Tests of a NACA 65(sub 1)-213 airfoil in the NASA Langley 0.3-meter transonic cryogenic tunnel

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• NASA-TM-85732 19840011219 T E S T S O F A NACA 651 - 213 AI R F O I L IN TH E N ASA L ANG LE Y 0 . 3 -ME TER TR AN S ON I C CRYOGE NI C TU N NEL E . B . P len t ov i ch ; ,o_ . _o_ : . , _ ; _ ' " ' Cha r l e s L . Ladson Ac qu illa S. Hil l FEBRUARY 1984 !:, . .':_ ,-_' ,.'j_._ ' ._ LANGLEY RESEAI?(%' _", i'_ ER , LIBRARY', NASA Hk YP TON, VIIi, G] NZA #

N ASA

Na t ional Aeronau t ics and Space Administrat i on Langley ResearchCenter Hamp ton, Virginia 23665 TESTS OF A NACA 651-213 AIRFOIL IN THE NASA LANGLEY O.3-METER . TRANSONIC CRYOGENIC TUNNEL E. B. Plentovich, CharlesL. Ladson,and Acquilla S. Hill l ABSTRACT A wind-tunnelinvestigationhas been conductedto study the two-dimensional aerodynamiccharacteristicsof the NACA 651-213 airfoil over a wide range of Reynolds numbers. Test temperatureranged from ambient to about lOOK at pressures ranging from about 1.2 to 6.0 atm. Mach number was varied from 0.22 to 0.80 and Reynolds number (based on airfoil chord) from 3 x 106 to 40 x 106. Data are includedwhich demonstratethe effects of fixed tran- sition, Mach number, and Reynolds number on the aerodynamiccharacteristics of the airfoil. A sample of data showing the effects of angle of attack on the pressure distributionis also given. The data are presentedin an uncorrected form with no analysis in order to expedite the release of the data.

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SUMMARY In cooperative efforts with both the U.S. manufacturers of large transport aircraft and a research establishment in Germany, NASAhas recently undertaken an extensive program to provide a systematic study of both well-known conventional and advanced technology airfoils over a wide range of Reynolds numbers. This airfoil program, referred to as the Advanced Technology Airfoil Tests (ATAT) program, is being conducted in the two-dimensional test section of the Langley O.3-Meter Transonic Cryogenic Tunnel (TCT).

I The results presented in the report are for the NACA651-213 correlation airfoil. The test temperatures ranged from ambient to about lOOK at pressures ranging from about 1.2 to 6.0 atm. Mach number was varied from 0.22 to 0.80.

These variables yielded Reynolds numbers (based on airfoil chord) from about 3 x 106 to 40 x 106. This test was primarily designed to test a NACA651-213 airfoil over a wide range of Reynolds numbers and compare the data to that obtained on the same profile in other facilities.

All the objectives of the test were met. Data are included which demonstrate the effects of fixed transition, Mach number, and Reynolds number on the aerodynamic characteristics of the airfoil. A sample of data showing the effects of angle of attack on the pressure distribution is also provided. The data are presented in an uncorrected Form with no analysis.

INTRODUCTION To augment the commercial aircraft industry's research on energy efficient aircraft, the Langley Aircraft Energy Efficient (ACEE) Project Office has sponsored the Advanced Technology Airfoil Tests (ATAT) program to test airfoils in the O.3-m TCT. The program is divided into four parts: (I) correlation airfoils, (2) an advanced NASAairfoil, (3) the U.S. industry program, with involvement by the Boeing Commercial Airplane Company (BCAC), the Lockheed Aircraft Company (LAC) and the Douglas Aircraft Company (DAC), and (4) a joint program with Deutsche Forschungs-und Versuchsanstalt fur Luft- und Raumfahrt (DFVLR), Federal Republic of Germany. The purpose of the program is to allow industry to test their latest technology airfoils in the O.3-m TCT where flight Reynolds numbers can be obtained at transonic speeds.

Some data would then be made available for use by industry, both foreign and domestic, For compariso,1 of current advanced technology. This program also serves the purpose of providing industry with experience in cryogenic model design and fabrication. A more complete description of the ATAT program is provided in references I and 2.

Results from tests of the Boeing BAC-I airfoil, the first airfoil of the NASA / U.S. industry phase, have been published in reference 3. The first test of the DFVLRCAST10-2 airfoil is described in reference 4.

The correlation airfoils were chosen to establish a relationship between the data obtained in the O.3-m TCT and that obtained at other facilities, such as, the Langley Low Turbulence Pressure Tunnel (LTPT), the Lockheed Aircraft CompanyCompressible Flow Facility (LAC CFF), and the Canadian National Aero- nautical Establishment (NAE) High Reynolds Number 15- x 60-1nch Two-Dimen- sional Transonic Test Facility. The four airfoils chosen as the correlation airfoils were the NACA 0012, NACA 651-213 (description of these two desig- nations can be found in reference5), NASA SC(2)-0510and NASA SC(2)-0714 (descriptonof these designationsis given in reference6). Reported herein are the results of the test program for the NACA 651-213 airfoil. The model was tested in the NASA Langley O.3-m TCT at Mach numbers from 0.22 to 0.80 and " at Reynolds numbers (based on'airfoilchord)from 3 x 106 to 40 x 106. The stagnationpressuresand temperaturesrequired to obtain these conditions varied from 1.2 to 6.0 atm and from ambient,320K, to cryogenic,lOOK, respec- tively. The data taken in this test consisted of model surface pressures, wake survey pressures,and tunnel floor and ceiling pressures. The aerody- namic results are presented in an uncorrectedform .asintegratedforces and moments. Some sample tabulatedpressure data and plots of pressure distri- butions are also included. Copies of the pressure data are availableon microfiche.

