY FORAIRCRAFT EQUIPPED WITHNONTRIMMING HYDRO- SKIS MOUNTED ONSHOCK STRUTS_ _nanuel Schnitzer_ September 1958 TN 4280 PRESSURE DISTRIBUTIONS AT TRANSONIC SPEEDS FORSLENDER BODIES HAV- ING VARIOUS AXIAL LOCATIONS OFMAXII_fUM DIAMETER_ John B. McDevitt and Robert A. Taylor_ July 1958 TN 4291 AN EVALUATION OF EFFECTS OF FLEXIBILITY ONWING STRAINS IN ROUGH AIR FORA LARGE SWEPT-WING AIRPLANE BYMEANS OF EXPERIMENTALLY DETERMINED FREQUENCY-RESPONSE FUNCTIONS WITHANASSESSMENT OF RANDOM-PROCESS TECHNIQUES EMPLOYED_ ThomasL. Coleman_Harry Press_ and May T. Meadows_ July 1958 TN 4304 MATRIX METHOD FOROBTAINING SPANWISE MOMENTS ANDDEFLECTIONS OF TORSIONALLY RIGID ROTOR BLADES WITHARBITRARY LOADINGS_ Alton P.

Mayo_August 1958 TN 4332 AN APPROACH TO THEPROBLEM OF ESTIMATING SEVERE ANDREPEATED GUST LOADS FORMISSILE OPERATIONS_ Harry Press and Roy Steiner_ Septem- ber 1958 TN 4335 PROCEDURE FORCALCULATING FLUTTER AT HIGHSUPERSONIC SPEEDS INCLUD- ING CAMBER DEFLECTIONS_ ANDCOMPARISON WITHEXPERIMENTAL RESULTS_ HomerG. Morgan_ Vera Huckel_ and Harry L. Runyan_September 1958 TN 4339 HYDRODYNAMIC IMPACT LOADS OF A 20° DEAD-RISE INVERTED-V MODEL AND COMPARISONS WITHLOADS OFA FLAT-BOTTOMMODEL_ Philip M. Edge_ Jr._ August 1958 TN 4342 FLIGHTMEASUREMENTS OF THEVIBRATORY BENDING ANDTORSIONAL STRESSES ONA MODIFIED SUPERSONIC PROPELLER FORFORWARDMACH NUMBERS UP TO 0.95_ ThomasC. O'Bryan_ July 1958 TN 4387 EXPERIMENTAL EVALUATION OF LOW-BAND-PASS LANDING-GEAR SHOCK ABSORB- ERFORPULSE LOADINGS_ _nanuel Schnitzer_ September 1958 TN4395 USEOF THEKERNEL FUNCTION IN A THREE-DIMENSIONAL FLUTTER ANALYSIS WITHAPPLICATION TOA FLUTTER-TESTED DELTA-WING MODEL_ Donald S.

Woolston_ John L. Sewall_ September 1958 TN 4400 MEASURI_IENTS OF GROUND-REACTION FORCES ANDVERTICAL CENTER OF GRAVITY ACCELERATIONS OF A BOMBER AIRPLANE TAXIINGOVER OBSTACLES_ JamesM. McKay_Richard H. Sawyer_ and Albert W. Hall_ September TN4401 HYDRODYNAMIC IMPACT LOADS ON30 ° AND60° V-STEPPLAN-FORM MODELS WITHANDWITHOUT DEAD RISE_Philip M. Edge_Jr._ and Jean P. Mason_ September 1958 TN4409 FLIGHTMEASURI_IENTS OF THEVIBRATION EXPERIENCED BY A TANDEM HELICOPTER IN TRANSITION_ VORTEX-RING STATE_ LANDING APPROACH_ AND YAWED FLIGHT_John E. Yeates_ September 1958 Applicable NASA Memoranda (Memo) MEMO 5-26-59L MODIFIED MATRIX METHOD FOR CALCULATING STEADY-STATE SPAN LOADING ON FLEXIBLE WINGS IN SUBSONIC FLIGHT, Patrick A. Gainer and William S. Aiken, Jr., June 1959 A method was presented for shortening the computations required to determine the steady-state span loading on flexible wings in subsonic flight. The method makes use of tables of downwash factors to find the necessary aerodynamic-influence coefficients for the application of lifting-line theory. Matrix equilibrium equations were converted into a matrix power series with a finite number of terms by using the properties of matrices. A trial and error process dependent on the required accuracy was used to determine the number of terms. The purpose was to com- bine some of the methods given in references into a procedure which can be readily followed by engineers. An example problem was given to show how the method was used.

The methods of this report were designed to save time and effort in solving steady-state aeroelastic problems without degrading the accuracy of the results. There was, however, an added flexi- bility in that the various quantities were obtained as functions of the parameter qm R where q ffi dynamic pressure and m R = lift curve slope of rigid wing per degree. These added quantities were also readily applied to any flight condition of dynamic pressure and Mach number.

Not Applicable NASA Memoranda (Memo) MEMO I0-17-58L FLUTTER TESTS OF SANDWICH-TYPE FLAT PANELS AT MACH NUMBERS OF 2.97 AND 4.12, Eldon E. Kordes and Ernest W. Evans, December MEMO 12-20-58L INVESTIGATION OF THE MAXIMUM SPIN-UP COEFFICIENTS OF FRICTION OBTAINED DURING TESTS OF A LANDING GEAR HAVING A STATIC-LOAD RATING OF 20,000 POUNDS, Sidney A. Batterson, January 1959 MEMO I-9-59L HYDRODYNAMIC IMPACT-LOAD ALLEVIATION WITH A PENETRATING HYDRO- SKI, Philip M. Edge, Jr., February 1959 MEMO 1-17-59L ANALYSIS OF ACCELERATION, AIRSPEED, AND GUST-VELOCITY DATA FROM A FOUR-ENGINE TRANSPORT AIRPLANE OPERATING OVER A NORTH- WESTERN UNITED STATES-ALASKA ROUTE, Jerome N. Engel and Martin R. Copp, February 1959 SUBSONIC WING LOADINGS ON A 45 ° SWEPTBACK-WING AND BODY COMBI- MEMO 1-18-59A NATION AT HIGH ANGLES OF ATTACK, John A. Axelson and Jack F.

Haacker, February 1959 MEMO 2-4-59L EXPERIMENTAL INFLUENCE COEFFICIENTS AND VIBRATION MODES OF A MULTISPAR 60 ° DELTA WING, Deene J. Weidman and Eldon E. Kordes, May 1959 MEMO 2-I0-59L A GENERALIZED HYDRODYNAMIC-IMPACT THEORY FOR THE LOADS AND MOTIONS OF DEEPLY IMMERSED PRISMATIC BODIES, Melvin F. Markey, March 1959 SOME EFFECTS OF YAW DAMPING ON AIRPLANE MOTIONS AND VERTICAL- MEMO 2-17-59L TAlL LOADS IN TURBULENT AIR, Jack Funk and T. V. Cooney, March MEMO 3-9-59A A WIND-TUNNEL INVESTIGATION OF THE STALL-FLUTTER CHARACTERISTICS OF A SUPERSONIC-TYPE PROPELLER AT POSITIVE AND NEGATIVE THRUST, Vernon L. Rogallo and Paul F. Yaggy, May 1959 MEMO 3-15-59L RESULTS OF CYCLIC LOAD TEST OF RB-47E AIRPLANE COORD. NO. AF- AM-171, Wilber B. Huston, January 1959 MEMO 3-23-59A A BUFFET INVESTIGATION AT HIGH SUBSONIC SPEEDS OF WING-FUSELAGE- TAlL COMBINATIONS HAVING SWEPTBACK WINGS WITH NACA FOUR-DIGIT THICKNESS DISTRIBUTIONS, FENCES, AND BODY CONTOURING, Fred B.

Sutton, March 1959 EFFECT OF HORIZONTAL-TAIL CHORD ON THE CALCULATED SUBSONIC SPAN MEMO 4-I-59L LOADS AND STABILITY DERIVATIVES OF ISOLATED UNSWEPT TAlL ASSEM- BLIES IN SIDESLIP AND STEADY ROLL, Katherine W. Booth, March MEMO 5-12-59A SURFACE PRESSURE DISTRIBUTION AT HYPERSONIC SPEEDS FORBLUNT DELTA WINGS AT ANGLE OFATTACK, Marcus O. Creager, May 1959 MEMO 5-26-59L MODIFIED MATRIX METHOD FORCALCULATING STEADY-STATE SPAN LOADING ONFLEXIBLE WINGS IN SUBSONIC FLIGHT,Patrick A.

Gainer and William S. Aiken, Jr., June 1959 CHORDWISE PRESSURE DISTRIBUTIONS OVER SEVERAL NACA16-SERIES MEMO 6-I-59L AIRFOILSAT TRANSONIC MACH NUMBERS UP TO 1.25, Charles L.

Ladson, June 1959 Applicable NASA Technical Notes TN D 1501 AN APPLICATION OF A NUMERICAL TECHNIQUE TO LIFTING SURFACE THEORY FOR CALCULATION OF UNSTEADY AERODYNAMIC FORCES DUE TO CONTINUOUS SINUSOIDAL GUSTS ON SEVERAL WING PLAN FORMS AT SUBSONIC SPEEDS, W. Prager, January 1948 A numerical lifting surface method is used to calculate direct gust forces and moments on wings of several plan forms. The gust velocities are continuous, vary sinusoidally in the stream direction and are uniform across the span. The procedure includes effects of wing plan form, nonsteady subsonic flow, and induced flow effects. The method provides for calculation of gust forces on a basis consistent with that for the calculation of forces due to motion and deformation. The direct gust forces and moments are in forms suitable to be inserted in equations of motion used in the calculation of dynamic responses of flexible lifting vehicles to random turbulence and to be compared with results from other methods.

Responses of the six wing plan forms are plotted. The known limitations of the method are discussed; in particular, aspect ratio must be less than i0.

Steady-state values of lift- and pitching-moment-curve slopes must be known.

The results include (i) spanwise distribution of section lift coefficient, (2) total lift coefficient, (3) total pitching moment coefficient.

TN D 1521 AN INTEGRAL EQUATION RELATING THE GENERAL TIME DEPENDENT LIFT AND DOWNWASH DISTRIBUTIONS ON A FINITE WING IN SUBSONIC FLOW, Eugene Migotsky, March 1948 Summary : An integral equation for obtaining the unsteady air forces on finite wings in subsonic compressible flow is presented. The equation is applicable for any time-dependent motion and can be utilized for flexible as well as rigid wings. The approach in- volves the derivation of an integral equation relating the unknown pressure distribution to any arbitrary time dependent downwash distribution. Special cases of the integral equation are treated for the 2-dimensional incompressible flow and are presented in the index. In particular, the 2-dimensional incompressible case has been developed in the appendix for the rapid determination of the growth of lift for any arbitrary time-dependent downwash distribution, with special attention given to a wing having a sudden change in angle of attack or penetrating a sharp-edge gust.

It was noted that the kernel function for oscillating finite wings is obtained as a special case of the integral expression.

No table, graphs, or plots were contained in the report.

Not Applicable NASA Technical Notes TN D AN EXAMINATION OF METHODS OF BUFFETING ANALYSIS BASED ON EXPERI- MENTS WITH WINGS OF VARYING STIFFNESS_ A. Gerald Rainey and Thomas A. Byrdsong_ APPENDIX A: DERIVATION OF EQUATIONS GOVERN- ING BUFFET RESPONSE OF A WING_ Don D. Davis_ Jr._ August 1959 TN D INVESTIGATION OF METHODS FOR COMPUTING FLUTTER CHARACTERISTICS OF SUPERSONIC DELTA WINGS AND COMPARISON WITH EXPERIMENTAL DATA, C. H. Wilts_ August 1959 TN D 15 EXPERIMENTAL INVESTIGATION AT TRANSONIC SPEEDS OF PRESSURE DIS- TRIBUTIONS OVER WEDGE AND CIRCULAR-ARC AIRFOIL SECTIONS AND EVAL- UATION OF PERFORATED-WALL INTERFERENCE_ Earl D. Knechtel_ August TN D 22 MEASUREMENTS OF GROUND-REACTION FORCES AND VERTICAL ACCELERATIONS AT THE CENTER OF GRAVITY OF A TRANSPORT AIRPLANE TAXIING OVER OBSTACLES, James M. McKay_ September 1959 TN D 27 SHIELDING STAGNATION SURFACES OF FINITE CATALYTIC ACTIVITY BY AIR INJECTION IN HYPERSONIC FLIGHT_ Paul M. Chung_ August 1959 TN D SUMMARY OF VGH AND V-G DATA OBTAINED FROM PISTON-ENGINE TRANSPORT AIRPLANES FROM 1947 TO 1958_ Walter G. Walker and Martin R. Copp_ September 1959 TN D 31 A DYNAMIC MODEL INVESTIGATION OF THE EFFECT OF A SHARP-EDGE VERTICAL GUST ON BLADE PERIODIC FLAPPING ANGLES AND BENDING MOMENTS OF A TWO-BLADE ROTOR_ John Locke McCarty_ George W. Brooks_ and Demenic J. Maglieri_ September 1959 TN D 36 ANALYSIS OF ACCELERATION_ AIRSPEED_ AND GUST-VELOCITY DATA FROM A FOUR-ENGINE TURBOPROP TRANSPORT OPERATING OVER THE EASTERN UNITED STATES_ Martin R. Copp and Mary W. Fetner 3 September 1959 TN D 40 SOME NOTES ON ATTITUDE CONTROL OF EARTH SATELLITE VEHICLES_ Warren Gillespie_ Jr._ Donald G. Eide_ and Allan B. Churgin_ December TN D 48 GROUND MEASUREMENTS OF THE SHOCK-WAVE NOISE FROM AIRPLANES IN LEVEL FLIGHT AT MACH NUMBERS TO 1.4 AND AT ALTITUDES TO 45_000 FEET, Domenic J. Maglieri_ Harvey H. Hubbard_ and Donald L.

Lansing_ September 1959 TN D 56 AN INVESTIGATION TO DETERMINE CONDITIONS UNDER WHICH DOWNWASH FROM VTOL AIRCRAFT WILL START SURFACE EROSION FROM VARIOUS TYPES OF TERRAIN_ Richard E. Kuhn_ September 1959 TN D 63 FIELD EXPERIMENTS ON TREATMENT OF FLUORINE SPILLS WITH WATER OR SODA ASH_ R. James Rollbuhler_ George R. Kinney_ and Lorenz C.

Leopoid_ September 1959 TN D 64 GRAPHICAL TRAJECTORY ANALYSIS_ Aaron S. Boksenbom_ December1959 TN D 68 GENERAL PURPOSE SUBROUTINES FORTHEIBM 650 MAGNETIC DRUM DATA- PROCESSING MACHINE WITHATTACHMENTS_ Vearl N. Huff_ DonN. Turner_ and Oliver W. Reese_October 1959 TN D 71 AN APPROXIMATE METHOD FORCALCULATING SURFACE PRESSURES ONCURVED PROFILEBLUNT PLATES IN HYPERSONIC FLOW_ Marcus O. Creager_ September 1959 TN D i00 AN ANALYSIS OF INCREMENTAL HORIZONTAL-TAlL LOADS MEASURED ONA SWEPT-WING BOMBER AIRPLANE IN SIDESLIPMANEUVERS_ William A.

McGowan_ October 1959 ROUGH-WATER DITCHING INVESTIGATION OF A MODEL OF A JET TRANSPORT TN D i01 WITHTHELANDING GEAR EXTENDED ANDWITHVARIOUS DITCHING AIDS, William C. Thompson_ October 1959 PREDICTED CHARACTERISTICS OF AN INFLATABLE ALUMINIZED-PLASTIC TN D 115 SPHERICAL EARTH SATELLITE WITHREGARD TO TEMPERATURE_ VISIBILITY_ REFLECTION OF RADAR WAVES_ ANDPROTECTION FROM ULTRAVIOLET RADIA- TION_GeorgeP. Woodand Arlen F. Carter 3 October 1959 TN D 137 A PRELIMINARY INVESTIGATION OF THEPENETRATION OF SLENDER METAL RODS IN THICKMETAL TARGETS_ JamesL. Summers and William R.

Niehaus, December1959 TN D 138 THEEFFECTS OFAN INVERSE-TAPER LEADING-EDGE FLAPONTHEAERO- DYNAMIC LOADING CHARACTERISTICS OF A 45° SWEPTBACK WING AT MACH NUMBERS TO0.90, Fred A. Demele_December1959 TN D 142 A METHOD FORCALCULATING THEAERODYNAMIC FORCES DUETO ARBITRARY_ TIME-DEPENDENT DOWNWASH FORA CLASS OF THIN_FLEXIBLEWINGS AT SUPERSONIC SPEEDS_ Robert W. Warner and Barbara B. Packard, February 1960 TN D 145 WATER-LANDING IMPACT ACCELERATIONS FORTHREE MODELS OF REENTRY CAPSULES_ Victor L. Vaughan_Jr._ October 1959 TN D 146 DERIVATION ANDTABULATION OFMOLECULAR INTEGRALS_ RoopC. Sahni and JamesW. Cooley_ December1959 TN D 147 STATISTICAL MEASUREMENTS OF CONTACT CONDITIONS OF COMMERCIAL TRANSPORTS LANDING ONAIRPORTS AT AN ALTITUDE OF 5_300 FEETAND AT SEALEVEL_NormanS. Silsby and Sadie Livingston_ November1959 TN D 154 BRAKING ANDLANDING TESTS ONSOME NEW TYPES OF AIRPLANE LANDING MATS ANDMEMBRANES_ Sidney A. Batterson_ October 1959 TN D 161 AN INVESTIGATION OF SOME ASPECTS OFTHESONIC BOOM BYMEANS OF WIND-TUNNEL MEASUREMENTS OF PRESSURES ABOUT SEVERAL BODIES AT A MACH NUMBER OF 2.01_ Harry W. Carlson_ December1959 TN D 165 A BRIEFINVESTIGATION OF THEEFFECT OFWAVES ONTHETAKE-OFF RESISTANCE OFA SEAPLANE_ Elmo J. Mottard_ December1959 TN D 175 DYNAMIC-MODEL INVESTIGATION OF THEDAMPING OF FLAPWISE BENDING MODES OF TWO-BLADE ROTORS IN HOVERING ANDA COMPARISON WITH QUASI-STATIC ANDUNSTEADY AERODYNAMIC THEORIES_ Milton A° Silveira and GeorgeW. Brooks_ December1959 TN D 176 WORKING CHARTS FORRAPIDPREDICTION OFFORCE ANDPRESSURE COEFFI- CIENTSONARBITRARY BODIES OF REVOLUTION BYUSEOFNEWTONIAN CONCEPTS_ Robert W. Rainey_ December1959 TN D 180 HYDRODYNAMIC CHARACTERISTICS OF A PLANING SURFACE WITHCONVEX LONGITUDINAL CURVATURE ANDAN ANGLE OFDEAD RISE OF 20°_ Elmo J. Mottard_ January 1960 TN D 192 SUMMARY OF RAWINSONDE MEASUREMENTS OF TEMPERATURES_ PRESSURE HEIGHTS_ ANDWINDS ABOUT 50_000FEETALONG A FLIGHT-TEST RANGE IN THESOUTHWESTERN UNITEDSTATES_ Terry J. Larson and Harold P.

Washington_January 1960 TN D 207 HYDRODYNAMIC IMPACT-LOADS INVESTIGATION OF CHINE-IMMERSED 0° DEAD- RISE CONFIGURATIONS HAVING LONGITUDINAL CURVATURE. WITHAN APPENDED BIBLIOGRAPHY OF LANGLEY IMPACT BASINHYDRODYNAMIC PUB- LICATIONS_ Robert W. Miller_ February 1960 TN D 213 DYNAMIC MODEL INVESTIGATION OFA LANDING-GEAR CONFIGURATION CON- SISTINGOF A SINGLE MAINSKIDANDA NOSE WHEEL_ Stanley Faber_ February 1960 TN D 214 EXPERIMENTAL INVESTIGATION OF SPIN-UPFRICTION COEFFICIENTS ON CONCRETE ANDNONSKID CARRIER-DECK SURFACES_ Walter B. Horne_ April TN D 215 VERTICAL-TAIL LOADS MEASURED IN FLIGHTONFOUR AIRPLANE CONFIG- URATIONS AT TRANSONIC ANDSUPERSONIC SPEEDS_ Robert D. Reed_ February 1960 TN D 227 EFFECT OF ECCENTRICITY OF THELUNAR ORBIT_OBLATENESS OF THE EARTH_ ANDSOLAR GRAVITATIONAL FIELD ONLUNAR TRAJECTORIES_ William H. Michael_ Jr._ and Robert H. Tolson_ June 1960 TN D 229 EXPERIMENTAL INVESTIGATION OF THEEFFECT OFASPECT RATIOANDMACH NUMBER ONTHEFLUTTER OF CANTILEVER WINGS_ E. Widmayer_Jr._ W.

T. Lauten_ Jr._ and S. A. Clevenson_ April 1960 THEDEPENDENCY OF PENETRATION ONTHEMOMENTUM PERUNIT AREA OF iN D 238 THEIMPACTING PROJECTILE ANDTHERESISTANCE OFMATERIALS TOPENE- TRATION_ Rufus D. Collins_ Jr._ and William H. Kinard_ May 1960 _N D 245 COMPRESSIBILITY EFFECTS ONTHEHOVERING PERFORMANCE OFA TWO- BLADE IO-FOOT-DIAMETER HELICOPTER ROTOR OPERATING AT TIP MACH NUMBERS UP TO0.98_ Joseph W. Jewel_ Jr._ April 1960 TN D 264 SUITABILITYOFCARBON RESISTORS FORFIELDMEASUREMENTS OF TE_IPER- ATURES IN THERANGE OF 35° TO i00 ° R_ Austin C. Herr_ HowardG.

Terbeek_ and Marvin W. Tiefermann_ February 1960 TN D 301 SPATIALCHARACTERISTICS OFWATER SPRAY FORMED BYTWO IMPINGING JETSAT SEVERAL JET VELOCITIES IN QUIESCENT AIR_ HamptonH.

Foster and Marcus F. Heidmann_July 1960 TN D 307 A HIGH-VELOCITY GUN EMPLOYING A SHOCK-COMPRESSED LIGHTGAS_ Carlton Bioletti and Bernard E. Cunningham_ February 1960 TN D 311 FULL-SCALE WIND-TUNNEL TESTS OFA SWEPT-WING AIRPLANE WITHA CASCADE-TYPE THRUST REVERSER_ Mark W. Kelly_ Richard K. Greif_ and William H. Tolhurst_ Jr._ April 1960 TN D 314 ANANALYSIS OF THEIMPACT MOTION OF AN INFLATED SPHERE LANDING VEHICLE_ E. Dale Martin and John T. Howe 3 April 1960 TN D 315 GASDYNAMICS OF AN INFLATED SPHERE STRIKING A SURFACE_ John T.

Howeand E. Dale Martin_ April 1960 TN D 351 A FLIGHTEVALUATION OFAN AIRBORNE PHYSIOLOGICAL INSTRUMENTATION SYSTEM_ INCLUDING PRELIMINARY RESULTS UNDER CONDITIONS OF VARYING ACCELERATIONS_ Harald A. Smedal_GeorgeR. Holden_ and Joseph R.

Smith_ Jr._ December1960 TN D 355 SOME BASICCONSIDERATIONS OF TELEMETRY SYSTEM DESIGN_ H. J. Peake_ June 1960 WIND-TUNNEL INVESTIGATION OF A SMALL-SCALE MODEL OFAN AERIAL TN D 377 VEHICLESUPPORTED BY DUCTED FANS_ Lysle P. Parlett_ May 1960 TN D 379 SUBSONIC KERNEL-FUNCTION FLUTTER ANALYSIS OF A HIGHLY TAPERED TAlL SURFACE ANDCOMPARISON WITHEXPERIMENTAL RESULTS_ Gerald D. Walberg 3 September 1960 TN D 392 THEORETICAL DETERMINATION OF WATER LOADS ONPITCHING HULLS AND SHOCK-MOUNTED HYDRO-SKIS_ EmanuelSchnitzer_ May 1960 TN D 405 INVESTIGATION OF TANDEM-WHEEL ANDAIR-JET ARRANGEMENTS FORIM- PROVING BRAKING FRICTION ONWET SURFACES_ Eziaslav No Harrin_ June 1960

TN D 421 INVESTIGATION AT TRANSONIC SPEEDS OFLOADING OVER A 30° SWEPTBACK WING OF ASPECT RATIO3_ TAPER RATIO0.2_ ANDNACA 65A004AIRFOIL SECTION MOUNTED ONA BODY_ Donald D. Arabian_ June 1960 TN D 460 EFFECT OFAERODYNAMIC HEATING ONTHEFLUTTER OF A RECTANGULAR WING AT A MACH NUMBER OF 2_ Harry L. Runyanand Nan H° Jones_ June 1960 TN D 498 BALANCING VANGUARD SATELLITES_ A. Simkovich and Robert C. Baumann_ April 1961 TN D 515 USEOF SUBSONIC KERNEL FUNCTION IN AN INFLUENCE-COEFFICIENT METHOD OFAERO-ELASTIC ANALYSIS ANDSOME COMPARISONS WITHEXPERIMENT_ John L. Sewall_ Robert W. Herr_ and Charles E. Watkins_ October TN D 522 EFFECT OF BODY-MOUNTED LATERAL CONTROLS ANDSPEED BRAKES ONTHE AERODYNAMIC LOAD DISTRIBUTION OVER A 45° SWEPT WING AT MACH NUMBERS FROM 0.80 TO0.98_ F. E. West_ Jr._ November1960 TN D 524 APPLICATION OFMONTE CARLO TECHNIQUE FORDETERMINING MANEUVERING LOADS FROM STATISTICAL INFORMATION ONAIRPLANE MOTIONS_ Harold A° Hamer_John P. Mayer_ and Wilber B. Huston_ May 1961 TN D 527 AN INVESTIGATION OF LANDING-CONTACT CONDITIONS FORA LARGE TURBO- JET TRANSPORT DURING ROUTINE DAYLIGHT OPERATIONS_ Joseph W.

Stickle and NormanS. Silsby_ October 1960 TN D 532 A FLIGHTINVESTIGATION OFAN AUTOMATIC GUST-ALLEVIATION SYSTEM IN A TRANSPORT AIRPLANE_ Paul A. Hunter_ Christopher C. Kraft_ Jr._ and William L. Alford_ January 1961 TN D 535 DAMAGE INCURRED ONA TILT-WING MULTI-PROPELLER VTOL/STOL AIR- CRAFT OPERATING OVER A LEVEL_GRAVEL-COVERED SURFACE_ Robert J. Pegg_ December1960 TN D 537 FLIGHTEVALUATION OF SEVERAL SPRING FORCE GRADIENTS ANDA BOB- WEIGHT IN THECYCLIC-POWER-CONTROL SYSTEM OFA LIGHTHELICOPTER_ Donald L. Mallick and John P. Reeder_October 1960 TN D 541 LANDING-IMPACT CHARACTERISTICS OFLOAD-ALLEVIATING STRUTS ONA MODEL OF A WINGED SPACE VEHICLE_ Ulysse J. Blanchard_ October TN D 542 THEORETICAL INVESTIGATION OF THESUBSONIC ANDSUPERSONIC FLUTTER CHARACTERISTICS OFA SWEPT WING EMPLOYING A TUNED STING-MASS FLUTTER SUPPRESSOR_ E. Carson Yates_ Jr._ November1960 TN D 552 STUDIES OF THERETARDATION FORCE DEVELOPED ONAN AIRCRAFT TIRE ROLLING IN SLUSH ORWATER_ Walter B. Horne_ Upshur T° Joyner_ and Trafford J. W. Leland_ September 1960 N D 620 AN INVESTIGATION OF WING ANDAILERON LOADS DUETO DEFLECTED INBOARD ANDOUTBOARD AILERONS ONA 4-PERCENT-THICK 30o SWEPT-BACK WING AT TRANSONIC SPEEDS_ Charles F. Whitcomb_Chris C. Critzos_ and Phillipa F. Brown_January 1961 _ND 643 FLIGHTINVESTIGATION OF SOME EFFECTS OF A VANE-CONTROLLED GUST- ALLEVIATION SYSTEM ONTHEWING ANDTAlL LOADS OFA TRANSPORT AIRPLANE_ Russell L. Schott and Harold A. Hamer_January 1961 TN D 649 LOADS INDUCED ONA FLAT-PLATE WING BY ANAIR JET EXHSUSTING PERPENDICULARLY THROUGH THEWING ANDNORMAL TOA FREESTREAM FLOW OFMACH NUMBER 2.0_ Joseph J. Janos_ March 1961 TN D 690 AERODYNAMIC LOADS AT MACH NUMBERS FROM 0.70 TO 2.22 ONAN AIRPLANE MODEL HAVING A WINGANDCANARD OF TRIANGULAR PLANFORM ANDEITHER SINGLE ORTWINVERTICAL TAILS_ Victor L. Peterson and GeneP.

Menees_June 1961 TN D 690-1 AERODYNAMIC LOADS AT MACH NUMBERS FROM 0.70 TO 2.22 ONAN AIR- PLANE MODEL HAVING A WINGANDCANARD OF TRIANGULAR PLANFORM AND EITHERSINGLE ORTWINVERTICAL TAILS. SUPPLEMENT I - TABULATED DATA FORTHEMODEL WITHSINGLEVERTICAL TAIL_ Victor L. Peterson and GeneP. Menees_June 1961 TN D 690-11 AERODYNAMIC LOADS AT MACH NUMBERS FROM 0.70 TO 2.22 ONAN AIRPLANE MODEL HAVING A WINGAND CANARD OF TRIANGULAR PLANFORM ANDEITHER SINGLE ORTWINVERTICAL TAILS. SUPPLEMENT II - TABULATED DATA FOR THEMODEL WITHTWINVERTICAL TAILS_Victor L. Peterson and Gene P. Menees_June 1961 TN D 712 INVESTIGATION AT TRANSONIC SPEEDS OF THELOADING OVER A 45° SWEPT- BACK WING HAVING AN ASPECT RATIOOF 3_ A TAPER RATIOOF0.2_ AND NACA 65A004AIRFOIL SECTIONS_ Jack F. Runckel and Edwin E. Lee_ Jr._ May 1961 TN D 729 STRUCTURAL-LOADS SURVEYS ONTWO TILT-WINGVTOLCONFIGURATIONS_ John F. Ward_March 1961 TN D 757 MEASURED RESPONSE TO WIND-INDUCED DYNAMIC LOADS OF A FULL SCALE SCOUT VEHICLE MOUNTED VERTICALLY ONA LAUNCHING TOWER_ G. W.

Jones_ Jr._ and Jean Gilman_ Jr._ April 1961 TN D 760 SKIDLANDINGS OF AIRPLANES ONROCKER-TYPE FUSELAGES_ Wilbur L.

Mayo_May 1961 TN D 803 EFFECTS OFMASS-LOADING VARIATIONS ANDAPPLIED MOMENTS ONMOTION ANDCONTROL OFA MANNED ROTATING SPACE VEHICLE_ William Grantham_ May 1961 TN D 811 EFFECT OF A LOAD-ALLEVIATING STRUCTURE ONTHELANDING BEHAVIOR OFA REENTRY-CAPSULE MODEL_ EdwardL. Hoffman_ SandyM. Stubbs_ and John R. McGehee_ May 1961 TN D 827 SUPERSONIC PANEL FLUTTER TESTRESULTS FORFLATFIBER-GLASS SAND- WICHPANELS WITHFOAMED CORES_ W. J. Tuovila and John G° Presnell_ Jr._ June 1961 TN D 829 CALCULATED NORMAL LOAD FACTORS ONLIGHTAIRPLANES TRAVERSING THE TRAILINGVORTEX OF HEAVY TRANSPORT AIRPLANES, William McGowan_ May 1961 TN D 830 TRANSONIC LOADS CHARACTERISTICS OFA 3-PERCENT-THICK 60° DELTA- WING-BODY COMBINATION_ John M. Swihart and Willard E. Foss_ Jr._ May 1961 TN D 831 A STUDY OF FLUTTER AT LOW MASS RATIOS WITHPOSSIBLE APPLICATION TOHYDROFOILS_ Robert W. Herr_ May 1961 TN D 833 EXPERIMENTAL STUDIES OF FLUTTER OF BUCKLED RECTANGULAR PANELS AT MACH NUMBERS FROM 1.2 TO 3.0 INCLUDING EFFECTS OF PRESSURE DIF- FERENTIAL ANDOF PANEL WIDTH-LENGTH RATIO_Maurice A. Sylvester_ May 1961 PRESSURE LOADS PRODUCED ONA FLAT-PLATE WINGBYROCKET JETSEX- TN D 893 HAUSTING IN A SPANWISE DIRECTION BELOW THEWING ANDPERPENDICULAR TOA FREE-STREAM FLOW OFMACH NUMBER 2.0_ Ralph A. Falanga and Joseph J. Janos_ May 1961 TN D 899 AN INVESTIGATION OF LANDING-CONTACT CONDITIONS FORTWO LARGE TURBOJET TRANSPORTS ANDA TURBOPROP TRANSPORT DURING ROUTINE DAYLIGHT OPERATIONS_ Joseph W. Stickle_ May 1961 AERODYNAMIC LOAD MEASUREMENTS ANDOPENING CHARACTERISTICS OF TN D 900 AUTOMATIC LEADING-EDGE SLATSONA 45° SWEPTBACK WING AT TRANSONIC SPEEDS_ Donald D. Arabian_ Jack F. Runckel_ and Charles F. Reid_ Jr._ September 1961 TN D 902 APPLICATIONS OF POWER SPECTRAL ANALYSIS METHODS TOMANEUVER LOADS OBTAINED ONJET FIGHTER AIRPLANES DURING SERVICE OPERATIONS_ John P. Mayer and Harold A. Hamer_May 1961 EFFECT OF HIGHSUBSONIC SPEEDS OFFUSELAGE FOREBODY STRAKES ON TN D 903 THESTATICSTABILITYANDVERTICAL-TAlL-LOAD CHARACTERISTICS OFA COMPLETE MODEL HAVING A DELTA WING_ Edward C. Polhamusand Kenneth P. Spreemann_ May 1961 TN D 918 TRANSONIC WIND-TUNNEL INVESTIGATION OF THEFIN LOADS ONA 1/8- SCALE MODEL SIMULATING THEFIRST STAGE OF THESCOUT RESEARCH VEHICLE_ ThomasC. Kelly_ June 1961 TN D 921 EXPERIMENTAL INVESTIGATION AT MACH NUMBER 3.0 OF THEEFFECTS OF THERMAL STRESS ANDBUCKLING ONTHEFLUTTER OF FOUR-BAY ALUMINUM ALLOY PANELS WITHLENGTH-WIDTH RATIOS OF I0_ Sidney C. Dixon_ George E. Griffith_ and HermanL. Bohon_October 1961 TND 924 AN EXPERIMENTAL INVESTIGATION OF THEEFFECTS OFMACH NUMBER_ STABILIZER DIHEDRAL_ ANDFIN TORSIONAL STIFFNESS ONTHETRANSONIC FLUTTER CHARACTERISTICS OF A TEE-TAIL_NormanS. Land and Annie G. Fox_ October 1961 TN D 942 FLUTTER AT VERY HIGHSPEEDS_ Harry L. Runyanand HomerG. Morgan_ August 1961 TN D 945 AERODYNAMIC LOADING CHARACTERISTICS AT MACH NUMBERS FROM 0.80 TO 1.20 OF A I/IO-SCALE THREE-STAGE SCOUT MODEL_ ThomasC. Kelly_ September 1961 TN D 971 TRANSONIC AERODYNAMIC LOADING CHARACTERISTICS OF A WING-BODY-TAIL COMBINATION HAVING A 52.5° SWEPTBACK WING OF ASPECT RATIO3 WITH CONICAL WING CAMBER ANDBODY INDENTATION FORA DESIGN MACH NUMBER OF _2_ Marlowe D. Cassetti_ Richard J. R% and William B. Igo% October 1961 TN D 974 COMPARISON OF EXPERIMENTAL ANDTHEORETICAL STATICAEROELASTIC LOADS ANDDEFLECTIONS OF A THIN45° DELTA WINGIN SUPERSONIC FLOW_ Floyd V. Bennett_ October 1961 TN D 975 LANDING-IMPACT-DISSIPATION SYST_4S_ Lloyd J. Fisher_ Jr._ December TN D 995 AERODYNAMIC LOADS ONAN ISOLATED SHROUDED-PROPELLER CONFIGURATION FORANGLES OF ATTACK FROM -I0 ° TO ii0°_ Kalman J. Grunwald and Kenneth W. Goodson_January 1962 TN D 1003 AN ANALYTICAL INVESTIGATION OF THELOADS_ TEMPERATURES_ ANDRANGES OBTAINED DURING THERECOVERY OF ROCKET BOOSTERS BYMEANS OF A PARAWING_ Howard G. Hatch_ Jr._ and William A. McGowan_ February TN D 1021 ANALYTICAL ANDEXPERIMENTAL INVESTIGATION OF FLUTTER ANDDIVERG- ENCE OF SPRING-MOUNTED CONE CONFIGURATIONS AT SUPERSONIC SPEEDS_ John L. Sewall_ Robert W. Hess_ and Charles E. Watkins_ April TRANSONIC FLUTTER TESTS OF A HIGHLY SWEPT ARROW WING WITHAND TN D 1023 WITHOUT SIMULATED TRAILING-EDGE-MOUNTED ENGINE MASSES_ Gerald D.

Walberg_ March 1962 TN D 1027 MODEL INVESTIGATION OF THELANDING CHARACTERISTICS OF A REENTRY SPACECRAFT WITHA VERTICAL-CYLINDER AIR BAGFORLOAD ALLEVIATION 3 John R. McGehee and Victor L. Vaughan_Jr._ March 1962 TN D 1030 AN EXPERIMENTAL TECHNIQUE FOR THE INVESTIGATION OF TIPOFF FORCES ASSOCIATED WITH STAGE SEPARATION OF MULTISTAGE ROCKET VEHICLES_ Robert L. Gungle_ William S. Brosier_ and H. Wayne Leonard_ March TN D 1058 FLIGHT FLUTTER RESULTS FOR FLAT RECTANGULAR PANELS_ Eldon E.