• SYMBOLS a mean-line designation;fraction of the chord from leading edge over which loading is uniform at the ideal angle of attack b airfoil model span, cm c airfoil model chord, cm cd section drag-forcecoefficientfrom wake measurements c_ section lift coefficient cm section pitching-moment coefficientabout quarter-chordpoint cn section normal-forcecoefficientfrom airfoil pressures Cp pressure coefficient M freestreamMach number Pt tunnel stagnationpressure,atm (1 atm = 101.3kPa) Rc Reynolds number based on airfoil chord Tt tunnel stagnationtemperature, K x chordwise distance from leading edge of airfoil, cm y spanwise distance along model from centerlineof tunnel and model, cm z thicknessfrom chordlineof tunnel,cm a uncorrectedangle of attack, deg WINDTUNNEL Tests of the NACA651-213 airfoil were conducted in the Langley 20- by 60-cm two-dimensional test section insert of the O.3-m TCT. A photograph of the tunnel is shown in figure l(a) and a schematic drawing showing some physical characterictics is given in figure l(b). A photograph of the 20- by 60- cm two dimensional test section is shown in figure 2. Here the plenum cover and the test section ceiling have been removed to show model installation. The O.3-m TCT is a continuous flow, fan driven, transonic tunnel which uses nitrogen gas as the test medium. As detailed in reference 2, the tunnel with the two-dimensional test-section insert, is capable of operating at tempera- tures varying from about 78K to about 340K and stagnation pressures ranging from slightly greater than 1.0 atmosphere up to 6.0 atmospheres. Mach number can be varied from about 0.20 to 0.90. The ability to operate at cryogenic temperatures combined with the six-atmosphere pressure capability provides an extremely high Reynolds number capability at relatively low model loadings.

For this test, slotted walls were installed for the floor and ceiling to help reduce model blockage. More information on the O.3-m TCT's design and operational capabilities can be found in reference 7.

The two-dimensionaltest section contains computer driven angle-of-attack and momentum rake systems. The angle of attack system is capable of varying the angle of attack over a range of about 40°. The momentum rake, located just downstreamof the airfoil (see figure 2), provides up to five total pressure measurementsacross the span of the model and can traverse verticallyfrom about one chord above to about one-half chord below the model. Integrationof these pressuremeasurementsprovides the wake drag coefficient. The compa- rison of these five spanwise pressure measurementsprovides a mechanism for determiningthe extent of two dimensionalityin the flow. For this test, it was necessaryto specify the upper and lower boundariesof the airfoil wake, and the number of pressure readings to be recordedwithin the wake for each set of conditionstested.

MODEL The model tested was a two-dimensionalairfoilwith a NACA 651-213 profile and has a chord of 15.25 cm. Given in Table 1 are the design coordinatesof the airfoil section as well as the coordinatesmeasured along the model center- span. The design coordinateswere obtained using the equationsprogrammedfrom reference8. The coordinatesfor the NACA 651-213 were found by computing the coordinates for a 65-012, then scaling the thicknesscoordinatesby multi- plying by 13 / 12. To ensure the proper loading, the coordinateswere then shifted about the camber line computed for c_ = 0.2 and a = 0.5. A schematic drawing of the model is shown in figure 3. Figure 2 shows the model installed in the O.3-m TCT test section. The model has a total of 57 surface static-pressureorifices, each with a diameter of 0.025 cm. Table 2 provides a list of the spanwise and streamwisecoordinatesfor each orifice.

Model Fabrication The model was constructedfrom PH 13-8Mo stainlesssteel, heat treated to the conditionH1150M. It was designed and fabricatedin accordancewith the NASA . aerodynamicand structuralrequirementsspecifiedfor the ATAT program. As shown in figure 4, the leading edge and trailing edge sections of the airfoil were connectedby a tongue and groove joint. The joint was pinned together with a dowel, the surfacewas then machine finshed. After fabricationwas . completed,the model was cycled to cryogenictemperaturesand back to ambient temperaturesat a rate similar t O that it would experienceunder O.3'm TCT operating conditions. After the cryogenic cycling, a small discontinuity appeared at the joint line. The discontinuity was found to be less than a 0.0025-cm differencein height.

Model Accuracy The airfoilwas measured for final contour and orifice locationwith a Brown & Sharp Validator 200 probe. Blotted in figure 5 is the differencebetween the design and measured airfoil coordinates. Over much of the airfoil, the measured contour checked to within ±0.0025 cm (the design tolerance)of the design coordinates. At the leadingedge, where the steep slope of the airfoil's surfacemade it difficult to accuratelymeasure, the final contour appears to be more in error than in fact it most likely is. The errors at the trailing edge are most likely caused by the handworkingrequired to form a sharp trailing edge. The airfoil was again validatedat the completionof the test. The airfoil contour checked to be within 0.0025 cm of what it had read prior to the test. From the measurements,there appeared to have been a further increase in displacementat the joint during the test; however, the displacementwas still less than 0.0025 cm.