Kordes and Richard B. Noll_ February 1962 TN D 1149 LONGITUDINAL FORCE AND MOMENT DATA AT MACHNUMBERS FROM 0.60 TO 1.40 FOR A FAMILY OF ELLIPTIC CONES WITH VARIOUS SEMIAPEX ANGLES_ Louis S. Stivers_ Jr._ and Lionel L. Levy_ Jr._ December 1961 TN D 1257 DIVISION OF AERODYNAMIC LOADS ON A SEMISPAN TILTING-DUCTED- PROPELLER MODEL IN HOVERINGAND TRANSITION FLIGHT_ Kalman J.

Grunwald and Kenneth W. Goodson_ May 1962 TN D 1280 APPROXIMATE ANALYSIS OF G LOADS AND HEATING DURING ATMOSPHERIC ENTRIES AND PASSES WITH CONSTANT AERODYNAMIC COEFFICIENTS_ Roger W. Luidens_ July 1962 TN D 1308 SURVEY OF ENERGY-ABSORPTION DEVICES FOR SOFT LANDING OF SPACE VEHICLES_ Jack B. Esgar_ June 1962 TN D 1353 FLUTTER OF AERODYNAMICALLY HEATED ALUMINUM-ALLOY AND STAINLESS- STEEL PANELS WITH LENGTH-WIDTH RATIO OF i0 AT MACH NUMBER OF 3.0_ Lawrence D. Guy and Herman L. Bohon_ July 1962 TN D 1376 INFLUENCE OF THE TIRE TREAD PATTERN AND RUNWAY SURFACE CONDITION ON BRAKING FRICTION AND ROLLING RESISTANCE OF A MODERN AIRCRAFT TIRE_ Walter B. Horne and Trafford J. W. Leland, September 1962 TN D 1380 EFFECTS OF ANGLE OF ATTACK AND THICKNESS RATIO ON THE FLUTTER OF A RIGID UNSWEPT DIAMOND-AIRFOIL-SECTION WING AT A MACH NUMBER OF i0.0_ Lou S. Young_ August 1962 TN D 1385 PANEL FLUTTER TESTS ON FULL-SCALE X-15 LOWER VERTICAL STABILIZER AT MACH NUMBER OF 3.0_ Herman L. Bohon_ October 1962 TN D 1485 EXPERIMENTAL INVESTIGATION AT MACH NUMBER 3.0 OF EFFECTS OF THER- MAL STRESS AND BUCKLING ON FLUTTER CHARACTERISTICS OF FLAT SINGLE- BAY PANELS OF LENGTH-WIDTH RATIO 0.96_ Sidney C. Dixon_ November TN D 1487 EFFECTS OF LEADING-EDGE BLUNTNESS ON FLUTTER CHARACTERISTICS OF SOME SQUARE-PLANFORM DOUBLE-WEDGE AIRFOILS AT A MACH NUMBER OF 15.4_ Robert C. Goetz_ October 1962 TN D 1593 INVESTIGATION OF THE LATERAL VIBRATION CHARACTERISTICS OF A 1/5- SCALE MODEL OF SATURN SA-I_ John S. Mixson_ John J. Catherine_ and Ali Arman_ January 1963 TN D 1594 SOME EFFECTS OF SWEEP ANDASPECT RATIOONTHETRANSONIC FLUTTER CHARACTERISTICS OF A SERIESOF THIN CANTILEVER WINGS HAVING A TAPER RATIOOF0.6, John R. Unangst and GeorgeW. Jones, Jr., February 1963 TN D 1600 EXPERIMENTAL PANEL FLUTTER RESULTS FORSOME FLATANDCURVED TITANIUMSKINPANELS AT SUPERSONIC SPEEDS, John G. Presnell, Jr., and R. L. McKinney_January 1963 TN D 1615 POSTBUCKLING EFFECTS ONTHEFLUTTER OF SIMPLYSUPPORTED RECTANGU- LARPANELS AT SUPERSONIC SPEEDS; Robert W. Fralich, March 1963 TN D 1616 MEASURED ANDCALCULATED SUBSONIC ANDTRANSONIC FLUTTER CHARACTER- ISTICS OFA 45° SWEPTBACK WING PLANFORM IN AIR ANDIN FREON-12 IN THELANGLEY TRANSONIC DYNAMICS TUNNEL_ E. Carson Yates, Jr., NormanS. Land_ and JeromeT. Foughner, Jr., March 1963 INVESTIGATION OF BUFFET PRESSURES ONMODELS OF LARGE MANNED TN D 1633 LAUNCH VEHICLE CONFIGURATIONS, GeorgeW. Jones_ Jr., and Jerome T. Foughner, Jr., May 1963 WING ANDFLAPLOADS OBTAINED FROM A WIND-TUNNEL INVESTIGATION OF TN D 1634 A LARGE-SCALE V/STOLMODEL, Robert J. Huston_ John F. Ward, and Matthew M. Winston, April 1963 TN D 1683 FLIGHTVIBRATION DATAFROM THEDELTA 9 LAUNCH VEHICLE,Lloyd A.

Williams, October 1963 TN D 1763 SINUSOIDAL VIBRATION TESTING OF NONLINEAR SPACECRAFT STRUCTURES_ William F. Bangs, September 1963 TN D 1788 EFFECT OF AERODYNAMIC HEATING ONTHEFLUTTER OF THINFLAT-PLATE ARROW WINGS,Joseph M. Groen and Richard Rosecrans 3 May 1963 TN D 1794 A STUDY OF SEVERAL FACTORS AFFECTING THEFLUTTER CHARACTERISTICS CALCULATED FORTWO SWEPT WINGS BYPISTONTHEORY ANDBY QUASI- STEADY SECOND-ORDER THEORY ANDCOMPARISON WITHEXPERIMENTS, Robert M. Bennett and E. Carson Yates_ Jr., May 1963 TN D 1821 DYNAMIC RESPONSE OF RISINGANDFALLINGBALLOON WINDSENSORS WITH APPLICATION TO ESTIMATES OFWINDLOADS ONLAUNCH VEHICLES, Wilmer H. Reed III, October 1963 TN D 1824 USEOFAERODYNAMIC PARAMETERS FROM NONLINEAR THEORY IN MODIFIED- STRIP-ANALYSIS FLUTTER CALCULATIONS FORFINITE-SPAN WINGS AT SUPERSONIC SPEEDS_ E. Carson Yates, Jr., and Robert M. Bennett_ July 1963 TN D 1893 A WIND-TUNNEL INVESTIGATION OF GROUND-WIND LOADS ONAXISYMMETRIC LAUNCH VEHICLES_ Donald A. Buell_ George B. McCullough, and William J. Steinmetz, October 1963 TN D 1930 AERODYNAMIC LOADING CHARACTERISTICS OF A 1/10-SCALE MODEL OF THE THREE-STAGE SCOUT VEHICLE AT MACH NUMBERS FROM 1.57 TO4.65; Lloyd S. Jernell; July 1963 TND 1935 LOADS INDUCED ONA FLATPLATE AT A MACH NUMBER OF4.5 WITHA SONIC ORSUPERSONIC JET EXHAUSTING NORMAL TO THESURFACE; William Letko; July 1963 TN D 1949 FLUTTER OF FLATRECTANGULAR ORTHOTROPIC PANELS WITHBIAXIAL LOAD- INGANDARBITRARY FLOW DIRECTION; HermanL. Bohon; September 1963 TN D 1954 PRESSURE DISTRIBUTIONS ONBLUNT DELTA WINGS AT ANGLES OF ATTACK UP TO 90° ANDMACH NUMBER OF 6.85; Peter T. Bernot; July 1963 TN D 1961 SURFACE PRESSURE DISTRIBUTIONS ON0.0628-SCALE MODELS OF PROPOSED PROJECT FIRE SPACE VEHICLES AT MACH NUMBERS FROM 0.25 TO 4.63; Albin O. Pearson_ September 1963 TN D 1962 SUPERSONIC INVESTIGATION OF NOZZLE HINGE MOMENTS OF A MODIFIED SATURN C-I MODEL WITHANDWITHOUT JET FLOW;Nickolai Charczenko and Jerry L. Lowery; November1963 TN D 1982 DYNAMIC RESPONSE OFHAMMERHEAD LAUNCH VEHICLES TOTRANSONIC BUFFETING_ Henry A. Cole; Jr.; October 1963 TN D 2038 EXPERIMENTAL ANDCALCULATED RESULTS OF A FLUTTER INVESTIGATION OF SOME VERY LOW ASPECT-RATIO FLAT-PLATE SURFACES AT MACH NUMBERS FROM 0.62 TO 3.00; Perry W. Hansonand Gilbert M. Levey; October TN D 2047 EFFECTS OF DIFFERENTIAL PRESSURE; THERMAL STRESS; ANDBUCKLING ON FLUTTER OFFLATPANELS WITHLENGTH-WIDTH RATIOOF 2; Sidney C.

Dixon and Charles P. Shore; December1963 TN D 2158 STATISTICAL TECHNIQUES FORDESCRIBING LOCALIZED VIBRATORY ENVIRON- MENTS OF ROCKET VEHICLES; Robert E. Barrett; July 1964 TN D 2179 WIND-TUNNEL FLUTTER STUDIES OF THESWEPTBACK T-TAlL OFA LARGE MULTIJET CARGO AIRPLANE AT MACH NUMBERS TO0.90; Charles L.

Ruhlin; Maynard C. Sandford; and E. Carson Yates; Jr.; March 1964 TN D 2192 FLUTTER OF CURVED ANDFLATSANDWICH PANELS SUBJECTED TO SUPERSONIC FLOW;John A. McElman;April 1964 TN D 2215 COMPARISON OF EXPERIMENTAL VIBRATION CHARACTERISTICS OBTAINED FROM A I/5-SCALE MODEL ANDFROM A FULL-SCALE SATURN SA-I; John S.

Mixson and John J. Catherine; November1964 TN D 2227 RESEARCH ONPANEL FLUTTER;D. R. Kobett and E. F. E. Zeydel; November1963 TN D 2293 EXPERIMENTAL FLUTTER RESULTS FORCORRUGATION-STIFFENED PANELS AT A MACH NUMBER OF 3_ HermanL. Bohon, May 1964 EFFECTS OF LEADING-EDGE SWEEP ONFLUTTER CHARACTERISTICS OF TN D 2360 SOME DELTA-PLANFORM SURFACES AT A MACH NUMBER OF 15.4_ Robert C. Goetz_ July 1964 TN D 2399 EXPERIMENTAL ANDANALYTICAL INVESTIGATION OF PROPELLER WHIRL FLUTTER OF A POWER PLANT ONA FLEXIBLEWING_ Robert M. Bennett and SamuelR. Bland_ August 1964 TN D 2418 A STUDY OF THEEFFECTIVENESS OFVARIOUS METHODS OF VIBRATION REDUCTION ONSIMPLIFIEDSCALE MODELS OF THENIMBUS SPACECRAFT_ Huey D. Carden and Robert W. Herr_ August 1964 TN D 2479 EFFECT OFSTORE PITCHFLEXIBILITY ONFLUTTER CHARACTERISTICS OF A WING-STORE CONFIGURATION AT MACH NUMBERS NEAR 0.85_ Lou S.

Young and Charles L. Ruhlin 3 September 1964 TN D 2582 DYNAMIC ANALYSIS OFA MULTI-LEGGED LUNAR LANDING VEHICLE TO DETERMINE STRUCTURAL LOADS DURING TOUCHDOWN_ John Admire and Alden Mackey_January 1965 TN D 2590 DETERMINATION OF LOADS ONA FLEXIBLELAUNCH VEHICLE DURING ASCENT THROUGH WINDS_ Harold C. Lester and Dennis F. Collins 3 February TN D 2602 FLIGHT-MEASURED WINGSURFACE PRESSURES ANDLOADS FORTHEX-15 AIRPLANE AT MACH NUMBERS FROM 1.2 TO 6.0_ Jon S. Pyl% January TN D 2604 AERODYNAMIC LOAD DISTRIBUTIONS FORTHEPROJECT FIRE CONFIGURATIONS AT MACH NUMBERS FROM 0.25 TO 4.63_ Ralph J. Muraca_ February 1965 Applicable NACA Technical Reports PRESSURE DISTRIBUTION OVER AN NACA 23012 AIRFOIL WITH A FIXED SLOT TR 732 AND A SLOTTED FLAPj Thomas A. Harris and John G. Lowry_ 1942 Tests were made at a dynamic pressure of 16.37 pounds per square fo_t_ velocity of 80 mph_ and effective Reynolds number of 3.5 x I0 v. The model was tested with slotted flap deflected from 0 ° to 60 ° in i0 ° increments. For each flap deflection_ tests were made for angle of attack range from zero lift to approximately maximum lift in 4 increments.

The peak pressures at the nose of the slat were very high in the range of angle of attack where slots are useful. The forces on the slat were smaller than the forces on the same portion of a plain airfoil at low angles of attack but built up to very high values above the stall of the plain airfoil. These forces were much higher than previously published loads on Handley Page slats.

The loads on the flap on the slotted airfoil were approximately the same as the loads on a flap on a plain airfoil; therefore_ any conventional flap should show little change in load if a similar leading-edge slot were added to the combination.

TR 805 AN ANALYSIS OF LIFE EXPECTANCY OF AIRPLANE WINGS IN NORMAL CRUIS- ING FLIGHT_ Abbott A. Putnam_ 1945 An analysis of wing life for normal cruising flight was made based on data on the frequency of atmospheric gusts. The results of the analysis indicate that_ in general_ the fatigue life and single- gust life of an airplane wing are of about equal importance for conventional designs and normal operating conditions. Occasional failures of the overload type and fatigue failures with moderate values of stress_concentration factor may be expected within the operating life of some existing airplanes. The trends toward higher wing loading_ reduced load factor_ larger size_ and in- creased speed appear to have a secondary effect on both the fatigue life and the single gust life.

FLIGHT INVESTIGATION ON A FIGHTER-TYPE AIRPLANE OF FACTORS WHICH TR 885 AFFECT THE LOADS AND LOAD DISTRIBUTIONS ON THE VERTICAL TAlL SURFACES DURING RUDDER KICKS AND FISHTAILS_ John Boshar_ 1947 Results are presented of a flight investigation conducted on a fighter-type airplane to determine the factors which affect the loads and load distributions on the vertical tail surfaces in maneuvers. An analysis is made of the data obtained in steady flight_ rudder kicks_ and fishtail maneuvers.

TR 9 i0 SUMMARY OF DRAG CHARACTERISTICS OF PRACTICAL-CONSTRUCTION WING SECTIONS_ John H. Quinn_ Jr._ 1948 From the analysis of the drag characteristics of practical- construction wings_ quantitative data were obtained that indicated the size_ number_ and location of surface waves sufficient to induce premature transition at Reynolds numbers greater than 9xI06_ 16xi06_ and 24xi06_ and for waves that did not bring about premature transition_ at least for RN's up to approximately 50xlO6.

TR 911 LIFTING-SURFACE-THEORY ASPECT-RATIO CORRECTIONS TO THELIFT AND HINGE-MOMENT PARAMETERS FORFULL-SPAN ELEVATORS ONHORIZONTAL TAlL SURFACESj Robert S. Swansonand Stewart M. Crandall_ 1948 The lifting-surface-theory method presented is believed to allow a satisfactory estimation of the lift and hinge-moment parameters of horizontal tail surfaces with full-span elevators from the section data. The application of the method is fairly simple and requires no knowledge of lifting-surface theory. A comparison of experimental finite-span lift and hinge-momentparameters for three horizontal tail surfaces with the parameters estimated by the method provided a satisfactory verification of the method.

The method consists of using given formulas in conjunction with charts and graphs in the report. The use of the graphs greatly simplifies the method.

THEORETICAL SYMMETRIC SPAN LOADING AT SUBSONIC SPEEDS FORWINGS TR 921 HAVING ARBITRARY PLANFORM,John DeYoungand Charles W. Harper_ A method is shown by which the symmetric span loading for a certain class of wings can be simply found. The geometry of these wings is limited only to the extent that they must have symmetry about the root chord_ a straight quarter-chord line over the semispan_ and no discontinuities in twist. A procedure is shown for finding the lift-curve slope_ pitching momentj center of lift, and induced drag from the span load distribution. A method of accounting for the effects of Mach number and for changes in section lift-curve slope is also given. The span load distribution is computed from a set of 5 simultaneous equations. The other aforementioned quan- tities are then found from given formulas which are based on the span load distribution.

Charts are presented which give directly the characteristics of manywings. Other charts are presented which reduce the problem of finding the symmetric loadings on all wings falling within the prescribed limits to the solution of not more than four simul- taneous equations. The results produced from this method compare well with results from other theories and experiments. The theory is applied to a number of wings to exhibit the effects of such variables as sweep_aspect ratio_ taper_ and twist. The results are comparedand conclusions drawn as to the relative effects of these variables.

TR 969 SOME THEORETICAL LOW-SPEED SPAN LOADING CHARACTERISTICS OF SWEPT WINGS IN ROLLANDSIDESLIP_John D. Bird_ 1950 The Weissinger method for determining additional span loading for incompressible flow is used to find the damping in roll_ the lateral center of pressure of the rolling load_ and the span loading coefficients caused by rolling for wing plan forms of various aspect ratios_ taper ratios_ and sweepangles. The cal- culations of span loadings carried out in the report were madeby the method of Weissinger as found in NACA_M 1120. The results of the calculations are given in the form of graphs. The theoreti- cal results compare favorably with those of experiment. Thus the method seemswell suited to the calculations of the span loading caused by roll and for the calculation of such resulting aero- dynamic derivatives of wings as do not involve considerations of tip suction.

TR 991 THEAPPLICATION OF THESTATISTICAL THEORY OF EXTREME VALUES TO GUST-LOAD PROBLI_IS_ Harry Press_ 1950 An analysis is presented which indicates that the statistical theory of extreme values is applicable to the problems of predict- ing the frequency of encountering the larger gust loads and gust velocities for both specific test conditions as well as commercial transport operations. The extreme-value theory provides an analy- tic form for the distributions of maximum values of gust load and velocity. Methods of fitting the distribution are given along with a method of estimating the reliability of the predictions.

The application of the distribution of maximum values to available V-G data yields estimates of the frequency of encountering the larger acceleration increments that are consistent with the avail- able data and appear to be more reliable than the estimates obtained in previous analyses.

TR 997 SUMMARY OF INFORMATION RELATING TO GUST LOADS ONAIRPLANES_ Philip Donely_ 1950 Available information on gust structure_ airplane reactions_ and pertinent operating statistics was examined. This report attempts to coordinate this information with a reference for the prediction of gust loads on airplanes. The material covered represents re- search up to October 1947 The simple sharp-edge-gust formula is given which assumesthe following: The gust is sharp-edge in the direction of flight and represents an instantaneous change in wind direction or speed.

The gust velocity is uniform across the span of the airplane at any instant of time or position of the airplane in space.

The gust direction is normal to the lateral axis of the airplane.

The airplane is in steady level flight prior to entry into the gust_ and the airplane flight path_ attitud% and ground speed are not affected by the action of the gust on the airplane.