TEST INSTRUMENTATION A detailed discussionof the instrumentation and proceduresselected for the calibrationand control of the O.3-m TCT can be found in reference9.

However, since the airfoil data are derived from (1) the pressure distri- butions around the airfoil, (2) the definitionof the wake defect, and (3) the correspondingangle of attack, the details of relevant instrumentation are discussed herein.

Airfoil Pressures The O.3-m TCT is equipped to obtain up to 96 static-pressure measurementson the airfoil surface by the use of individualprecisioncapacitivepotentio- meter pressure transducers. The pressure transducersare located adjacent to the test section in order to reduce response time. For increasedaccuracy, the transducersare mounted on thermostatically controlledheater bases to • maintain a constant temperatureand on "shock"mounts to reduce possible vibrationeffects. The electricaloutputs from the transducersare recon- nected to individualsignal conditionerswith autorangingcapabilitythat are located in the tunnel control room. As a result of the autorangingcapa- bility, the analog_electrical output to the data acquisitionsystem is kept at a high level, even though the pressure transducermay be operatingat the low end of its range; however, the output is equally accurate on any of its ranges.

Wake Pressures A vertically traversing probe is located on the sidewall of the two- di l nensional test section downstream of the airfoil (see figure 2) and has a traversing range of 25.4 cm. For this test, the measurements were taken at a measurement plane which was about i.i chord lengths downstream of the airfoil trailing edge. The probe is driven by an electric stepper motor and is designed to operate at speeds from about 0.25 cm / sec to about 15 cm / sec.

There are five wake total pressure probes at different spanwise locations y / (b / 2). These locations are 0.125, 0.000, -0.125, -0.375, and -0.500.

Tunnel sidewall static pressure taps positioned in the plane of the probes are used to provide an average static pressure in the airfoil wake for use in calculation of wake drag coefficients. Individual transducers are used on each tube on the probe assembly and for each of the wall taps.

Angle of Attack The angle-of-attack mechanism has a traversing range of ±20° which can be offset from 0 ° in either direction at model installation. The mechanism is driven by an electr i c stepper motor which is connected through a yoke to the perimeter of both model mounting turntables. This arrangement drives both ends of the model through the angle-of-attack range to eliminate possible model twisting. The angular position of the turntable and, therefore, the angle of attack of the model are recorded using the output from a digital shaft encoder geared to the turntable.

TEST PROGRAM Figure 6 shows t i le test program (Rc versus M) used in the investigation. The selection of test conditions was chosen to coincide with data from tests conducted in other facilities, such as LTPT and LAC CFF. The extent of the effort to establish transition effects (fixed and free), Rc effects and M effects can be seen in this figure.

Transition The model was tested with both fixed and free transition. Reference 10 was used to determine the critical height needed for transition. Because of the range of Reynolds numbers over which the model was tested, two sizes of roughness particles were used. For Reynolds numbers from 3 x 106 to 9 x 106, glass spheres with an approximate diameter of 0.037 to 0.044 _ were used, and for Reynolds numbers from 12 x 106 to 20 x 106 glass microbeads were used which have an approximate diameter of 0.020 to 0.025 mm.

The thin transition strip (approximate 0.159 cm in width) was applied 0.660 cm aft of the leading edge on both the upper and lower surface.

DATA REDUCTION " In the data reduction process, the thermodynamic properties of the nitrogen gas are calculated using the Beattie-Bridgeman equation of state. This equation of state has been shown to give essentially the same thermodynamic propertiesand flow calculationresults as the more complicatedJacobsen equation of state in the operational temperatureand pressure regime of the O.3-m TCT, reference11. The test Mach number reflects the average of the longitudinalMach number distributions, which were measured as a function of Reynolds number in the calibrationof the '!empty" test section.

As previouslymentioned, the pressureson the surface of the airfoil were measured using individualpressure transducers. The rawdata were reduced according to a process described in an unpublishedin-house,data-reduction program. Normal force coefficientsand pitchingmoment coefficients were then calculatedfrom pressure integrationaround the airfoil.

The wake pressureswere measured by individualtransducersand were reduced according to the in-house program. The drag force was obtained as an integrationof total pressure decrementacross the airfoilwake correctedfor a "threshold"decrement,which accountedfor a nonzero pressure decrement outside the wake. This threshold decrement,in the form of incrementaldrag coefficient,was derived by looking at several runs early in the test. The compromisevalue for the entire test was 0.0008.

The results from the data reductionprocess are presented in Table 3.

Correctionof Results The aerodynamicresults presented in this paper are in an uncorrectedform so that any o_ several types of correctioncan easily be applied. The correc- tions to which the data are subject are: (1) an angle-of-attack correction due to lift interference,and (2) a Mach number correctiondue to solid blockage and Sidewall boundary-layer effects. Based on the works of Davis and Moore (reference12) and Barnwell (reference13), the correctionto angle of attack is about -1.72 cn. As indicatedin reference13, the slottedwall was designed for zero blockage and the effects of sidewall boundary layer on Mach numbers are discussedin reference14. Examples of the effects of these correctionson data from this facilityare presented in references14 and 15.