The primary effect of encountering a gust is to change the lift on the airplane.

The lift increment of the horizontal tail due to the action of the gust is negligible as comparedto that on the wing.

An investigation was also carried out on the structure of atmos- pheric gusts. Available information on the structure of atmos- pheric gusts has shown that when the gust size and the gust- gradient distance are expressed in meanwing chordsj the gust size is independent of airplane_ weather3 topography3 and alti- tude. The probable size of the gust is 20 chords_ and the prob- able gust-gradient distance for the standard gust is about I0 chords. A wedge-shapedgust with the gust velocity uniform across the span and either triangular of sinusoidal in shape with a base of 20 chords is believed to be the proper type for most load cal- culations.

Although the two-dimensional unsteady-lift functions yield the most satisfactory estimates of the load increments due to gusts for conventional airplanes with fuselages_ finite-aspect-ratio unsteady -lift functions appear pertinent for flying wings.

For unconventional configurations such as swept wings_ strip theory with two-dimensional unsteady-lift functions appears adequate.

Available data on horizontal and vertical tail loads indicate that detailed calculations of tail load are not warranted. The lift on either tail surface due to a gust can be estimated apparently by utilizing a true gust velocity and neglecting the alleviating effects of unsteady lift and airplane motion but consideration of the downwash.

TR I000 CALCULATION OF THEAERODYNAMIC LOADING OF SWEPT ANDUNSWEPT FLEXI- BLEWINGS OF ARBITRARY STIFFNESS (Supersedes NACATN 1876)_ Franklin W. Diederich 3 1950 A method is presented for calculating the aerodynamic loading_ the divergence speed_ and certain stability derivatives of swept and unswept wings and tail surfaces of arbitrary stiffness. Pro- vision is made for using either stiffness curves and root rota- tion constants or structural influence coefficients in the analy- sis.

The assumptions made in the development of the method are: (a) All deflections and angles of attack are small.

(b) The wing is mounted flexibly at an effective root perpendicu- lar to the elastic axis through the intersection of the elastic axis and the fuselage.

(c) All deformations other than those due to the root rotations are given by the elementary theories of bending and of torsion about the reference axis_ which is in this case the elastic axis.

TR 1007 HORIZONTAL TAIL LOADS IN MANEUVERING FLIGHT (Supersedes TN 2078)_ Henry A. Pearson_ William A. McGowan_ and James J. Donegan_ 1951 A method was presented for determining the horizontal tail loads in maneuvering flight with the use of a prescribed load-factor variation. The incremental tail load was separated into four components representing _ _ y_ and c. The camber component is so small that it may be neglected; therefore_ the number of aero- dynamic parameters needed in this computation of tail loads was reduced to a minimum.

An approximate method is presented for predicting maximum angular accelerations and maximum angular velocities.

TR i0 I0 A RECURRENCE MATRIX SOLUTION FOR THE DYNAMIC RESPONSE OF AIRCRAFT IN GUSTS (Supersedes TN 2060)_ John C. Houbolt_ 1951 A systematic procedure is developed for the calculation of the structural response of aircraft flying through a gust by use of difference equations and matrix notation. A detailed analysis is then given which leads to a recurrence matrix equation for the determination of the response of an airplane in a gust. The method takes into account wing bending and twisting deformations, fuselage deflections_ vertical and pitching motion of the air- plane_ and some tail forces. The method is based on aerodynamic strip theory. Either a sharp-edge gust or a gust of arbitrary shape in the spanwise or flight directions may be treated.

Once the time history of the displacements has been found_ the normal or torque loading on the wing can be found with little effort.

TR i0 34 INVESTIGATION OF SPOILER AILERONS FOR USE AS SPEED BRAKES OR GLIDE PATH CONTROLS ON TWO NACA 65-SERIES WINGS EQUIPPED WITH FULL SPAN SLOTTED FLAPS (Supersedes TN 1933), 1951 The report investigates aileron characteristics per title. Several plug-aileron and retractable-aileron configurations were investi_ gated on the two wing models with the full-span flaps retracted and deflected. Tests were made at various Mach numbers between 0.13 and 0.71. Results show that the use of plug or retractable ailerons_ either alone or in conjunction with wing flaps_ as speed brakes of glide-path controls is feasible and very effective.

TR 1056 THEORETICAL ANTISYMMETRIC SPAN LOADING FORWINGS OFARBITRARY PLANFORM AT SUBSONIC SPEEDS (Supersedes TN 2140)_ John DeYoung, A simplified lifting-surface theory that includes effects of compressibility and spanwise variation of section lift-curve slope is used to provide charts with which antisymmetric loading due to arbitrary antisymmetric angle of attack can be found for wings having symmetric plan forms with a constant spanwise sweepangle of the quarter-chord line. Consideration is given to the flexible wing in roll. Aerodynamic characteristics due to rolling_ deflect_ ed ailerons_ and sideslip of wings with dihedral are considered.

Experimental and theoretical verification of the theory is shown to be good. The theory is applicable for large aerodynamic angles provided the flow remains unseparated.

TR 1071 THEORETICAL SYMMETRIC SPAN LOADING DUETO FLAPDEFLECTION FOR WINGS OF ARBITRARY PLANFORM AT SUBSONIC SPEEDS (Supersedes TN 2278)_ John DeYoung_1952 A simplified lifting-surface theory is applied to the problem of evaluating span loading due to flap deflection for arbitrary wing plan forms. With the resulting procedure_ the effects of flap deflection on the span loading and associated aerodynamic charac_ teristics can easily be computed for any wing which is symmetrical about the root chord and which has a straight quarter-chord line over the wing semispan.

For the special case of straight-tapered wings_ the loading dis- tributions and values of flap effectiveness are given in chart form for a range of wing plan forms.

On the basis of experimental comparisons_ it is concluded that the method of the subject report can predict the flap effectiveness of wings at subsonic speeds with good accuracy.

TR 1136 ESTIMATION OF THEMAXIMUM ANGLE OF SIDESLIPFORDETERMINATION OF VERTICAL-TAIL LOADS IN ROLLING MANELF_ERS (Supersedes TN 2633), Ralph W. Stone_ Jr._ 1953 The results of the investigation presented give the following indications with regard to sideslip angles and resultant vertical_ tail loads in rolling maneuvers for a current (1953) high-speed airplane: I. The expressions that existed at this time which were simpli- fied for calculating maximum sideslip angles in rolling maneuvers will greatly underestimate the maximum sideslip angle for some conditions.

2. Solutions of the three linearized lateral equations of motion_ including product-of-inertia terms_ will generally indicate with sufficient accuracy the sideslip angles expected in aileron rolls from trimmed flight.

CHARTS ANDAPPROXIMATE FORMULAS FORTHEESTIMATION OF AEROELASTIC TR 1140 EFFECTS ONTHELOADING OF SWEPT ANDUNSWEPT WINGS (Supersedes TN 2608)_ Franklin W. Diederich and Kenneth A. Foss_ 1953 Charts were presented for the estimation of aeroelastic effects on the spanwise lift distribution_ lift-curve slope_ aerodynamic center_ and damping in roll of swept and unswept wings at subsonic and supersonic speeds. Two types of stiffness distributions were considered: one which consists of a variation of the stiffness with the fourth power of the chord and is appropriate for solid wings_ and one which is based on an idealized constant-stress structure and is believed to be more nearl_ representative of actual structures.

The limitations of these charts are that they do not apply to wings with very low aspect ratio or very large angles of sweep nor to wings with large sources of concentrated aerodynamic forces. The charts are likely to be less reliable for wings with zero taper than for wings with other taper ratios and less reliable when the componentof the Machnumber perpendicular to the leading edge is transonic than when this componentis either subsonic or supersonic.

Wings with large discontinuities in the spanwise distribution of the bending or torsional stiffnesses cannot be analyzed directly by use of the charts_ but an approximate method was presented. No charts have been presented for inertia effects but a method of estimating these effects has been outlined.

TR 1146 AERODYNAMIC FORCES ANDLOADINGS ONSYMMETRICAL CIRCULAR-ARC AIR- FOILS WITHPLAIN LEADING-EDGE ANDPLAIN TRAILING-EDGE FLAPS_ Jones F. Cahill_ William J. Underwood_Robert J. Nuber_ and Gail A.

Cheesman_ 1953 An investigation was madein the Langley two-dimensional low- turbulence tunnel and in the Langley two_dimensional low-turbulence pressure tunnel of 6- and 10%-thick symmetrical circular-arc airfoil sections at low Machnumbers and several Reynolds numbers.

The airfoils were equipped with 0.15-chord plain leading-edge flaps and 1.20-chord plain trailing-edge flaps.

TR 1154 ANALYSIS OF LANDING-GEAR BEHAVlOR_ Benjamin Milwitzky and Francis E. Cook_ 1953 The report first works problem out for the complete system of equations involved in the problem_ first for the instant of impact and then for the shock-strut deflection. The report then general- izes a simple solution in non-dimensional form which has been found to be accurate_ and leads to a rapid solution.

Plots are given for a series of solutions to the generalized equa- tions. The graphs are for dimensionless time_ against velocity ratio. These graphs may be used for rapidly estimating landing- gear performance in preliminary design.

TR 1172 A STUDY OF THEAPPLICATION OF POWER-SPECTRAL METHODS OF GENERALIZED HARMONIC ANALYSIS TO GUST LOADS ONAIRPLANES_ Harry Press and Bernard Mazelsky_ 1954 The analysis of the application of power-spectral methods of analysis to gust-load problems has indicated the following re- suits: I. The application of power-spectral methods of analysis to load calculations provides a measure of load intensity for continuous rough air in terms of the standard deviation of the load output.

2. The probability distribution of load intensity in homogeneous rough air appears to approximate a normal distribution.

3. For the case of the normally distributed output_ the standard deviation of load completely describes the probability distribu- tion of loads specifying the proportion of total time that vari- ous load values are exceeded.

4. Calculations for a limited series of conventional and stable airplane configurations indicate that the loads in continuous rough air for variations in individual airplane geometric and aerodynamic parameters are to a first approximation adequately reflected by the peak-load response to the arbitrary 10-chord triangular gust commonlyused.

The power-spectral method itself wasn't shown in the report.

TR 1228 CALCULATED SPANWISE LIFT DISTRIBUTIONS_ INFLUENCE FUNCTIONS_ AND INFLUENCE COEFFICIENTS FORUNSWEPT WINGS IN SUBSONIC FLOW (Super- sedes TN 3014)_ Franklin W. Diederich and Martin Zlotnick_ 1955 Spanwise lift distributions were calculated for nineteen unswept wings with various aspect ratios and taper ratios and with a variety of angle.of-attack or twist distributions_ including flap and aileron deflections by meansof the Weissenger method with eight control points on the semispan. Also calculated were aerodynamic influence coefficients which pertain to a certain definite set of stations along the span_ and several methods are presented for calculating aerodynamic influence functions and co- efficients for stations other than those stipulated.

The information presented can be used in the analysis of untwisted wings of wings with known twist distributions_ as well as in aero- elastic calculations involving initially unknowntwist distribu- tions.

Several pages of equations are required to present the method.

TR 1248 AN EXPERIMENTAL STUDY OFAPPLIEDGROUND LOADS IN LANDING (Super- sedes TN 3246)_ DeanC. Lindquist and Dexter M. Potter_ 1955 A study was madeof the applied loads and the coefficient of fric- tion in impacts of a small landing gear under controlled conditions on a concrete landing strip in the Langley impact basin. The basic investigation included three major phases: forward-speed tests at horizontal velocities up to approximately 86 feet per second_ forward-speed tests with reverse wheel rotation to simulate hori- zontal velocities up to about 273 feet per second_ and spin-up drop tests for comparison with the other tests.

TR 1269 THEORETICAL SPAN LOAD DISTRIBUTIONS ANDROLLING MOMENTS FORSIDE- SLIPPING WINGS OF ARBITRARY PLANFORM IN INCOMPRESSIBLE FLOW (Super- sedes NACATN 3605)_ M. J. Queijo_ 1956 A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings_ this requirement should not seriously restrict the application of the present method. The basic method requires a mechanical differentiation and integration to obtain the rolling momentfor the general wing in sideslip. For wings having straight leading and trailing edges over each semispan_ the rolling momentdue to sideslip is given by a simple equation in terms of plan-form parameters and the lateral center of pressure of the lift due to angle of attack.

The mechanical differentiation and integration required to obtain the rolling momentfor the general wing can be avoided by use of a step-load method which is also derived. Charts are presented from which the rolling-moment parameter CI_/ C L can be obtained for wings having straight leading and trailing edges over each semi- span.

The agreement between this theoretical method and experimental results showedgood agreement.

A RE-EVALUATION OF DATAONATMOSPHERIC TURBULENCE ANDAIRPLANE TR 1272 GUST LOADS FORAPPLICATION IN SPECTRAL CALCULATIONS (Supersedes NACA TN 3362)_ Harry Press_ May T. Meadows_ and Ivan Hadlock_ 1956 The available information on the spectrum of atmospheric turbulence is first briefly reviewed. On the basis of these results_ methods are developed for the conversion of available gust statistics normally given in terms of counts of gusts of acceleration peaks into a form appropriate for use in spectral calculations. The fundamental quantity for this purpose appears to be the probabili- ty distribution of the root-mean-square of the gust velocity.

Estimates of this distribution are derived from data for a number of load histories of transport operationsj also_ estimates of the variation of this distribution with altitude and weather condition are derived from available data. The method of applying these results to the calculation of airplane gust-response histories in operation is also outlined.

EFFECT OF INTERACTION ONLANDING-GEAR BEHAVIOR ANDDYNAMIC LOADS TR 1278 IN A FLEXIBLEAIRPLANE STRUCTURE (Supersedes NACA TN 3467)_ Francis E. Cook and Benjamin Milwitzky_ 1956 The effects of interaction between a landing gear and a flexible airplane structure on the behavior of the landing gear and the loads in the structure were studied by treating the equations of motion of the airplane and the landing gear as a coupled system.

The landing gear is considered to have nonlinear characteristics typical of conventional gears_ namely_ velocity-squared damping_ polytropic air_compression springing_ and exponential tire force- deflection characteristics. For the case where only two modesof the structure are considered_ an equivalent three-mass system is derived for representing the airplane and landing-gear combina- tions.

Examples are given based on the structural properties of two large airplanes having considerably different mass and flexibil- ity characteristics.

SUMMARY OF DERIVED GUST VELOCITIES OBTAINED FROM MEASURI_IENTS TR 1285 WITHINTHUNDERSTORMS (Supersedes NACATN 3538)_ H. B. Tolefson_ This report presents the available data on the derived gust velocities in thunderstorms for altitudes up to 34_000 feet. The derived gust velocities were obtained from the previously evaluated effective gust velocities through use of a conversion factor that is a function of airplane characteristics and altitude. The re- suits indicate that the intensity of the derived gust velocities in thunderstorms is essentially constant for altitudes up to about 20_000 feet and that an approximate lO%-reduction in the intensity occurs as altitude is increased from 20_000 to 30_000 feet.

TR 1305 MEASUREMENT OF AERODYNAMIC FORCES FORVARIOUS MEAN ANGLES OF ATTACK ONAN AIRFOIL OSCILLATING IN PITCHANDONTWO FINITE-SPAN WINGS OSCILLATING IN BENDING WITHEMPHASIS ONDAMPING IN THE STALL(Supersedes NACA TN 3643)_ A. Gerald Rainey_ 1957 The oscillating air forces on a two-dimensional wing oscillating in pitch about the midchord were measuredat various meanangles of attack and at Mach numbers of 0.35 and 0.7. In addition_ the aerodynamic damping in_ essentially_ the first bending modehas been measuredfor two finite-span wings over a range of mean angles of attack and reduced frequency.

TR 1322 METHOD FORCALCULATING THEAERODYNAMIC LOADING ONAN OSCILLATING FINITE WINGIN SUBSONIC ANDSONIC FLOW (Supersedes NACA TN 3694)_ Harry L. Runyanand Donald S. Woolston_ 1957 This report presents a method for determining the air forces on an oscillating finite wing of general plan form in subsonic flow including the limiting case of sonic flow. The loading on the wing is assumedto be given by a series containing unknownco- efficients which satisfies various boundary conditions at the edges. The required integrations are performed by approximate means_and a set of simultaneous equations in terms of the coeffi- cients in the loading series is obtained. Solution of this set of equations then gives the loading coefficients. This method is applied to rectangular and delta wings and comparison is madewith existing theories.

TR 1327 THEORETICAL ANDEXPERIMENTAL INVESTIGATION OF THESUBSONIC-FLOW FIELDSBENEATH SWEPT ANDUNSWEPT WINGS WITHTABLES OF VORTEX- INDUCED VELOCITIES_ William J. Alford_ Jr._ 1957 Report uses potential theory adjusted for span_ chord_ and thick- ness effects.

Results indicate significant chordwise gradients in flow proper- ties_ which diminish as distance from chord plane increases. In- creasing C L caused large changes in local downwash and sidewash angles_ and in q/qoo" Wing sweep increased sidewash.

Theoretical results overpredicted downwash angles toward tip of swept wing and underpredicted sidewash angles ahead of unswept wing.

TR 1345 THERESPONSE OF AN AIRPLANE TO RANDOM ATMOSPHERIC DISTURBANCES (Supersedes NACA TN 3910)_ Franklin W. Diederich_ 1958 The statistical approach to the problem of calculating the dynamic responses and the stresses of an airplane subjected to continuous random atmospheric turbulance has been extended in several respects_ basically_ only the assumptions of linearity_ that is_ of small motions and deformations_ as well as homogeneity and axisymmetry of the turbulence are retained.

First considered was the effect of spanwise variations of the instantaneous turbulent velocities on the lift and momentsdue to turbulence. The mean-square lift was shown to be reduced considerably if the span of the airplane is relatively large comparedwith the integral scale of turbulence. The shape of the spectrum of this lift is affected relatively little by the spanwise variations of gust intensity 3 except at very high frequencies_ if the decrease in the effective mean-square inten- sity is taken into account. The effect of sweep on the mean- square lift and its spectrum has been shown to be small for wings with a given distance from root to tip.

The mean-square rolling momentwas shown to be proportional to the ratio of the wing span to the integral scale of turbulence for small values of that ratio.

The dynamic responses of both a rigid airplane and a flexible airplane were treated. It was shown that the simultaneous action of longitudinal_ verticalj and leteral gusts on the wing stresses can be taken into account by simply adding the power spectra of the various contributions_ provided the turbulence is isotropic.

Also_ the mean-square pitching momentis shown to be substantially increased if the tail length is relatively large comparedwith the scale of the turbulence.

MEASUREMENT OF STATICPRESSURE ONAIRCRAFT_ William Gracey_ 1958 TR 1364 Extremely good information on construction of total-pressure measuring devices was found in NACATN 1605 and 3641_ which have been superseded by NACA Reports 919 and 1303.

[The report concluded that the location of a static pressure source on the fuselage nose3 or on the tube extended from the wing tip forward_ or on the tube extended ahead of the upper tip of the vertical tail is satisfactory for speeds below Mach0.8.] Best location must be found by experiment. For most of the locations tested which are standard_ the error was generally less than 0.5% for Machnumbers below 0.8. Best results were obtained when orifice did not protrude and the edges of the orifice were smooth with a slight inward bevel. The report gives several methods of determining pressure error.