PRESENTATION OF RESULTS The forces and moments are presented in Table 3. A representative sample of the pressure data is provided in Table 4. Copies of the pressure data from any run are available on microfichefrom: Acquilla S. Hill Mail Stop 274 NASA Langley Research Center Hampton, Virginia 23665 804 / 865-3225 (Please refer to Test 148, NACA 651-213 Airfoil Study.)

An outline of the plotted data follows.

Effect of fixing transitionon aerodynamiccharacteristics of airfoil: Figure M = 0.22; Rc = 6 x 106 ................................

M = 0.22; Rc = 15 x 106 .............................. ii Effect of Mach number on aerodynamiccharacteristics of airfoilwith free transition: Effect of Mach number on aerodynamic characteristics of airfoil with fixed transition: el. leo i o.ooaool ooo,o..ooeo., i iooo....... • ,.

Rc = 6 x 106 .9.5 Effect of Reynolds number on aerodynamiccharacteristics of airfoil with free transition: Effect of Reynolds number on aerodynamiccharacteristicsof airfoil with fixed transition: M = 0 60 , ". 31 ? . • o e • •• •o • m • moo • oo m • •• omm mo • o• o momm •• • . . ••.oo m o ••m M 0 7 0 . ..o • o • ... o oo.• ••e o.•o•..•• e•••e o e .. o eo . .oo •. .' ' . _, ++ _ • o . • • Effect of angle of attack on pressure distributionof airfoil with - free transition: _. r ..... '' '' ' " _ - ..oe• . o . ..ooeoo _ o b •.

M _ . _ . . .••. .. coc o. ' " "' 0 60; Rc 3 x 106 .... _ ' 33 M = 0.60; RC = 6 x. _................................

106 " 35 • .ooeoo . ...o. . o••_.. oe u • f o• . e. o o mo. : M 0 60; BC _= 9 x " • _ - _ .. ..e eo •.o eoe . e eo.e oeo. ee a . •o.. . _ • -o e M 0 60; R c 15 x 106 / ' 36 • _ . eee e eee em eeeoeeeeee.eeeeeeee eeee | " M 0 60; Rc 40 x 106 - 3 7 e coNCLbDINGREMARKS ' • _. " ,_ The results presented in the report are fo_ the NACA . 651-213correlation airfoil• The.test temperaturesranged-from_ambient to about lOOK'at pressures ranging from about 1.2 to 6.0 atm. Mach number was'varied from D .22 t o 0.80. These variablesy_elded Reynolds numbers (based on airfoi_"chord)from about 3 x 106 to 40 x 10°. This test was primarilydesigned to testa NACA 651-213 airfoil over a_widerange of.Rey 6 oldsnumbe_s and comparethe data to thatobtained on the. sam, profile in other facilities.

All the objectivesof the test were met. Data are includedwhich demonstrate the effects . of:fixe d transition,Mach number, and Reynolds number on the aerodynamiccharacteristicsof the airfoil. A sample of data showing the effects of angle of attack on the pressure distributionis also provided.

REFERENCES 1. Lads,n, Charles L. and Ray, Edward J.: Status of Advanced Airfoil Tests in the Langley O.3-MeterTransonic CryogenicTunnel, ACEE Project Oral Status Review• Advanced Aerodynamics- Selected NASA Research,NASA CP-2208, December 1981.

" 2. Ray, Edward J.: A Review of Reynolds Number Studies Conducted in the Langley O.3-m Transonic CryogenicTunnel. AIAA-82-0941,June 7-11, 1982.

• 3. Johnson, Wil]iam G., Jr.; Hill,Acquilla S.; Ray, Edward J.; Rozendaal,Roger A . ;.andButler, Thomas W . . : _"HighReynold s Number Tests of a Boeing BAC1 Airfoil inthe LangleyO.3-Meter _ransoni € Crylpgenic Tunnel• NASA TM-81922,April 1982.

4. Dress, David A.; Johnson, Charles B.; McGuire, Peggy D.; Stanewsky,Egon; and Ray, Edward J.: High Reynolds Number Tests of the CAST IO-2 / DOA 2 Airfoil in the Langley O.3-MeterTransonicCryogenicTunnel - Phase I.

NASA TM-84620,May 1983.

5. Abbott, Ira H.; and von Doenhoff,Albert E.: Theory of Wing Sections.

Dover Publications,lnc., New York, pp. 111-123,1959.

6, Harris, Charles D.; McGhee, Robert J.; and Al l ison, Dennis 0.: Low-SpeedAerodynamicCharacteristics o f a 14-PercentThick NASA Phase 2 Supercritic_ 1 Airfoil Designed for a Lift Coefficientof 0.7.

NASA TM-81912_Deces n ber 1980.

7, Ray, Edward J.; Ladson, Charles L,; Adcock, Jerry B.; Lawing, Pierce L.; Hall, Robert ,_ I .:Revi_ of Design and OperationalCharacteristicsof the O.3-MeterTranson i c Cryogeni c Tunnel. NASA TM-80123,September 19 7 9.

8. Ladson, Charles L.; and Brooks, Cuyler W. Jr,: Developmentof a Computer Program to Obtain Ord in atesfor NACA 6- and 6A- Series Airfoil. NASA TM X-3069, 19 7 4, 9, La d son, Charle s L,; and Kilgore, Robert A.: Instrumentation for Ca li bration and Control.of a Continuous-Flow CryogenicTunnel. HASA TM-8_825, 1980.

I0, Braslow, Albert L,; and Knox, Eugene C. SimplifiedMethod for Determinationof Cr i tical He i ght of DistributedRoughnessParticles for Boundary-Layer Transitionat Mach Numbers from 0 to 5. NASA TN 4363, 1958.

11. Hall, Robert 14.;and Adcock,Jerry B.: Simulationof Ideal-GasFlow by Nitrogen and Other Selected Gases at CryogenicTemperatures. NASA TP-1901, September 7981.

12. Davis, Don D., Jr.; and Moore, Dewey; AnalyticalStudy of Blockage- and Lift-lnterference Correctionsfor Slotted Tunnels Obtained by the Substitutionof an EquivalentHomogeneousBoundary for the Discrete Slots. NACA RM L53EO7b, June 29, 1953.

13. Barnwell, Richard W.: Design and PerformanceEvaluationof Slotted Walls for Two-Dimensional14ind Tunnels. NASA TM 78648, February 1978.

14. Kemp, W. B., Jr.; and Adcock, J. B,: Combined Four-Wall Interference Assess_nent in Two_DimensionalAirfoil Tests. AIAA-82-0586,I_arch 21- 24, 1982.

15. Murthy, A. V.; Johnson, C. B.; Ray, E. J.; Lawing, P. L.; and Thibo_leaux, J.J.: Investigationof the Effect of Upstream Sidewall Boundary-LayerR_moval on a Supercr J ticalAirfoil. AIAA-83-0386, January IQ-14, 198 3 .

,, Table 1 : Coordinatesof NACA 651-213Airfoil Section - a. Upper Surface - x l c z l c ....

Design L Measured 0.000000 0.000000 _.' 0.0000 0.001678 0.007443 _., -_ 0.0071.

0.003410 0.009994 ._ 0.0098 _ - 0.005030 0.011758 0.01-1'7 0.006700 0.013252i_ 0.0133 ' , ' 0.008386 0.014567, . 0.0146 ' , , 0.011059 0.016381 0.0165 0.033239 0.027097 0.0273 . _,, .

0.043164 0.030862. 0.0310 , ' 0.050622 0.033447 ,, 0.0336 " 0.060583 0.036629 • 0.0367 0.073052 0.040277 0 .0403 _ , , 0.083039 0.042983 0.0430 0.095534 0.046 1 35 ' _ "_ _ 0.0461 ,: -, ..'

0.108041 0.049058,_ _., 0.0491 " "- 0. 1 38096 0.055279 0.0553 0.168190 0.060579_ 0.0606 0.248574 0.071175 0.0713 0.329093 0.077504 ' 0.0777 .... _ 0.409721 0.079916, ' 0.0802 , 0.510809 0.076324 0.0764 0.591318 0.067696, 0.0677 0.671361 0.055594 0.0555 0.751123 0.041353 0.0412 " , 0.790936 0.033806 0.0336 0.840669 0.024292 0.0240 0.880450 0.016869 0.0165 0.920247 0.009910 0.0097 0.960084 0.003893 0.0038 0.970053 0.002644 0.0026 0.980028 0.001537 0.0016 0.990010 0.000619 0.0008 1.000000 0.000000 0.0005 - , 11 b. Lower Surface

x / c z / c

T • Design Measured 0.000000 0.000000 0.0000 0.001838 -0.004839 -0.0041 0.003322 -0.006681 -0.0061 0,0050_ -0.008288 -0.0077 " 0.00677 -0.009546 -0.0090 0,00825 7 -0.010597 -0.0102 0.011630 -0,_12409 I i -0.0121 0,016498 -0,014435 iI _0.0141 0.026656 -Q.017 7 05 I -0.0174 0.034238 -0,019_49 Ii -0.0194 Q,041802 -0,021987 -0.0213 0.051865 _0.023792 -0.0235 0,061909 -0.025764 -0.0255 0,071938 -0,027560 -0.0273 0,084459 -0,029618 -0.0294 0.096966 -0.031501 -0.0313 0.111959 -0,033560 -0.0333 0, 1 41904 _0.037127 -0.0369 0.1 7 1810 -0.040115 -0.0399 0.251426 -Q.045921 -0.0457 0.330907 -0.049166 -0.0490 0.390446 -0.050093 -0.0500 0.489491 _0.048105 -0.0480 0,588682 -0.041596 -0.0414 0.668639 -0.033900 -0.0337 0.748877 -0.024841 -0.0246 0.789064 -0.020046 -0.0198 0.839331 -0.014024 -0.0138 0.879550 -0.009375 -0.0091 0.919753 -0.005108 -0.0048 0.959916 -0.001631 -0.0013 0.969947 -0.000_80 -0.0007 t 0.979972 -0.000453 -0.0002 0.989990 -0.000091 +0.0002 I 1.000000 0.000000 -0.0014