Not Applicable NACA Technical Reports TR 685 MECHANISM OF FLUTTER: A THEORETICAL AND EXPERIMENTAL INVESTIGATION OF THE FLUTTER PROBLEM, Theodore Theodorsen and I. E. Garrick, TR 741 FLUTTER CALCULATIONS IN THREE DEGREES OF FREEDOM, Theodore Theodorsen and I. E. Garrick, 1942 TR 759 DERIVATION OF CHARTS FOR DETERMINING THE HORIZONTAL TAIL LOAD VARIATION WITH ANY ELEVATOR MOTION, Henry A. Pearson, 1943 TR 792 FLIGHT STUDIES OF THE HORIZONTAL-TAIL LOADS EXPERIENCED BY A FIGHTER AIRPLANE IN ABRUPT MANEUVERS, Flight Research Maneuvers Section - LMAL, 1944 TR 795 THE NACA IMPACT BASIN AND WATER LANDING TESTS OF A FLOAT MODEL AT VARIOUS VELOCITIES AND WEIGHTS, Sidney A. Batterson, 1944 TR 807 A METHOD OF ANALYSIS OF V-G RECORDS FROM TRANSPORT OPERATIONS, A. M. Peiser and M. Wilkerson, 1945 TR 810 ANALYSIS AND MODIFICATION OF THEORY FOR IMPACT OF SEAPLANES ON WATER, Wilbur L. Mayo, 1945 TR 826 A METHOD FOR DETERMINING THE CAMBER AND TWIST OF A SURFACE TO SUPPORT A GIVEN DISTRIBUTION OF LIFT, WITH APPLICATIONS TO THE LOAD OVER A SWEPTBACK WING, Doris Cohen, 1945 TR 836 BENDING-TORSION FLUTTER CALCULATIONS MODIFIED BY SUBSONIC COM- PRESSIBILITY CORRECTIONS, I. E. Garrick, 1946 TR 838 CONSIDERATION OF DYNAMIC LOADS ON THE VERTICAL TAIL BY THE THEORY OF FLAT YAWING MANEUVERS, John Boshar and Philip Davis, 1946 TR 846 FLUTTER AND OSCILLATING AIR-FORCE CALCULATIONS FOR AN AIRFOIL IN A TWO-DIMENSIONAL SUPERSONIC FLOW, I. E. Garrick and S. I. Rubinow, TR 859 MEASUREMENTS IN FLIGHT OF THE PRESSURE DISTRIBUTION ON THE RIGHT WING OF A PURSUIT-TYPE AIRPLANE AT SEVERAL VALUES OF MACH NUMBER, Lawrence A. Clousing, William N. Turner and L. Stewart Rolls, TR 867 A THEORETICAL INVESTIGATION OF HYDRODYNAMIC IMPACT LOADS ON SCALLOPED-BOTTOM SEAPLANES AND COMPARISONS WITH EXPERIMENT, Benjamin Milwitzky, 1947 TR 966 FLUTTER OF A UNIFORM WING WITH AN ARBITRARILY PLACED MASS ACCORDING TO A DIFFERENTIAL-EQUATION ANALYSIS AND A COMPARISON WITH EXPERIMENT, Harry L. Runyan and Charles E. Watkins, 1950 STUDY OF EFFECTS OF SWEEP ON THE FLUTTER OF CANTILEVER WINGS, TR 1014 J. G. Barmby, H. J. Cunningham, and I. E. Garrick, 1951 TR EQUATIONS AND CHARTS FOR THE RAPID ESTIMATION OF HINGE-MOMENT AND EFFECTIVENESS PARAMETERS FOR TRAILING-EDGE CONTROLS HAVING LEADING AND TRAILING EDGES SWEPT AHEAD OF THE MACH LINES, Kenneth L. Goin, 1951 AN ITERATIVE TRANSFORMATION PROCEDURE FOR NUMERICAL SOLUTION TR 1073 OF FLUTTER AND SIMILAR CHARACTERISTIC-VALUE PROBLEMS, Myron L. Gossard, 1952 SINGLE-DEGREE-OF-FREEDOM-FLUTTER CALCULATION FOR A WING IN SUB- TR 1089 SONIC POTENTIAL FLOW AND COMPARISON WITH AN EXPERIMENT, Harry L. Runyan, 1952 GENERALIZED THEORY FOR SEAPLANE IMPACT, Benjamin Milwitzky, 1952 TR 1103 THEORY AND PROCEDURE FOR DETERMINING LOADS AND MOTIONS IN CHINE- TR 1152 IMMERSED HYDRODYNAMIC IMPACTS OF PRISMATIC BODIES, Emanuel Schnitzer, 1953 LIFT DEVELOPED ON UNRESTRAINED RECTANGULAR WINGS ENTERING GUSTS TR AT SUBSONIC AND SUPERSONIC SPEEDS, Harvard Lomax, 1954 ON THE USE OF THE INDICIAL FUNCTION CONCEPT IN THE ANALYSIS OF TR UNSTEADY MOTIONS OF WINGS AND WING-TAIL COMBINATIONS, Murray Tobak, 1954 A REVISED GUST-LOAD FORMULA AND A RE-EVALUATION OF V-G DATA TR 1206 TAKEN ON CIVIL TRANSPORT AIRPLANES FROM 1933 TO 1950, Kermit G. Pratt and Walter G. Walker, 1954 1208 A COMPARISON OF THE SPANWISE LOADING CALCULATED BY VARIOUS TR METHODS WITH EXPERIMENTAL LOADINS OBTAINED ON A 45 ° SWEPTB_CK WING OF ASPECT RATIO 8.02 AT A REYNOLDS NUMBER OF 4.0 x i0v, William C. Schneider, 1954 STATISTICAL MEASUREMENTS OF CONTACT CONDITIONS OF 478 TRANSPORT- TR 1214 AIRPLANE LANDINGS DURING ROUTINE DAYTIME OPERATIONS, Norman S.

Silsby, 1955 TR 1219 MEASUREMENT AND ANALYSIS OF WING AND TAIL BUFFETING LOADS ON A FIGHTER AIRPLANE, Wilber B. Huston and T. H. Skipinski, 1955 THEORETICAL CALCULATIONS OF THE PRESSURES, FORCES, AND MOMENTS TR 1268 AT SUPERSONIC SPEEDS DUE TO VARIOUS LATERAL MOTIONS ACTING ON THIN ISOLATED VERTICAL TAILS, Kenneth Margolis and Percy J.

Bobbltt, 1956 THEPROPER COMBINATION OFLIFT LOADINGS FORLEASTDRAG ONA TR 1275 SUPERSONC WING,Frederick C. Grant, 1956 TR 1280 THEORETICAL INVESTIGATION OF FLUTTER OFTWO-DIMENSIONAL FLAT PANELS WITHONESURFACE EXPOSED TO SUPERSONIC POTENTIAL FLOW, Herbert C. Nelson and Herbert J. Cunningham,1956 TR 1365 A CORRELATION OFRESULTS OFA FLIGHTINVESTIGATION WITHRESULTS OF AN ANALYTICAL STUDY OF EFFECTS OF WING FLEXIBILITYONWING STRAINS DUETOGUSTS, C. C. Shufflebarger, Chester B. Payne, and GeorgeL. Cahen, 1958 TR 1390 INCOMPRESSIBLE FLUTTER CHARACTERISTICS OF REPRESENTATIVE AIR- CRAFT WINGS,C. H. Wilts, 1958 Applicable NASA Technical Reports There were no applicable aerodynamic loads reports in the NASA technical report series.

Not Applicable NASA Technical Reports TRR 20 TIRE-TO-SURFACE FRICTION-COEFFICIENT MEASUREMENTS WITH A C-123B AIRPLANE ON VARIOUS RUNWAY SURFACES, Richard H. Sawyer and Joseph J. Kolnick, 1959 TR R 58 CALCULATION OF AERODYNAMIC LOADING AND TWIST CHARACTERISTICS OF A FLEXIBLE WING AT MACH NUMBERS APPROACHING 1.0 AND COMPARISON WITH EXPERIMENT, John P. Mugler, Jr., 1960 TR R MECHANICAL PROPERTIES OF PNEUMATIC TIRES WITH SPECIAL REFERENCE TO MODERN AIRCRAFT TIRES, Robert F. Smiley and Walter B. Horne, TR R ANALYTICAL STUDY OF SOFT LANDINGS ON GAS-FILLED BAGS, Jack B.

Esgar and William C. Morgan, 1960 TR R 150 THEORETICAL STUDY OF CAMBER FLUTTER CHARACTERISTICS OF MONOCOQUE AND MULTIWEB WINGS, Robert G. Thomson and Edwin T. Kruszewski, Applicable NACA Wartime Reports WRL 52 HINGE MOMENTS OF SEALED INTERNAL BALANCE ARRANG_4ENTS FOR CONTROL SURFACES. II - EXPERIMENTAL INVESTIGATION OF FABRIC SEALS IN THE PRESENCE OF A THIN PLATE OVERHANG_ Jack Fischel_ August 1945 As an experimental verification and an extension of a previous analytical investigation_ tests were made to determine the hinge moments produced in an internal-balance arrangement by fabric seals of various widths that seal flap-nose gaps of various widths in the presence of a thin-plate overhang. The tests were conducted with horizontal_ vertical_ and circular types of balance chamber wall forward of the balance and with various heights of the balance chamber.

WRL 53 LIFTING SURFACE THEORY VALUES OF THE DAMPING IN ROLL AND OF THE PARAMETER USED IN ESTIMATING AILERON STICK FORCES, Robert S.

Swanson and E. LaVerne Priddy_ August 1945 An investigation was made by lifting-surface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagnetic-analogymethod. From the results_ aspect-ratio corrections for the damping in roll and aileron hinge moments for a wing in steady roll were obtained that are more accurate than those given by lifting-line theory.

The values of the damping in roll_ were obtained from NACA Clp_ ARR No. 3J29. The stick-force computations for a range of aileron deflections are presented in a table in the report. The results were given but not the method of computations.

WRL 93 FLIGHT STUDIES OF THE HORIZONTAL TAlL LOADS EXPERIENCED BY A MODERN PURSUIT AIRPLANE IN ABRUPT MANEUVERS_ By Flight Research Maneuvers Section_ June 1944 Tail loads in maneuvers were estimated by measuring pressure distributions and comparing to data obtained in wind tunnel tests.

Also_ strain gages and motion pictures were used to estimate nature and order of magnitude of loads.

Conc lus ions Theory developed was verified by experiments and analysis on 27 aircraft. Aileron fixed maneuvers were deemed most useful as criterion for vertical-tail loads. More adverse combinations were considered possible but improbable because they cannot be maintained long.

WRL 108 A SUMMARY OF DRAG RESULTS FROM RECENT LANGLEY FULL SCALE TUNNEL TESTS OF ARMY AND NAVY AIRPLANES_ Roy H. Lange_ February 1945 Astudy wasmade of waysto reduce drag on 12military airplanes. It was found that large reductions in drag result from slight modifica- tions. Attention to minor details in design is of utmost impor- tance. Power plant and its accessories is (stacks, supercharter, coolers) often responsible for more excess drag than any other item.

WRL 124 COMPARISON OF PITCHING MOMENTS PRODUCED BY PLAINFLAPSANDBY SPOILERS ANDSOME AERODYNAMIC CHARACTERISTICS OFAN NACA23012 AIRFOILWI_ VARIOUS TYPES OFAILERON_ Paul E. Purser and Eliza- beth G. McKinney, April 1945 An analysis of wind tunnel data on the pitching-moment charac- teristics of airfoils with plain flaps and spoilers indicated the following conclusions: (i) The pitching momentsproduced by spoilers were less positive than those produced by plain flaps of equal effectiveness.

(2) The positive values of the pitching momentsproduced by both the plain flaps and the spoilers decreased as the devices were located nearer the airfoil leading edge.

(3) From two isolated cases it was indicated that an increase in Machnumber caused less increase in the pitching momentspro- duced by the spoiler than in those produced by the plain flap.

The investigation was carried out in the Langley 7- by 10-foot wind tunnel.

WRL 129 CALCULATION OF STICKFORCES FORAN ELEVATOR WITHA SPRING TAB, Harry Greenberg, June 1944 Formulas for the calculation of hinge-moment characteristics of an elevator with a spring tab were developed in terms of basic aerodynamic parameters, spring stiffness_ and airspeed. The formulas were used in a study of the stick-force gradients on a pursuit airplane equipped with an elevator with a spring tab.

WRL 169 RESUME OF HINGE MOMENT DATA FORUNSHIELDED HORN BALANCED CONTROL SURFACES, John G. Lowry_ June 1943 The report summarizes available data from British and American sources on unshielded horn balanced control surfaces. Data indicate that stick-free stability can be increased by using a horn balance3 but often leads to control force heaviness. It divides control surfaces into 2 groups, determined by correlation of the data. It seems that tip correction factor is necessary to get good correlation. Graphs for both groups show considerable range within which stick-free stability is greater than stick- fixed stability (Ch_ positive and Ch6negative), where Ch_ is large enough to overcome Ch8 and cause control surface to move against displacement of airplane. Balances_ in general_ are not yet ready for use because yaw affects them adversely_ leading to very large stick forces to keep controls undeflected.

HINGE MOMENTS OF SEALED INTERNAL B_CE ARRANGEMENTS FORCONTROL WRL 174 SURFACES. I - THEORETICAL INVESTIGATION_ Harry E. Murray and Mary A. Erwi% August 1945 The report is a theoretical analysis of hinge-momentcharacteris- tics of various sealed-internal-balance control surfaces. It considers overhangs sealed to various wing structures by flexible seals or flexible systems of plates. Leakagewas not considered but gap width was. Most nearly linear hinge-moment characteris- tics were obtained by narrow flexible seals of about 0.i chord of overhang gap.

WRL 181 ANALYSIS OF VERTICAL TAIL LOADS IN ROLLING PULLOUTMANEUVERS_ Robert R. Gilruth_ August 1944 An analysis is presented of the vertical-tail loads to be expected as a result of abrupt aileron action in accelerated flight_ as in rolls from turns or pull-outs.

It was concluded that critical loads may occur in rolling pull- out maneuvers_particularly on airplanes with good ailerons and low directional stability.

COMPARISON BETWEEN CALCULATED ANDMEASURED LOADS ONWING AND WRL 193 HORIZONTAL TAlL IN PULLUPMANEUVERS_ Cloyce E. Matheny_ October The calculations were based on four assumptions and results were found to be as good as assumptions.

i. Changein load factor in maneuver is negligible.

2. Aerodynamic quantities are linear functions of angle of attack.

3. Speed is constant during maneuver.

4. Effects of flexibility neglected.

WRL 205 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

XVl. PRESSURE DISTRIBUTION OVER AN NACA 0009 AIRFOIL WITH 0.30- AIRFOIL-CHORD BEVELED-TRAILING-EDGE FLAPS_ H. Page Hoggard_ Jr., and Marjorie E. Bulloch_ April 1944 Pressure-distribution tests were made in the NACA 4- by 6-foot vertical tunnel of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30% of the airfoil chord and the bevel chords were 15% and 20% of the flap chord. From the tests the following conclusions were drawn: (i) At a given angle of attack and flap deflection_ the addition of a bevel reduced the resultant pressures over the entire airfoil_ except for the pressure at the flap hinge axis in- cluding the peak at the airfoil nose_ and caused a reversal of pressure over the beveled part of the flap.

(2) The normal-force coefficient for the beveled-trailing-edge flap was less than the coefficient for the plain-airfoil- contour flap with the airfoil at the same angle of attack and the flap deflected through the same angle.

(3) The open gap at the flap nose gave the flap a tendency toward over-balance because of a decrease in negative pressures over the upper surface of a downward deflected beveled flap.

(4) The size of the radius used to fair the bevel juncture did not appreciably effect the pressure distribution.

(5) The results obtained from the pressure-distribution tests generally were in fair agreement with force-test results of a comparable arrangement.

WR L 221 THEORETICAL DISTRIBUTION OF LOAD OVER A SWEPT-BACK WING_ Doris Cohen_ October 1942 The load over an elliptical wing with 30 ° sweepback has been calculated. The method of calculating the lift distribution is given in detail in TN 855. The method consists of replacing the wing and its wake by a continuous distribution of vortices and computing the induced vertical velocities caused by this vortex system at several points on the wing. The vortices coincide with the contour lines of the circulation function F_ which is obtained by integrating the lift back along the chord from the leading edge. This method takes into account the chordwise distribution of lifting area.

WR L 227 EFFECTS OF PROPELLER OPERATION AND ANGLE OF YAW ON THE DISTRIBU- TION OF THE LOAD ON THE HORIZONTAL TAlL SURFACE OF A TYPICAL PURSUIT AIRPLANE_ Harold H. Sweberg and Richard Dingeldein_ February 1944 Measurements were made in the NACA full_scale tunnel of the pres- sure distribution over the horizontal tail surface of a typical pursuit airplane in order to determine the effects of propeller operation and angle of yaw on the tail load distribution. Most of the tests were made with the propeller operating to simulate climb conditions_ high-speed dives_ and pull-ups to various normal accelerations for angles of yaw ranging from i0o to -i0 °.

WRL 264 PRESSURE DISTRIBUTION OVER AN AIRFOIL WITHA BALANCED SPLIT FLAP_ Milton B. Ames_Jr._ and John G. Lowry_ December1941 A pressure-distribution was conducted in the NACA 4- by 6-foot vertical wind tunnel to determine the airloads on an airfoil with a 22. l-percent-chord balanced split flap. Pressures were measured on both the upper and lower surfaces of the airfoil and the flap for several angles of attack and for several flap deflections.

The data_ presented as pressure diagrams and as graphs of the section coefficients for the airfoil-flap combination and for the flap alone_ are applicable to the structural design of an airfoil with a balanced split flap. It is believed that the results are applicable to airfoils of different thickness and to symmetrical or moderately camberedairfoils of similar contour.

WRL 289 EFFECT OF CHANGES IN AILERON RIGGING ONTHESTICKFORCES OF A HIGH-SPEED FIGHTER AIRPLANE_ Harry E. Murray and S. Anne Warren_ May 1944 The effect of changes in aileron rigging between 2° up and 2° down on the stick forces was determined from wind-tunnel data for a finite-span wing model. These effects were investigated for ailerons deflecting equally in both directions and linearly with stick deflection.

WRL 318 WIND-TUNNEL TESTS OF HINGE-MOMENT CHARACTERISTICS OF SPRING TAB AILERONS_ Frederick H. Imlay and J. D. Bird_ January 1944 The purpose of spring tab ailerons is to reduce the stick force re- quired to work the ailerons. Tests were madein the NACAstability tunnel on two types of spring tab ailerons. The amount of tab deflection dependedon control system force.

Results showedthat the control system force remained fairly constant throughout the speed range tested. Moderate oscillations occurred in control system at or near the stall_ due to alternate stalling and unstalling of the tab. This could be avoided by using a tab of sufficient size so that large deflections are not needed to obtain desired results. Figures show the variation of tab angle_ aileron angle_ increment of section lift angle_ and control hinge momentcoefficient with control stick deflection for the ailerons tested.

Preloading the spring control of the tab allowed for the reduction of the control forces at high speeds_ but still allows for the feel of a plain aileron at low speed_ or at small aileron deflections.

Removingthe tab gap seal considerably reduced the effectiveness of the tab as a balance.

WRL 350 WIND-TUNNEL INVESTIGATION OF CONTROL-SURFACE CHARACTERISTICS.

XVIII - A LINKEDOVERHANG AERODYNAMIC BALANCE_ Richard I. Sears and Robert B. Liddell_ February 1944 A trend in flap design has been to use an overhang to keep control forces within reason for high speed flight. This report investigates the use of a overhang which is hinged from the flap so that it deflects less than the flap_ thus avoiding the common fault of overbalance. The flap was tested always with a chord of .30 chord of the airfoil_ with the overhang chord ranging from 50%to 100%of the flap chord.

WRL 426 SOME EFFECTS OF PROPELLER OPERATION ONTHEDISTRIBUTION OF THE LOAD ONTHEVERTICAL TAlL SURFACE OF A TYPICAL PURSUIT AIRPLANE_ Harold H. Swebergand Richard C. Dingeldeinj March 1944 Full scale tests madein NACAfull scale tunnel on typical pursuit plane. Results show that prop operation caused an increment of force on the vertical tail in a positive direction (force to right) regardless of the direction of the initial load on the surface. The largest effects of prop operation were measured at a section located approximately in the middle of the fin and resulted in a large concentration of the vertical-tail load at this section. The distribution of the load over the portion of the vertical tail that is blanketed by the fuselage changed only slightly with changes in either yaw angle or prop operation.

For the range of prop-operation conditions of these tests_ the slopes of the curves of vertical-tail normal-force coefficient against angle of yaw varied only slightly with increase in thrust and torque coefficients. The effects of increases in slipstream rotation resulting from increases in prop torque on the vertical- tail loading were far more pronounced than the effects of in- creases in the axial velocity in the slipstream due to increases in propeller torque.

WRL 434 WIND-TUNNEL TESTS OFAILERONS AT VARIOUS SPEEDS.V - PRESSURE DISTRIBUTIONS OVER THENACA66_20216ANDNACA23012 AIRFOILSWITH VARIOUS BALANCES ON0.20-CHORD AILERONS_ W. Letko and H. G. Denaci_ November1943 Pressure-distribution tests of an NACA66_2-2163 a = 1.0_ airfoilj equipped with a blunt-nose-balance aileron and a sealed internal- balance aileron_ and of an NACA23012 airfoil_ equipped with a Frise aileron and a blunt-nose-balance aileron_ were madein the LMALstability tunnel. Mach numbers ranged from 0.20 to 0.47.

Pressures were measuredon the upper and lower surfaces at the midspans of the main airfoil and the aileron for several different aileron deflections at several angles of attack.

Data was presented in the form of pressure-distributions diagrams for the airfoil-aileron combinations and for the aileron alone and as curves of section coefficients which were obtained by integra- tion of the pressure-distribution diagrams of the airfoil-aileron combinations.

The report checked the usefulness of aileron balances (closeness of balance without any overbalance at any speed).

WR L 439 FULL-SCALE TUNNEL INVESTIGATION OF THE PRESSURE DISTRIBUTION OVER THE TAlL OF THE P-47B AIRPLANE_ Richard C. Dingeldein_ May 1943 Pressures on the horizontal and vertical surfaces were measured for several airplane angles of attack and angles of yaw and with numerous control-surface deflections to provide a check on the design loads. The report shows the distribution of the tail normal force between the fixed and the movable surfaces_ the effects of yaw and rudder deflection on the normal forces on the horizontal tail surfaces_ and the similar effects of angle of attack and elevator deflection on the vertical tail surfaces. Some theoreti- cal calculations were made for comparison.

WR L 443 AN ANALYTICAL STUDY OF WING AND TAIL LOADS ASSOCIATED WITH AN ELEVATOR DEFLECTION_ H. A. Pearson and J. B. Garvin_ June 1941 The equations relating the wing and tail loads are derived for the type of control movement that proceeds at a constant rate to a maximum value and thereafter remains constant.

WR L 467 ADJUSTMENT OF STICK FORCE BY A NONLINEAR AILERON-STICK LINKAGE_ John G. Lowry_ November 1942 A system was developed to allow for a non-linear variation of aileron deflection with stick deflection. This was do_e by making use of sinusoidal variation. The system results in reduced forces at large deflections_ but slightly increased forces at small de- flections.

WR L 488 DERIVATION OF CHARTS FOR DETERMINING THE HORIZONTAL TAIL LOAD VARIATION WITH ANY ELEVATOR MOTION 3 Henry A. Pearson_ January 1943 Equations relating the wing and tail loads are derived for a unit elevator displacement. Equations are then converted into a non- dimensional form and general charts given by which the wing- and tail-load-increment variation may be determined under dynamic conditions for any type of elevator motion and for various degrees of airplane stability. Examples of wing and tail load evaluation are given to illustrate the technique. Methods are given for determining the necessary derivatives from results of wind-tunnel tests when such tests are available. Extensive charts were in- cluded.

WRL 496 THEORY ANDPRELIMINARY FLIGHTTESTS OFAN ALL-MOVABLE VERTICAL TAlL SURFACE_ Robert T. Jones and Harold F. Kleckner_ January 1943 Results of tests show that: Pilots detected no difference in the flying qualities of the plane with all-movable tail and conventional tail.

All-movable tail developed considerably greater normal force per unit area than the original tail.

Directional stability with the all-movable tail was as great with the rudder free as with the rudder fixed.

Dampingof large rudder-free lateral oscillations was satisfactory.

An undamped oscillation of small amplitude was obtained in the rudder-free turns with the tail hinged at 30%of the meanaero- dynamic chord.

Pilots were able to make satisfactory normal turns with the all- movable tail using only the stick.

Stalling of the all-movable tail was obtained without flutter or vibration and was apparent to the pilot only through observation of tuft action.

PRESSURE-DISTRIBUTION MEASUR_ENTS ONVARIOUS SURFACES OF A 0.2375- WRL 553 SCALE MODEL OF THEDOUGLAS XA-26 AIRPLANE IN THE19-FOOT PRESSURE TUNNEL_ C. Dixon Ashworth_ October 1943 Pressure distribution measurementson a 0.2375-scale model of the Douglas XA-26 airplane were conducted. The measurementswere made on the spinner-cowl-nacelle assembly and the fuselage for angles of attack from -8° to 8° . The airspeed was approximately 95 mph with the tunnel air compressedto 35 pounds per square inch abso- lute.

PRESSURE-DISTRIBUTION MEASUREMENTS OF A LOW-DRAG AIRFOIL WITH WRL 676 SLOTTED FLAPSU_ITTED BY CURTISS-WRIGHT CORPORATION_ I. H. Abbott_ December1941 The test model was described in: Abbott_ I. H.: Lift and Drag Characteristics of a Low-Drag Airfoil Model with Slotted Flap Submitted by Curtiss-Wright Corporation. NACA MR_Dec. 2_ 1941.

The model was equipped with 0.25c slotted flap with the lip on- upper airfoil surface at approximately 90%of the airfoil chord.

The model was equipped with pressure-distribution orifices.

The report gives graphs of pressure-distribution for angle of attack and flap deflection. Values of corrected dynamic pressure and impact pressure level in sameunits are given on each graph.

Static pressure level is obtained by subtracting value of q to impact pressure level.

PRESSURE-DISTRIBUTION MEASUREMENTS OF TWO AIRFOIL MODELS WITH L 700 FOWLER FLAPS SU_41TTED BY CONSOLIDATED AIRCRAFT CORPORATION AS ALTERNATIVE WING SECTIONS OF THE X-B-32 AIRPLANE_ Ira H. Abbott_ January 1942 Pressure distributions diagrams for several angles of attack and flap deflections are presented. Values of corrected dynamic pres- sure and impact pressure level in terms of the same units are given on each figure. Static pressure level is obtained by subtracting the value of q to the impact pressure level.

Not Applicable NACA Wartime Reports WRAI3 MEASUR_ENTS IN FLIGHT OF THE PRESSURE DISTRIBUTION ON THE RIGHT WING OF A P-39N-I AIRPLANE AT SEVERAL VALUES OF MACH NUMBER_ L. A. Clousing_ W. N. Turner_ and L. S. Rolls_ April 1945 WRA81 FLIGHT MEASUREMENTS OF HORIZONTAL TAIL LOADS ON A TYPICAL PROPELLER DRIVEN PURSUIT AIRPLANE DURING STALLED PULL-OUTS AT HIGH SPEED_ L. A. Clousing and W. N. Turner_ April 1944 STATISTICAL ANALYSIS OF THECHARACTERISTICS OF REPEATED GUSTS IN WRL 39 TURBULENT AIR_ A. I. Moskovitz and A. M. Peiser_ November1945 EFFECTS OF COMPRESSIBILITY ONTHEMAXIMUM LIFT CHARACTERISTICS WRL 51 ANDSPANWISE LOAD DISTRIBUTION OF A 12-FOOT-SPAN FIGHTER TYPE WING OF NACA230-SERIES AIRFOIL SECTION_ E. O. Pearson_ Jr._ A. J. Evans_and F. E. West_ Jr._ November1945 VARIATION OF HYDRODYNAMIC IMPACT LOADS WITHFLIGHTPATHANGLE FORA WRL 68 PRISMATIC FLOAT AT 12° TRIMANDWITHA 22 1/2° ANGLE OF DEAD RISEj S. A. Batterson_ February 1946 WRL 69 VARIATION OF HYDRODYNAMIC IMPACT LOADS WITHFLIGHTPATH ANGLE FORA PRISMATIC FLOAT AT 6° AND9° TRIMANDA 22 1/2° ANGLE OF DEAD RISE_ S. A. Batterson and T. Stewart# February 1946 THEORETICAL ANDEXPERIMENTAL DYNAMIC LOADS FORA PRISMATIC FLOAT WRL 70 HAVING AN ANGLE OF DEAD RISE OF 22 i/2°_ W. L. Mayo_July 1945 WRL 73 FREQUENCY OF OCCURRENCE OF CRITICALGUST LOADS ONOVERLOADED AIR- PLANES_ ThomasD. Reisert, March 1945 WRL 146 CONSIDERATIONS OFWAKE EXCITED VIBRATORY STRESS IN A PUSHER PROPELLER_ B. W. Corson_ Jr._ and M. F. Miller_ February 1944 WRL 160 THEEFFECT OF HIGHWING LOADING ONLANDING TECHNIQUE ANDDISTANCE_ WITHEXPERIMENTAL DATA FORTHEB-26 AIRPLANE_ F. B. Gustafson and William J. O'Sullivanj Jr._ January 1945 WRL 182 THERELATION BETWEEN SPANWISE VARIATIONS IN THECRITICAL MACH NUMBER ANDSPANWISE LOADDISTRIBUTIONS# R. T. Whitcomb_December WRL 185 EFFECT OF HINGE MOMENT PARAMETERS ONELEVATOR STICKFORCES IN RAPIDMANEUVERS 3 R. T. Jones and H. Greenberg_November1944 WRL 211 VARIATION OF HYDRODYNAMIC IN2ACTLOADS WITHFLIGHT-PATHANGLE FORA PRISMATIC FLOAT AT 3° TRIMANDWITHA 22 1/2° ANGLE OF DEAD RISE_ S. A. Batterson_ February 1945 WRL 269 CORRELATION OFFLIGHTDATAONLIMIT PRESSURE COEFFICIENTS AND THEIRRELATION TOHIGH-SPEED BURBLING ANDCRITICALTAlL LOADS_ R. V. Rhode#September 1944 WRL 270 ANALYSIS OF EFFECT OF ROLLING PULL-OUTS ONWINGANDAILERON LOADS OFA FIGHTER AIRPLANE# Henry A. Pearson and William S. Aiken_ Jr._ March 1946 WRL 281 LIMITATIONS OF LIFTING-LINE THEORY FORESTIMATION OF AILERON HINGE-MOMENT CHARACTERISTICS# R. S. Swansonand C. L. Gillis_ December1943 WRL 657 FLUTTER TESTS ONSB2U MODEL IN 16-FOOT TUNNEL_ Theodore Theodorsen_ R. P. Coleman, N. H. Smith_ February 1943 WRL 679 FLUTTER TESTS OF B-24 FIN-RUDDER-TAB SYSTEM_ T. Theodorsen and N. H. Smith_ September 1944 WRL 699 EFFECTS OFMEAN-LINE LOADING ONTHEAERODYNAMIC CHARACTERISTICS OF SOME LOWDRAG AIRFOILS_Milton Davidson and Harold R. Turner, Jr._ September 1943 WRL 723 AN ANALYSIS OF THEINDICATIONS OF THEUNIVERSITY OF CHICAGO AIR- BORNE TURBULENCE INDICATOR IN GUSTY AIR_ H. B. Tolefson and K. G.

Pratt_ August 1946 WRL 731 A CORRELATION OF LOADINGS ANDAFTERBODY LENGTH-BEAM RATIOS OF VARIOUS FLYING-BOAT HULLS_ J. B. Parkinson_ June 1946 WRL 742 FLUTTER TESTS OFMODIFIED SB2UMODEL IN 16-FOOT TUNNEL_ Theodore Theodorsen_ R. P. Coleman_and N. H. Smith_ August 1943 WRL 743 VIBRATION RESPONSE TESTS OFA I/5-SCALE MODEL OF THEGRUMMAN F6F AIRPLANE IN THELANGLEY 16-FOOT HIGH-SPEED TUNNEL_ Theodore Theodorsen and Arthur A. Regler, November1944 WRW 41 A CORRELATION OF THEDIMENSIONS_ PROPORTIONS_ ANDLOADINGS OF EXISTINGSEAPLANE FLOATS ANDFLYING-BOAT HULLS_ W. S. Locke_ Jr._ March 1943 WRW 92 DYNAMIC LOADS ONAIRPLANE STRUCTURES DURING LANDING_ M. A. Biot and R. L. Bisplinghoff_ October 1944 WRW 106 LANDING IMPACT CHARACTERISTICS FROM MODEL TESTSjJ. D. Pierson_ February 1946 Applicable NACA Research Memoranda RML7GI8 EXPERIMENTAL INVESTIGATION OF A PRELOADED SPRING-TAB FLUTTER MODEL_ N. H. Smith_ S. A. Clevenson_ and J. G. Barmby_ December Results presented of tests of a preloaded spring-tab flutter model indicated that_ with a rudder mass-balanced and at a low frequency compared with the tab frequency_ the tab frequency appears to be the most significant parameter. Because the frequency of a pre- loaded spring-tab system was found to vary inversely with ampli- tude_ the flutter speed decreased with an increase in initial displacement of the tab. Although the effect of aspect ratio was small_ it was indicated that the tab with the low aspect ratio showed a tendency to flutter at a higher speed than the tab with a higher aspect ratio having the same area and frequency.

RML8A26 CHARTS FOR DETERMINING PRELIMINARY VALUES OF SPAN-LOAD_ SHEAR_ BENDING-MOMENTS_ AND ACCUMULATED TORQUE DISTRIBUTIONS OF SWEPT WINGS OF VARIOUS TAPER RATIOS_ Bertram C. Wollner_ July 1948 Charts are presented which may be used in determining preliminary values of the spanwise-load_ shear_ bending_moment_ and the accumulated-torque distributions of swept wings of various taper ratios. The charts are based on strip theory and include four aerodynamic-load distributions. The taper ratios considered cover the range from 1.0 to 0_ and the results are applicable to any angle of sweep.

These charts strictly apply to tapered wings having the following geometric characteristics: I. The slopes of the leading and trailing edges are constant along the span.

2. The lines of aerodynamic centers_ elastic centers_ and centers of gravity of the sections are straight and are located at con- stant fractions of the chord behind the leading edge.

3. Ailerons and flaps have constant flap-chord ratios along the span and hence introduce constant values of cm.

4. Any built-in or aerodynamic twist varies linearly along the span.

5. The wing section and hence the pitching-moment coefficient is constant along the span.

The charts will give results that are reasonably accurate when compared with distributions determined by means of more accurate and laborious methods. On the basis of these results_ the charts may be considered as being applicable in preliminary design work.

PRELIMINARY EXPERIMENTAL INVESTIGATION OF EFFECTS OFAERODYNAMIC RML9EI7 SHAPE OF CONCENTRATED WEIGHTS ONFLUTTER OF A STRAIGHT CANTILEVER WING_John L. Sewall and Donald S. Woolston_ July 1949 Results are presented to show the effect on flutter characteris- tics of variation of the aerodynamic shape of concentrated weights rigidly mounted on a simplified wing structure. The model was mounted as a rigid cantilever and tested with weights that were 7½percent and 5 percent of the weight of the wing. In regard to shape_ two general types of weights_ having similar mass and moment-of-inertia properties_ were employed: one a streamlined body resembling in shape an external wing fuel tank and the other a chosen nonstreamlined_ or blunt_ body. Approximately 20 flut- ter tests were conducted in a preliminary program at low Mach numbers with weights varied over a wide range of spanwise posi- tions; an additional chordwise position was included at the wing tip. The concentrated weights were selected so that the ratio of their weights to that of the wing was comparable to the ratio of the weights of an empty external fuel tank and the wing of a typical airplane.

RML53K02aA COMPILATION OF EXPERIMENTAL FLUTTER INFORMATION_ H. J. Cunningham and Harvey H. Brown_ January 1954 Somesalient results of much of postwar experimental research in the U. S. on flutter of simplified wing and wing-aileron models are compiled and references to the sources are given. Tabulated material is grouped as follows: (i) wings without concentrated weights_ (2) wings with concentrated weights_ (3) delta and tri- angular wings_ and (4) wings with control surfaces. Plots are included to show experimental coverage of ranges of aspect ratio_ Mach number_and sweep angle for flexure-torsion flutter of simply constructed models.