k

Table 2 : Pressure Orifice Coordinates a. Upper Surface Orifice x / c y / (b / 2) 1 0.0000 0.0120 2 0.0244 _ 0.3892 3 0.0513 -0.0203 4 , 0.0765 -0.0203 5 0.1005, -0.0203 '6 ' 0.1508 _ -0.7429 7 _ 0.,1508,!:_ -0.2394 8 0.I506 ' -0.0203 9 0._507 _ 0.2628_ 10 0.1507 0.5112 11 0.1508 ' 0.7620 12 0.200¢ -0.02D3 13 0.2500 -0.0240 ' :14 ! 0.2988 -0.0235 15 0.3492, : -0.0_35_: 16 0.398 6 _ -0.0228, 17 0.447 9 _ ' -0.0235, 18 0.4984. _ -0.741B _ 19 ! 0.4984 -0.4910 20 _ 0.4984 -0.2401 21 "" _ ....... 0.4983 ............... i0.0235 ................

22 0.4983 0.5122 23 0.4984 0.7630 24 0.5466 -0.0210 25 0.5962 -0.0208 26 0.6457 -0.0208 27 0.6957 -0.0213 28 0.7461 -0.0215 29 0.7950 -0.7423 30 0.7950 -0.4900 31 0.7952 -0.2404 32 0.7952 -0.0215 33 0.7952 0.2613 34 0.7952 0.5124 35 0.7952 0.7630 36 0.8457 -0.0213 37 0.0906 0.3892 b. Lower Surface Orifice x / c y / (b / 2) _ _ L 38 O.0129 O.3782 o 39 0.0257 0.0319 40 0,0607 0.0319 41 I 0.0749 0.0319 42 O, i000 0.0319 43 O.15QI 0.0319 44 0.1996 0.0319 45 0.2494 0.0319 46 O.2998 0.0319 47 0,3487 ! 0.0319 i 48 O.3892 i 0.0319 49 0.4470 _i 0.0319 50 0, 4 977 ! 0.0319 51 0.5459 ! 0.0319 I 52 0.5958 i 0.0319 53 0.645_ 0.0319 i 54 0,6950 0.0319 55 O.7449 O.0319 56 O. 7955 0.0319 57 0.8453 0.0319 T A B LE3 . - NACA 6 5 1 - 2 13 T EST RESULTS [ The f ollow i n g r es u lts wi ll be l is t e d b y a scen d i ng Mo ch nu mb er ] (o) Fi xed tr o ns it ion Point H R x 10 "s c o c n c m c d RU N 60 2 ,2 2 3 2 °4 9 8 - 3, 0 1! -. 15 7 r . O 15 . 00 9 0 9 3 .22 5 3.021 _ 1 .9 7 -. 0 60 " _ 01 8 . 00 881 : • 0 20 ,00855 4 _ .225 3. 0 42 ' - . q 6 . 0 26 i 5 .22 k 3 . 03 1 1.04 .2 0 0 . -.024 .0081 9 • 6 .222 3 .02 8 12.0 4 .2 9 4' -. 027 ,007 5 7 _ 7 ,22 1 3 , 00 8 3,03 _ 38 4 _. 029 , 00787 _ 8 ,22Z 3 . 010 4 , 0 2 ,4 7 4 - ,0 3 1 . 007 8 9 9 .221 3 .01 , 0 5. 0 Z _ ,568 - . 033 . 008 42 I0 , 221 3 ,0 0 4 6,0 3 ,65 8 _ - . ' 035 , 0 p89 5 1 1 .2 2 1 3 . 0 t 9 7.04 ': . 7 4 7 - ,03 5 . O p q bp 12 .221 3.025 8.02 .834 -_.038 .010 2 7 1 3 1,222 3 . 013 q,O2 _ .916 -*03 7 . 0 11 30 14 ,222 3 , 015 10 . 0 21 ' ' 1"9 9 7 -. 03 q . 0 1220 15 .222 3 . 0 1 0 1 1. 0 41 1 .0 7 4 , .b_ 8 . 0 1 363 1 6 .221 3 . 0 06 12.031 i.i_ 7 : ".. ' -- ' .0139 . 0 14 9 2 1 7 .22 3 3 . 03 2 . 13 .02 1 .201 l = . 03 9 .01606 ' 1 8 .22 2 3. 01 6 14, 03 I_235 - . 045 . 0 1 7 87 l 20 .22 3 3 .0 3i_ 1 5.04 1 ,23 9 _ 1 -- _ 0 72 . 0 4 51 4 21 .22 3 3, 073 : ,0 1 .1_5 -, 0 25 .0082 8 !