Not Applicable NACA Research Memoranda RMA7C28 A SUMMARY REPORT ON THE EFFECTS OF MACH NUMBER ON THE SPAN LOAD DISTRIBUTION ON WINGS OF SEVERAL MODELS_ Henry Jessen, Jr._ July RMA7GI7 COMPARISON BETWEEN FLIGHT-MEASURED AND CALCULATED SPAN LOAD DISTRIBUTION AT HIGH MACH NUMBERS_ L. Stewart Rolls_ November 1947 RMA5IJl0 AN INVESTIGATION OF THE CONTROL-SURFACE FLUTTER DERIVATIVES OF AN NACA 651-213 AIRFOIL IN THE AMES 16-FOOT HIGH-SPEED WIND TUNNEL_ John A. Wyss and Robert M. Sorenson_ December 1951 RMA54A29 AN EXPERIMENTAL INVESTIGATION OF THE FLUTTER OF SEVERAL WINGS OF VARYING ASPECT RATIO_ DENSITY_ AND THICKNESS RATIO AT MACH NUMBERS 0.60 TO I. i0_ Raymond Herrera and Robert H. Barnes_ April 1954 RMA54C24 EFFECTS OF AIRFOIL PROFILE ON THE TWO-DIMENSIONAL FLUTTER DERIVA- TIVES FOR WING OSCILLATING IN PITCH AT HIGH SUBSONIC SPEEDS_ John A. Wyss and James C. Monfort_ May 1954 RMA54E03 FORCES AND MOMENTS ON INCLINED BODIES AT MACHNUMBERS FROM 3.0 TO 6.3_ David H. Dennis and Bernard E. Cunningham_ June 1954 RMA54HI2 EFFECTS OF ANGLE OF ATTACK AND AIRFOIL PROFILE ON THE TWO- DIMENSIONAL FLUTTER DERIVATIVES FOR AIRFOILS OSCILLATING IN PITCH AT HIGH SUBSONIC SPEEDS_ John A. Wyss and Raymond Herrera_ October RMA54128 THE EFFECT OF STICK-FORCE GRADIENT AND STICK GEARING ON THE TRACK- ING ACCURACY OF A FIGHTER AIRPLANE_ Marvin Abramovitz and Rudolph D. Van Dyk% Jr._ December 1954 RMA55AO 6 SUMMARY OF THE FLIGHT CONDITIONS AND MANEUVERS IN WHICH MAXIMUM WING AND TAlL LOADS WERE EXPERIENCED ON A SWEPT-WING FIGHTER AIR- PLANE_ Melvin Sadoff_ March 1955 RMA55D06 A METHOD FOR EVALUATING THE LOADS AND CONTROLLABILITY ASPECTS OF THE PITCH-UP PROBLEM_ Melvin Sadoff_ Frederick H. Matteson_ and C. Dewey Havill 3 August 1955 RMA55EI7 LOAD DISTRIBUTIONS ON WINGS AND WING-BODY COMBINATIONS AT HIGH ANGLES OF ATTACK AND SUPERSONIC SPEEDS_ Elliott D. Katzen and William C. Pitts_ July 1955 RM A55 O38 COMPARISON BETWEEN ANALYTICAL AND WIND-TUNNEL RESULTS ON FLUTTER OF SEVERAL LOW-ASPECT-RATIO_ HIGH-DENSITY_ UNSWEPT WINGS AT HIGH SUBSONIC SPEEDS AND ZERO ANGLE OF ATTACK_ Robert W. Warner_ September 1955 AN EXPERIMENTAL INVESTIGATION OF THEHINGE-MOMENT CHARACTERISTICS RMA55J24 OFA CONSTANT-CHORD CONTROL SURFACE OSCILLATING AT HIGHFREQUENCY, David E. Reese, Jr._ and William C. A. Carlson_ December1955 RME8B04 EFFECT OF AERODYNAMIC HYSTERESIS ONCRITICALFLUTTER SPEED AT STALL_Alexander Mendelson_June 1948 RME57GII ACCELERATIONS IN FIGHTER-AIRPLANE CRASHES [with list of references ]j Loren W. Acker, Sugald O. Black_ and Jacob C. Moser_ November1957 RMH57DI7a AIRPLANE MOTIONS AND LOADS INDUCED BY FLYING THROUGH FLOW FIELD GENERATED BY AIRPLANE AT LOW SUPERSONIC SPEEDS [with list of references], Gareth H. Jordan_ Earl R. Keener_ and Stanley P.

Butchart, June 1957 RM H57EO i FLIGHT MEASUR/_qENTS AND CALCULATIONS OF WING LOADS AND LOAD DISTRIBUTIONS AT SUBSONIC, TRANSONIC, AND SUPERSONIC SPEEDS 3 Frank S. Malvestuto_ Thomas V. Cooney_ and Earl R. Keener_ July AN ANALYSIS OF SURFACE PRESSURES AND AERODYNAMIC LOAD DISTRIBUTION RM H58A30 OVER THE SWEPT WING OF THE DOUGLAS D-558-II RESEARCH AIRPLANE AT MACH NUMBERS FROM 0.73 TO 1.73j Norman V. Taillon 3 April 1958 RM H58C26 CONTROL DEFLECTIONS_ AIRPLANE RESPONSE_ AND TAIL LOADS MEASURED ON AN F-100A AIRPLANE IN SERVICE OPERATIONAL FLYING, Chris Pembo and Gene J. Matranga_ June 1958 RM H58D29 EFFECT OF LEADING-EDGE-FLAP DEFLECTION ON THE WING LOADS, LOAD DISTRIBUTIONS_ AND FLAP HINGE MOMENTS OF THE DOUGLAS X-3 RESEARCH AIRPLANE AT TRANSONIC SPEEDS 3 Earl R. Keener_ Norman J. McLeod, and Norman V. Taillon, July 1958 RM L7GI8 EXPERIMENTAL INVESTIGATION OF A PRELOADED SPRING-TAB FLUTTER MODEL 3 N. H. Smith, S. A. Clevenson_ and J. G. Barmby_ December 1947 RM L8C30 FLIGHT INVESTIGATION OF LOADS ON A BUBBLE-TYPE CANOPY, Cloyce E.

Matheny and Wilber B. Huston; October 1948 RM LgEI7 PRELIMINARY EXPERIMENTAL INVESTIGATION OF EFFECTS OF AERODYNAMIC SHAPE OF CONCENTRATED WEIGHTS ON FLUTTER OF A STRAIGHT CANTILEVER WlNGj John L. Sewall and Donald S. Woolston, July 1949 RM L53DI6 LOADS EXPERIENCED IN FLIGHTS OF TWO SWEPT-WING RESEARCH AIRPLANES IN THE ANGLE-OF-ATTACK RANGE OR REDUCED STABILITY, Hubert M. Drake_ Glenn H. Robinson and Albert E. Kuhl; June 1953 RML53E05a SOME MEASURemENTS OFLANDING CONTACT CONDITIONS OF TRANSPORT AIRPLANES IN ROUTINE OPERATIONS_ NormanS. Silsby_ EmanuelRind_ and Garland J. Morris, July 1953 RML53E08 A SUMMARY OF DATAONTHEDIVISION OF LOADS FORVARIOUS WING- FUSELAGE COMBINATIONS_ Clarence L. Gillis_ June 1953 RML53EI8a DISCUSSION OF THREE-DIMENSIONAL OSCILLATING AIR FORCES BASED ON WIND-TUNNELMEASUREMENTS_ ShermanA. Clevenson_ SumnerA. Lead- better and WeimerJ. Tuovila_ June 1953 RML53130 AERODYNAMIC LOAD MEASUREMENTS ANDOPENING CHARACTERISTICS OFAUTO- MATICLEADING-EDGE SLATS ONA 45° SWEPTBACK WING AT TRANSONIC SPEEDS_ Donald D. Arabian_ Jack F. Runckel_ and Charles F. Reid_ Jr._ April 1954 RML54B24 TRANSONIC AERODYNAMIC ANDLOADS CHARACTERISTICS OF A 4-PERCENT- THICKUNSWEPT-WING - FUSELAGE COMBINATION_ Gerald Hieser_ James H. Henderson_and John M. Swihart_ May 1954 RML54C22 FREE-FLIGHT TESTS OF 45° SWEPT WINGS OF ASPECT RATIO3.15 AND TAPER RATIO0.54 TOMEASURE WING DAMPING OFFIRST BENDING MODE ANDTO INVESTIGATE POSSIBILITYOF FLUTTER AT TRANSONIC SPEEDS_ Burke R. O'Kelly_ Reginald R. Lundstrom_ and William T. Lauten_ Jr._ October 1954 RML54EI8 COMPARISON OFNORMAL LOAD FACTORS EXPERIENCED WITHJET FIGHTER AIRPLANES DURING COMBAT OPERATIONS WITHTHOSE OFFLIGHTTESTS CONDUCTED BYNACA DURING OPERATIONAL TRAINING [with list of references]_ Harold A. Hamer_Carl R. Huss_ and John P. Mayer_ June 1954 RML54G23 ANALYSIS OF V-G RECORDS FROM I0 TYPES OFNAVY AIRPLANES IN SQUAD- RON OPERATIONS DURING PERIOD 1949 TO 1953_ John P. Mayer and Agnes E. Harris_ March 1955 RML54HI8 AN INVESTIGATION OF THEEFFECTS OF A GEOMETRIC TWISTONTHEAERO- DYNAMIC LOADING CIARACTERISTICS OFA 45° SWEPTBACK WING-BODY CONFIGURATION AT TRANSONIC SPEEDS_ Claude V. Williams_ October RML54KI7 RESULTS OF INITIAL WIND-TUNNEL FLUTTER EXPERIMENTS AT LOWSPEED WITHA TOWED AIRPLANE MODEL HAVING A 40° SWEPTBACK WING OF ASPECT RATIO3.62 EQUIPPED WITHPYLON-MOUNTED STORES_ Albert P. Martina and George E. Young_March 1955 MODEL INVESTIGATION OF THEEFFECT OFMOUNTING HYDRO-SKIS ONSHOCK RML54L02 ABSORBERS, EdwardL. Hoffman and Lloyd J. Fisher, March 1955 CHARACTERISTICS OF LOADS IN ROUGH AIR AT TRANSONIC SPEEDS OF RML54LI7 ROCKET-POWERED MODELS OF A CANARD AND A CONVENTIONAL-TAIL CONFIG- URATION, A. James Vitale, March 1955 TRANSONIC FLUTTER INVESTIGATION OF A FIGHTER-AIRPLANE WING MODEL RM L55BI6 AND COMPARISON WITH A SYSTEMATIC PLAN-FORM SERIES, Norman S. Land and Frank T. Abbott, Jr., October 1955 SOME EFFECTS OF CONFIGURATION VARIABLES ON STORE LOADS AT RM L55E05 SUPERSONIC SPEEDS, Norman F. Smith and Harry W. Carlson, July 1955 SOME RECENT EXPERIMENTAL DATA ON THREE-DIMENSIONAL OSCILLATING AIR RM L55E09 FORCES, Sumner A. Leadbetter and Sherman A. Clevenson, June 1955 RM L55EI2a LOADS ASSOCIATED WITH SPOILERS AT SUPERSONIC SPEEDS, Douglas R.

Lord and K. R. Czarnecki, June 1955 VERTICAL AND DRAG GROUND-REACTION FORCES DEVELOPED IN LANDING RM L55EI2c IMPACTS OF LARGE AIRPLANE [with list of references], Richard H.

Sawyer, Albert W. Hail, and James M. McKay_ June 1955 RM L55EI3a A STUDY OF MEANS FOR RATIONALIZING AIRPLANE DESIGN LOADS_ John P.

Mayer and Harold A. Hamer_ June 1955 RM L55EI3b LOADS ON EXTERNAL STORES AT TRANSONIC AND SUPERSONIC SPEEDS, Lawrence D. Guy, July 1955 RM L55EI7a LOADS ON WINGS DUE TO SPOILERS AT SUBSONIC AND TRANSONIC SPEEDS, Alexander D. Hammond, June 1955 RM L55EI8b EXPERIMENTAL AND THEORETICAL STUDIES OF PANEL FLUTTER AT MACH NUMBERS 1.2 TO 3.0, Maurice A. Sylvester, Herbert C. Nelson, and Herbert J. Cunningham, July 1955 RM L55EI9a FLUTTER CHARACTERISTICS OF SWEPT WINGS AT TRANSONIC SPEEDS, Laurence K. Loftin, Jr., July 1955 RM L55E31b EXPLORATORY INVESTIGATION OF THE MOMENTS ON OSCILLATING CONTROL SURFACES AT TRANSONIC SPEEDS, Dennis J. Martin_ Robert F. Thomp- son, and C. William Martz, August 1955 RM L55FI0 SOME EFFECTS OF FLUID IN PYLON-MOUNTED TANKS ON FLUTTER [with list of references], James R. Reese, July 1955 RM L55HI2 AERODYNAMIC LOADS ON AN EXTERNAL STORE ADJACENT TO A 45 ° SWEPTBACK WING AT MACHNUMBERS FROM 0.70 TO 1.96, INCLUDING AN EVALUATION OF TECHNIQUES USED, Lawrence D. Guy and William M. Hadaway_ November 1955 RML55H22b INITIAL EXPERIMENTAL INVESTIGATION OF THEAERODYNAMIC LOAD ONTHE WING OFA MODEL CAUSED BYA BLAST-INDUCED GUST THATINCREASES THE ANGLE OF ATTACK INTOTHESTALLREGION_ Harold B. Pierce and Thoma_ D. Reisert_ December1955 RML55113a SOME EFFECTS OF SWEEP ANDASPECT RATIOONTHETRANSONIC FLUTTER CHARACTERISTICS OFA SERIES OF THIN CANTILEVER WINGS HAVING A TAPER RATIOOF0.6_ John R. Unangst and GeorgeW. Jones_ Jr._ January 1956 RML55J03 PRESSURE DISTRIBUTIONS ANDAERODYNAMIC LOADINGS FORSEVERAL FLAP- TYPETRAILING-EDGE CONTROLS ONA TRAPEZOIDAL WING AT MACH NUMBERS OF 1.61 AND2.01_ Douglas R. Lord and K. R. Czarnecki_ March 1956 RML55J21 FREE-FLIGHT FLUTTER TESTS IN THETRANSONIC ANDLOWSUPERSONIC SPEED RANGE OF THREE LOW-ASPECT-RATIO_ SWEPT_ TAPERED WINGS ON ROCKET-PROPELLED VEHICLES_ William T. Lautenj Jr. 3 and Burke R.

O'Kelly_ March 1956 RML55KI7 OSCILLATING HINGE MOMENTS ANDFLUTTER CHARACTERISTICS OF A FLAP- TYPECONTROL SURFACE ONA 4-PERCENT-THICKUNSWEPT WING WITHLOW ASPECT RATIOAT TRANSONIC SPEEDS_ Robert.F. Thompson and William C. Moseley_ Jr._ February 1956 RML55K30 INVESTIGATION TODETERMINE EFFECTS OF CENTER-OF-GRAVITY LOCATION ONTHETRANSONIC FLUTTER CHARACTERISTICS OF A 45° SWEPTBACK WING_ GeorgeW. Jones_ Jr._ and John R. Unangst_ February 1956 RML55L22 EXPERIMENTAL TRANSONIC FLUTTER CHARACTERISTICS OFAN UNTAPERED_ 45o SWEPTBACK_ ASPECT-RATIO-4 WING_ Charles L. Ruhlin_ March 1956 RML55L30b THEORETICAL PREDICTION OF THESIDEFORCE ONSTORES ATTACHED TO CONFIGURATIONS TRAVELING AT SUPERSONIC SPEEDS_ Percy J. Bobbitt_ Frank S. Malvestuto_ Jr._ and Kenneth Margolis_ March 1956 RML56B0 2 TRANSONIC INVESTIGATION OF THEEFFECTIVENESS ANDLOADING CHARAC- TERISTICS OFA FLAP-TYPE AILERON WITHANDWITHOUT PADDLE BALANCES ONAN UNSWEPT-WING - FUSELAGE MODEL_ Gerald Hieser_ April 1956 RML56FI2 INVESTIGATION AT TRANSONIC SPEEDS OF THELOADING OVER A 45° SWEPT.

BACK WING HAVING AN ASPECT RATIOOF 3_ A TAPER RATIOOF0.2_ AND NACA 65A004AIRFOIL SECTIONS_ Jack F. Runckel and Edwin E. Lee_ Jr._ October 1956 RML56FI4a FLUTTER INVESTIGATION AT LOWSPEED OF A 40° SWEPTBACK WING WITH PYLON-MOUNTED STORES# TESTED AS A S_ISPAN-CANTILEVER WING AND AS A FULL-SPAN WING ONA TOWED AIRPLANE MODEL_ Albert P. Martina 3 September 1956 EXPERIMENTAL STUDY ANDANALYSIS OFLOADING ANDPRESSURE DISTRIBU- RML56114 TIONSONDELTA WINGS DUETO THICKNESS ANDTOANGLE OF ATTACK AT SUPERSONIC SPEEDS, William B. Boatright, December1956 TANKINVESTIGATION OF A SERIESOF RELATED HYDRO-SKIS AS LOAD- RML56125a ALLEVIATION DEVICES FORLANDING A SEAPLANE IN WAVES, Arthur W.

Carter, Archibald E. Morse, Jr., and David R. Woodward,December RML56126 MEASUREMENTS OF RUNWAY ROUGHNESS OF 4 COMMERCIAL AIRPORTS [with one reference]_ Dexter M. Potter, January 1957 TRANSONIC FLUTTER INVESTIGATION OF TWO 64° DELTA WINGS WITHSIMU- RML56127 LATED STREAMWISE RIB ANDORTHOGONAL SPAR CONSTRUCTION, GeorgeW.

Jones, Jr._ and Lou S. Young, Jr., January 1957 FLUTTER CHARACTERISTICS AT TRANSONIC SPEEDS OF A 45° SWEPTBACK WING RML56128 WITHANDWITHOUT INBOARD MODIFICATIONS AT THELEADING ANDTRAILING EDGES, ThomasB. Sellers and NormanS. Land, January 1957 TRANSONIC WIND-TIFNNEL INVESTIGATION OF AERODYNAMIC-LOADING CHAR- RML56J12a ACTERISTICS OF A 2-PERCENT-THICK TRAPEZOIDAL WINGIN COMBINATION WITHBASICANDINDENTED BODIES,ThomasC. Kelly, January 1957 RML56JI5 APPLICATIONS OF POWER SPECTRAL ANALYSIS METHODS TOMANEUVER LOADS OBTAINED ONJET FIGHTER AIRPLANES DURING SERVICE OPERATIONS_ John P. Mayer and Harold A. Hamer, January 1957 TOLERABLE LIMITS OF OSCILLATORY ACCELERATIONS DUETO ROLLING MO- RML56K20 TIONSEXPERIENCED BY ONEPILOT DURING AUTOMATIC-INTERCEPTOR FLIGHT TESTS_ Roy F. Brissenden, Donald C. Cheatham, and Robert A. Cham- pine, January 1957 RML56K26 FLUTTER INVESTIGATION IN HIGHSUBSONIC ANDTRANSONIC SPEED RANGE ONCANTILEVER, DELTA-WING PLANFORMS WITHLEADING-EDGE, SWEEPBACK OF 60o, 53°8'_ AND45°_ William T. Lauten, Jr., and Marvin F.