R U N 59 13 .224 6.051 - . 0 1 .122 - .025 ,00776 14 . 225 6.078 : -3 . 0 1_ - .15 3 - . 01 7 . 00830 1 5 .224 6,116 - 1.97 1. 0 65 l - . 0 1 7 . 00 792 17 .224 6, 0 7 3 - , 9 9 . 02 3 - . 0 2 0 , 00 7 8 6 18 .224 6.07 3 1,0 3 .2 17 - . 0 26 . 00 76 8 1 9 .225 6. 0 8 3 2.02 . 30g - . 0 29 . 00 776 2 0 .226 6. i 06 3 .01 .6 0 3 - .0 31 . 007 97 2 1 .224 6.08 0 14. 0 1 .4 9 7 - .0 33 . 0 08 3 4 26 .225 6. 0 9 0 5. 0 1 ,590 - .0 3 6 . 0 0 8 6 q 27 .224 6.053 6. 0 1 .67 9 -. 03 7 . 00 907 33 ,226 6 , 0 7 0 6,99 ,772 - , 0 4 0 , 00 979 3 4 .225 6. 0 72 8, 0 2 .86 7 - . 0 4 1 . 0 1060 35 .223 6. 0 46 9.02 . q 5 9 - .062 . 0 1 115 36 .223 6.050 10.01 1.0 3 8 -.042 .01225 3 7 ,224 6, 0 69 II .0 3 1.127 -. 0 62 . 0 1 3 2 3 3 8 .22 3 6. 058 12. 03 1 .207 -.0 4 3 . 01 6 63 39 .223 6.066 13 .02 1 .27 5 -. 0 62 . 0 1650 42 ,224 6. 0 8 6 1 4,0 3 1, 3 40 - .042 , 01 841 44 .22 3 6.065 15.0 3 1. 3 84 -.041 .01945 6 5 ,226 6 . 0 8 3 16. 03 1. 377 - . 0 55 .02776 46 .22 3 6. 0 40 1 7o 0 5 1 .2 77 - . 0 86 .1 1 252 TABLE 3. - Continued.

(a) Continued.

Potnt I"1 R x 10 -G c a c n c m c d - RUN 61 2 3 .22D 9.136 - 3 .00 -.1 5 2 -.0 1 9 .0 0 7 50 2& ,224 9,110 -2.00 -.0 57 - .OZl .00 7 48 29 .224 9.117 -.g8 .03 % -. 0 _4 .3073g 20 .224 9,128 1.01 . 22 2 -.028 .00754 27 .224 9. 13 3 2.0 1 ,3 17 -.0 3 _ .00799 28 .224 g.log 3,02 .412 -.034 . 007 7 7 29 .226 9.161 4.0_ .506 -,036 .00835 30 , 22 9 g,l]2 _.O3 ,59g -.03_ .00837 ]I .2_5 g.156 6.62 .691 -.040 .0087g 3 2 .22 3 go127 7 .02 . 7 £0 -.O4O .00g£6 3 3 ,22 3 g_ l O_ 8,03 .BBO -. 0 66 . 0 0 9 76 34 ,224 9.142 9.0 3 .9(_ -.045 .OlO k 7 3 5 ,224 9. 1 50 13. 0 2 1. 0 63 _.066 .01144 3 6 .22 3 9. 0 9 5 11, 03 1.1 3 5 -.06 5 .01223 37 , 2 _2 q.Ob? 12.0 3 1. 2 0 6 -. 0 47 .01364 3 8 .22) 9, 0 81 1 3 .01 1.266 -.050 .91467 3 9 .2 2 5 9.1 6 8 16.0 2 1, 3 22 - .056 .01562 40 .227 9.262 1 5 .0 3 1. 35 0 -.050 .0166& 4 1 .226 _134 16 .03 1 . 3 70 -.068 .0277 3 4 2 . 229 g,171 17.03 1 . 2 98 -. O R7 .1 3 62 3 4 3 . 7 24 9,1 5 4 .00 ,126 -.0_6 . 0 0723 RUN 64 12 .225 12.298 .01 .125 - .027 . 0 9776 13 .22D 12.210 - 2.99 -.1 5 8 - .021 . 0 0739 i_ ,226 1 2.22 3 -2.O 0 -.O66 - .023 .00727 15 ,226 I?,252 -.99 .030 -.025 ,00745 I t .220 12.292 1.01 .22R - .032 . 0 08 0 8 17 ._25 12.232 3,02 ,421 -,037 .0S_82 II_ .225 12._38 5.02 .b 1 4 -.06 2 .00990 I< ; .225 12.211 7.04 ._04 -.046 .01016 20 ,225 12.262 _.0 3 .0 o 7 -.050 .01212 21 .224 12,1 5 _ 11.0 3 [. 1 63 -,06g .C1511 22 .227 12.276 12.06 1,2 3 8 -,047 .01696 23 .227 12.2 6 0 13._3 1.292 -.047 .01788 26 .Z26 12.207 14,02 1,3 3 7 -.068 .01905

l -

RUN 6 6 _ 8 .227 12.2 3 5 16.03 1,421 - .051 .02250 ig .227 12.240 17, 03 1.355 -,098 .12931 TABLE3. - C on tinue d .

( a ) Continued .