Burgess_ January 1957 INVESTIGATION OF TRANSONIC FLUTTER CHARACTERISTICS OF A THIN i0 ° RML56LI4a SWEPTBACK WING HAVING .ANASPECT RATIOOF4 ANDA TAPER RATIOOF 0.6, GeorgeW. Jones, Jr., February 1957 RML57AI5 STATISTICAL APPROACH TO THEESTIMATION OF LOADS ANDPRESSURES ON SEAPLANE HULLS FORROUTINE OPERATIONS, Roy Steiner, March 1957 RML57A24 AN EXPERIMENTAL INVESTIGATION OF THEEFFECTS OFMACHNUMBER_ STABILIZER DIHEDRAL, ANDFIN TORSIONAL STIFFNESS ONTHETRANSONIC FLUTTER CHARACTERISTICS OFA TEE-TAlL, NormanS. Land and Annie G. Fox_ October 1957 RM L57A28a EXPERIMENTAL INVESTIGATION TO DETERMINE THE LOADS ON A HORIZONTAL TAlL OF A MODEL CAUSED BY A BLAST-INDUCED GUST_ Harold B. Pierce and Raymond J. Spahl_ March 1957 RM L57C19 INVESTIGATION AT MACH NUMBERS TO 1.04 OF BLADE-LOADING CHARACTERIS- TICS OF TWO FULL-SCALE THREE-BLADE SUPERSONIC PROPELLERS DIFFER- ING IN BLADE-SECTION CAMBER_ Leland B. Salters_ Jr._ September RM L57DI2 TRANSONIC LOADS CHARACTERISTICS OF A 3-PERCENT-THICK 60 ° DELTA- WING - BODY COMBINATION_ John M. Swihart and Willard E. Foss_ Jr._ May 1957 RM L57DI6a FLUTTER AT VERY HIGH SPEEDS_ Harry L. Runyan and Homer G. Morgan_ June 1957 RM L57DI9b RECENT DATA ON TIRE FRICTION DURING LANDING [with one reference]_ Sidney A. Batterson_ June 1957 RM L57D22a EXPERIMENTAL RESULTS ON WING LOADS DUE TO BLASTS_ Harold B° Pierce and Donald R. McFarland_ May 1957 RM L57D23b AIR LOAD DISTRIBUTIONS ON A FLAPPED WING RESULTING FROM LEADING- EDGE AND TRAILING-EDGE BLOWING_ H. Clyde McLemore_ June 1957 RM L57D24a SPAN LOADINGS DUE TO WING TWIST AT TRANSONIC AND SUPERSONIC SPEEDS_ Frederick C. Grant and John P. Mugler_ Jr._ July 1957 RM L57D24b STEADY LOADS DUE TO JET INTERFERENCE ON WINGS_ TAILS_ AND FUSE- LAGES AT TRANSONIC SPEEDS_ John M. Swihart and Norman Lo Crabill_ May 1957 RM L57D24c STATUS OF FLUTTER OF FLAT AND CURVED PANELS_ Robert W. Leonard and John M. Hedgepeth_ May 1957 RM L57D25 THE USE OF WIND TUNNELS TO PREDICT FLIGHT BUFFET LOADS_ Don D.

Davis_ Jr._ and Wilber B. Huston_ June 1957 RM L57D29a INVESTIGATION AT MACH NUMBERS FROM 0.80 TO 1.43 OF PRESSURE AND LOAD DISTRIBUTIONS OVER A THIN 45 ° SWEPTBACK HIGHLY TAPERED WING IN COMBINATION WITH BASIC AND INDENTED BODIES_ Thomas L. Fischetti_ June 1957 RM L57EI5 EXPERIMENTAL INVESTIGATION OF WING-AILERON FLUTTER CHARACTERIS- TICS OF I/4-SCALE DYNAMIC MODEL OF X-IE AIRPLANE_ Frederick W.

Gibson_ William B. Igoe_ and P. R. Maloney_ July 1957 RM L57E23 TRANSONIC FLUTTER INVESTIGATION OF A CANTILEVERED_ ASPECT-RATIO-4_ 45 ° SWEPT-BACKj UNTAPERED WING WITH THREE DIFFERENT PYLON-MOUNTED EXTERNAL-STORE CONFIGURATIONS_ Charles L. Ruhlin and Robert W.

Boswinkle_ Jr._ July 1957 EFFECTS OF CONTROL PROFILE ONTHEOSCILLATING HINGE-MOMENT AND RML57E27 FLUTTER CHARACTERISTICS OF A FLAP-TYPE CONTROL AT TRANSONIC SPEEDS_ William C. Moseley_ Jr._ and GeorgeW. Price_ Jr._ August RML57F24 FLUTTER ANDDIVERGENCE OF RECTANGULAR WINGS OF VERY LOWASPECT RATIO_Robert W. Fralich_ John M. Hedgepethand W. J. Touvila_ June 1957 RML57GO i TRANSONIC FLUTTER INVESTIGATION OF A 64° DELTA WING CONSTRUCTED WITHSPARS ALONG CONSTANT-PERCENT CHORD LINES ANDSTREAMWISE RIBS_ GeorgeW. Jones_ Jr._ August 1957 RML57GO9a INVESTIGATION AT TRANSONIC SPEEDS OFLOADING OVER A 30° SWEPTBA_K WING OF ASPECT RATIO3_ TAPER RATIO0.2_ ANDNACA65A004AIRFOIL SECTION MOUNTED ONA BODY_ Donald D. Arabian_ September 1957 RML57H22 TRANSONIC FLUTTER INVESTIGATION OFARROWHEAD WING WITHTIP AILER- ONSANDTRAILING-EDGE FLAPS_GeorgeW. Jones_ Jr._ and Robert W.

Boswinkle_ Jr._ November1957 AERODYNAMIC LOAD DISTRIBUTION OVER A 45° SWEPT WING HAVING A RML57JII SPOILER-SLOT-DEFLECTOR AILERON ANDOTHER SPOILER AILERONS FOR MACH NUMBERS FROM 0.60 TO 1.03_ F. E. West_ Jr._ Charles F. Whit- comb_and JamesW. Schmeer_December1957 RML57J14a TRANSONIC FLUTTER INVESTIGATION OF TWO 50° SEMISPAN MODIFIED- DELTA WINGS WITHTIP AILERONS_ Robert J. Platt_ Jr._ February RML57J25 EXPERIMENTAL HINGE MOMENTS ONTWO FREELY OSCILLATING TRAILING-EDGE CONTROLS HINGED AT 55 PERCENT CONTROL CHORD_ C. William Martz_ December1957 RML57KI5a EFFECT AT HIGHSUBSONIC SPEEDS OFFUSELAGE FOREBODY STRAKES ONTHE STATICSTABILITYANDVERTICAL-TAIL-LOAD CHARACTERISTICS OFA COM- PLETE MODEL HAVING A DELTA WING_Edward C. Polhamusand Kenneth P. SpreemannjFebruary 1958 RML57L02 AERODYNAMIC LOAD DISTRIBUTION ONA 45° SWEPTBACK WING WITHLEADING- EDGE CHORD-EXTENSIONS AT TRANSONIC SPEEDS_ INCLUDING EFFECTS OFA SPOILER-SLOT-DEFLECTOR AILERON 3 JamesW. Schmeer_Charles F.

Whitcomb_and F. E. West_ Jr._ February 1958 RML57LI0 CALCULATION OFFLUTTER CHARACTERISTICS FORFINITE-SPANSWEPT OR UNSWEPT WINGS AT SUBSONIC ANDSUPERSONIC SPEEDS BYA MODIFIED STRIPANALYSIS_ E. Carson Yates_ Jr._ March 1958 RML58B25 EFFECT OF CONTROL TRAILING-EDGE THICKNESS ORASPECT RATIOON OSCILLATING HINGE-MOMENT ANDFLUTTER CHARACTERISTICS OFFLAP-TYPE CONTROL AT TRANSONIC SPEEDS_ William C. Moseley_ Jr._ and Robert F. Thompson_ April 1958 RML58C28a LANDING ANDTAXIINGTESTS OVER VARIOUS TYPES OF RUNWAY LIGHTS [with list of references]_ Robert C. Dreher and Sidney A. Batter- son_ August 1958 RML58DI7 SOME EFFECTS OFMASS RATIOONTHETRANSONIC FLUTTER CHARACTERIS- TICS OFUNTAPERED 45° SWEPTBACK WINGS OF ASPECT RATIOS 2 AND3.5_ H. Neale Kelly_ June 1958 RML58F 25 MEASURI_IENTS OF THEBUFFETING LOADS ONTHEWING ANDHORIZONTAL TAlL OFA I/4-SCALE MODEL OF THEX-IE AIRPLANE_ A. Gerald Rainey and William B. Igo% September 1958 Applicable NACA Technical Memoranda TM 948 A SIMPLE APPROXIMATION METHOD FOR OBTAINING THE SPANWISE LIFT DISTRIBUTION_ O. Schrenk_ August 1940 A simple approximation method is presented for rapidly computing the lift distributions of arbitrary airfoils. Comparison with an exact method shows satisfactory agreement. The method includes the important case of the wing with end plates.

TM 1117 FORCE AND PRESSURE-DISTRIBUTION MEASUR_IENTS ON A RECTANGULAR WING WITH DOUBLE-HINGED NOSE_ H. A. Lemme_ March 1947 Previous measurements on airfoils with hinged nose disclosed a comparatively large low-pressure peak at the bend of the hinged nose_ which favored the separation of flow. It was therefore attempted to reduce these low-pressure peaks by reducing the camber of the forward profile and thereby ensure a longer adherence of the flow and a maximum lift increase.

The forces were measured on a rectangular wing with double-hinged nose and end platesj the pressure distributions were measured in the center section of the wing.

The measurements disclosed that the highest lift attained with a single-hinged nose cannot be increased by a double-hinged nose.

The sum of the deflection angles of both hinged noses related to the maximum lift was about equal to the corresponding angle of the single-hinged (30 ° to 40o). The respective angle of attack in both cases amounted to approximately 21 ° . Even the low-pressure peak was about the same in both cases (p/q = -5.5). Therefor% a milder curvature of the forward portion of the profile afforded no definite increase of the maximum lift.

TM 1126 PRESSURE-DISTRIBUTION MEASUREMENTS ON A STRAIGHT AND ON A 35 ° SWEPT-BACK TAPERED WING_ A. Thiel and J. Weissinger_ January 1947 The spanwise lift-distribution measurements in straight air flow on a straight and a 35 ° swept-back tapered wing (NACA airfoil section 0012) were compared with theory for two angles of attack each (_ = 6° and _ = 12 ° ) in the unstalled range of flow. The complete pressure distribution for the greater of the two angles was indicated.

Figures were given representing the chordwise pressure distribution for _ = approximately 12 °. Figures were also given for spanwise lift distributions of both wings.

TM 1164 PRESSURE-DISTRIBUTION MEASUREMENTS ON UNYAWED SWEPT-BACK WINGS_ W. Jacobs_ July 1947 This report was a comprehensive report on pressure distribution of swept-back wings. Experimental results were compared with the theory of Weissinger and Multhopp. The purpose was to isolate effects of sweepback on load distributions. Tests were carried out at extremely low Reynolds numbers such as 4.5xi05.

The wing section was the NACA 23012. The report first gave the aerodynamic characteristics of the wing section for each angle of sweepback. Contrary to theory and previous American experiments_ CL increased only to a 30° sweepback angle_ and then decreased; this may be due to Reynolds number_ but the cause was not defin- itely determined. The drag increased with sweepback angle_ es- pecially as CL increased.

Pressure distribution measurements indicated that lift distribu- tion with span increased toward the tip with increasing sweepback.

That is_ as sweepback is increased_ the outer portion of the wing becomes more heavily loaded while the center sections become more lightly loaded.

Results showed both Weissenger and Multhopp to be very inaccurate in the prediction of lift increases with sweepback. Weissenger was superior in predictions of lift distribution.

The purpose of the report was to compare accuracy of theories of Weissenger and Multhopp_ and it merely concluded that the theory of Weissenger is superior to that of Multhopp.

TM 1177 WIND-TUNNEL INVESTIGATIONS ON A CHANGED MUSTANG PROFILE WITH NOSE FLAP FORCE AND PRESSURE-DISTRIBUTION MEASUR_ENTS_ W. Kruger_ September 1947 The Mustang 2 profile used in the report was not defined. Tests were run at a Reynolds number of 2°14xi06. The wing was tested with a nose flap and a split flap.

Effect of nose flap: increased maximum lift and maximum angle of attack.

Pressure distribution for deflected nose flap: The nose flap reduced the maximum negative pressure peak at the profile nose.

The flap tended to delay separation.

Effect of the curvature of the leading edge of nose flap: In general_ increasing curvature of leading edge of flap increased the lift-increasing effect of the nose flap.

Effect of disturbances at flap-wing transition: a small groove at the juncture was found to have no effect on the results. Any leakage from flap pressure side to suction side will reduce the effects of the flap considerably_ about 30 to 50%.

TM 1194 FORCE- ANDPRESSURE-DISTRIBUTION MEASURI_IENTS ONEIGHTFUSELAGES_ G. Lange_ October 1948 This report deals with force- and pressure-distribution measure- ments on a number of fuselage forms of varying slenderness ratio_ varying rearward position of maximumthickness_ and varying nose ratio. The effect of these parameters on force and momentcoeffi- cients was determined.

TM1220 PRESSURE-DISTRIBUTION MEASURE_IENTS ONTHETAIL SURFACES OF A ROTATING MODEL OF THEDESIGN BFW - M 31_ M. Kohler and W. Mautz_ December1949 The model was a low-wing monoplanewith open cock-pit and fixed conventional gear. Rotation was about an axis through the pilot's seat and could be adjusted for angle of attack and yaw angle.

The angle of attack for all measurementswas 60° . Elevator deflec- tion_ rudder deflectionj yaw angle and freestream velocity were varied.

The most interesting result was that for all arrangements investi- gated in rotation_ the pressures on the vertical tail surfaces had the effect of originating a force in the direction of rotation.

Thus the vertical surface tends to reinforce the spin under test conditions. This is because the vertical tail surfaces lie com- pletely in the region of separated flow of the horizontal_tail_ surface suction side. The result is that the negative pressures on the suction side and the positive pressures on the pressure side always lie higher on the leading than on the trailing wing.

Not Applicable NACA Technical Memoranda TM 963 CHORDWISE LOAD DISTRIBUTION OF A SIMPLE RECTANGULAR WING, Karl Wieghardt, December 1940 TM 1041 TAIL BUFFETING, G. Abdrashitov, February 1943 TM 1046 EXPERIMENTAL INVESTIGATION OF IMPACT IN LANDING ON WATER, R. L.

Kreps, August 1943 TM 1153 CALCULATION OF THE PRESSURE DISTRIBUTION ON BODIES OF REVOLUTION IN THE SUBSONIC FLOW OF A GAS PART - AXIALLY SYMMETRICAL FLOW, H. Bilharz and E. Holder, July 1947 TM 1247 LANDING PROCEDURE IN MODEL DITCHING TESTS OF BF 109, W. Sottorf, December 1949 TM 1257 VIBRATION OF A WING OF FINITE SPAN IN A SUPERSONIC FLOW, M. D.

Haskind and S. V. Falkovich, April 1950 Applicable NASA Technical Translation There were no applicable aerodynamic loads reports in the NASA technical translation series.

Not Applicable NASA Technical Translations TT F 25 SMALL OSCILLATIONS OF THIN RESILIENT CONICAL SHELLS, E. I.

Grigolyuk, May 1960 TT F 52 THE EFFECT OF THE BEHAVIOR OF THE LOAD ON THE FREQUENCY OF THE FREE VIBRATIONS OF A RING, E. B. Wasserman, January 1961 TT F UNSTEADY MOTION OF A WING OF FINITE SPAN IN A COMPRESSIBLE MEDIUM, E. A. Krasilshchikova, May 1961 TT F 81 AEROELASTICITY SYMPOSIUM, Gottingen, April 16-17, 1957, September Applicable NASA Technical Memorandum There were no applicable aerodynamic loads reports in the NASA technical memorandum series.

Not Applicable NASA Technical Memoranda TMX 53 EXPERIMENTAL AND CALCULATED RESULTS OF A FLUTTER INVESTIGATION OF SOME VERY LOW ASPECT-RATIO FLAT-PLATE SURFACES AT MACH NUMBERS FROM 0.62 TO 3.00, Perry W. Hanson and Gilbert M. Levey, August TMX 61 WIND-TUNNEL INVESTIGATION OF PRESSURES AND HINGE MOMENTS ON A SWEPTBACK T-MOUNTED HORIZONTAL TAlL AT MACH NUMBERS FROM 0.60 TO 1.075, Robert J. Ward and Joseph M. Hallissy, Jr., November TMX 71 EFFECTS OF GROSS LOAD AND VARIOUS BOW MODIFICATIONS ON THE HYDRO- DYNAMIC CHARACTERISTICS OF A HIGH-SUBSONIC MINE-LAYING SEAPLANE, Walter J. Kapryan, January 1960 TMX 119 AERODYNAMIC LOADING CHARACTERISTICS INCLUDING EFFECTS OF AERO- ELASTICITY OF A THIN-TRAPEZOIDAL-WING-BODY COMBINATION AT A MACH NUMBER OF 1.43, Thomas C. Kelly, September 1959 TMX 123 EFFECT OF WING THICKNESS AND SWEEP ON THE OSCILLATING HINGE-MOMENT AND FLUTTER CHARACTERISTICS OF A FLAP-TYPE CONTROL AT TRANSONIC SPEEDS, William C. Moseley, Jr° and Thomas G. Gainer, October 1959 TMX 129 PRESSURE DISTRIBUTION INDUCED ON A FLAT PLATE AT A FREE-STREAM MACH NUMBER OF 1.39 BY ROCKETS EXHAUSTING UPSTREAM AND DOWNSTREAM, Abraham Leiss, December 1959 TMX 135 TRANSONIC FLUTTER CHARACTERISTICS OF A 45 ° SWEPTBACK WING WITH VARIOUS DISTRIBUTIONS OF BALLAST ALONG THE LEADING EDGE, John R.

Unangst, December 1959 TMX 136 TRANSONIC FLUTTER CHARACTERISTICS OF AN ASPECT-RATIO-4, 45 ° SWEPT- BACK, TAPER-RATIO-0.2 PLAN FORM, John R. Unangst, December 1959 TMX 182 SOME EFFECTS OF VARIATIONS IN DENSITY AND AERODYNAMIC PARAMETERS ON THE CALCULATED FLUTTER CHARACTERISTICS OF FINITE-SPAN SWEPT AND UNSWEPT WINGS AT SUBSONIC AND SUPERSONIC SPEEDS, E. Carson Yates, Jr., January 1960 TMX 183 USE OF EXPERIMENTAL STEADY-FLOW AERODYNAMIC PARAMETERS IN CALCU- LATION OF FLUTTER CHARACTERISTICS FOR FINITE-SPAN SWEPT OR UNSWEPT WINGS AT SUBSONIC, TRANSONIC SPEEDS, E. Carson Yates, Jr., January 1960 TMX 239 FIN LOADS AND TIP-CONTROL HINGE MOVEMENTS ON I/8-SCALE MODEL SIMULATING IST STATE OF SCOUT RESEARCH VEHICLE AT MACH NUMBER OF 2.01, Ross B. Robinson and Emma Jean Landrum, April 1960 TMX 275 PRESSURE DISTRIBUTION OF 0.0667-SCALE MODEL OFX-15 AIRPLANE FOR ANGLE-OF-ATTACK RANGE OF 0 ° TO 28 ° AT MACH NUMBERS OF 2.30, 2.88, AND 4.65, B. Leon Hodge and Paige B. Burbank, May 1960 TMX 344 BASIC PRESSURE MEASUREMENTS ON 0.0667-SCALE MODEL OF NORTH AMERICAN X-15 RESEARCH AIRPLANE AT TRANSONIC SPEEDS, Robert S.

Osborne and Virginia C. Stafford, October 1960 TMX 518 LANDING-GEAR BEHAVIOR DURING TOUCHDOWN AND RUNOUT FOR 17 LANDINGS OF X-15 RESEARCH AIRPLANE, James M. McKay and Betty J. Scott, March 1961 TMX 639 LANDING LOADS AND DYNAMICS OF X-15 AIRPLANE, James M. McKay and Eldon E. Kordes, March 1962 NASA-Langley, 1970 _ 2 CR-1485 705