P o int 14 R x 1g -s c o c n c m c d R UN 6 7 2 0 .225 15.282 . 0 1 . 1 38 - . 0 28 . 00 661 21 .226 15. 3 03 - 2.99 - .150 - .021 .007 00 22 .226 15, 3 47 - 2.00 -.055 -.024 .00675 23 .227 1 5 . 3 91 -,q q .04 8 -.028 .00663 24 .22 7 15. 37 5 1.01 .241 - .0 33 .0 0 6 5 7 25 ,2 27 15,3 6 3 2 ,0 1 , 339 -.036 ° 0 0 6 39 26 , 227 15,3 61 3 .0 1 ,k 3 0 - . 03 6 . 0 0679 27 .22 7 15 . 377 4, 01 . 537 -oO k 2 . 00 685 28 .226 1 5. 30 2 5.00 ,625 1 . 0 42 . 0 0 7 14 29 . 2 28 15.4 5 8 6. 0 2 . 7 26 - .045 . 007 5 7 31 ,226 15. 3 11 7 . 0 1 .819 -. 0 46 . 0 0808 3 2 .228 15.445 8 .02 .910 - .047 . 00883 RUN 62 44 .6 00 2.995 - . 0 5 .1 3 4 -. 0 29 . 0 0 7 46 45 .6 0 1 2. 9 90 -1. 0 1 . 0 24 -. 0 26 . 0 0781 46 .6 00 2.998 1. 0 2 .251 -. 03 2 . 00 766 4 7 .60 0 2.994 2.0 0 . 3 62 -. 03 4 ,0 08 14 4 8 .6 01 2,998 3 , 01 .477 -.0 37 . 0 0 858 % 9 . 599 2.99 1 4, 0 1 ,58 g -, 03 9 . 00 9 3 2 5 0 ° 6 0 0 2,99 % 5.01 .7 0 1 - . 0 40 , 0 102 8 51 , 5 9 7 2,98 5 6,02 °794 -,0 3 9 °0 11 83 5 2 , 5 9 8 2,9 8 8 7 . 0 2 . 8 77 -.0 3 5 . 01371 53 , 6 01 2. 9 9 8 8 . 0 1 ,9 8 7 1. 030 . 0 1 5 7q

I

R UN 58 3 .6 0 4 6. 0 2 3 - 1 .0 3 .014 - . 0 25 . 0081 0 4 .6 0 2 6.017 1. 03 .23 3 -.0 3 0 . 008 1 0 5 .60 3 6. 0 18 2. 03 . 3 43 -.0 33 . 0083 1 6 . 6 0 4 6.028 3 . 0 4 . 4 47 1. 03 5 . 00 8 5 2 7 .6 0 2 6.016 4. 0 4 .556 -. 03 7 o OO q O q 8 .60 1 6.005 5. 0 5 .667 -, 038 . 0 10 0 8 9 ,60 0 5 , q 9 8 6, 0 6 .779 - . 03 8 . 0 1 1 15 10 ,6 00 6. 003 7 . 05 .8 7 4 -,0 3 5 . 01 26 8 II .601 6. 013 8. 0 4 .979 -, 0 29 .0 1 584 1 2 , 601 6. 00 8 - . 01 . 1 29 -,028 , 008%1

1 7

TABLE ,3. - Continued .

(a) Continued.

Point H R x 18 -s c a c n c m c d RUN 57 45 .503 9.032 - i,00 .028 - °025 .00782 46 ,50 0 9.0 0 0 1,0 1 , 254 -. 03 2 .00791 47 .601 9.009 2.02 .363 -.035 .008II 48 .601 9.0II 3.02 ,473 -°037 ,0084i 49 .601 9.003 4.03 .575 -.038 . 00894 50 .604 9.044 5.02 .688 -.039 .00955 51 .598 8.980 5.03 .799 -.038 .01061 52 ,603 9.032 7.04 .912 -.035 .01264 5 & .603 9. 033 8. 01 .998 - .029 .01602 55 .601 9.014 .00 .140 -.029 .00788 I RUN 65 m i .602 12.016 .00 ,138 -.029 .00732 2 .604 12.029 -3.00 -.186 -.022 .00752 3 .601 12,010 -,97 ,031 -,026 .00736 4 .502 12 . 0 3 0 1.0 3 ,255 - .032 .00719 5 .602 12.025 2.03 .362 -.034 .00735 7 . 603 12.030 3.01 .469 -.037 .00754 8 . 6 04 12.031 4.05 .582 - . 039 °0 0 792 12 . b 04 12.024 5.01 .693 -.043 .00851 13 .b03 12.001 6.03 .825 -.042 .00916 14 .602 11.974 7.05 .924 -.037 .01097 1 5 . 605 12.025 8. 0 5 .991 -.0 31 . 01 3 7 3 RUN 52 I .703 3.005 .OI .I3I -.032 .0099I 3 .703 3.005 -I.00 .01g -.030 .00957 4 ,700 2.997 1.01 .243 -.034 .01019 5 .700 2.997 2.01 .34g -.036 .01058 6 .700 2.994 3.03 .458 -.037 .01133 7 .700 2.995 4.03 . 565 -.038 .01215 8 .701 3.015 5.03 .680 -.040 .01430 9 .701 3.008 5.03 .778 -.040 .01682 TAB L E3 . - C ont inued .

(o) Continued.

Point H R c x 1B - e e c n c m c d RUN 5 3 11 , 7 0 1 6 , 015 .02 ; 146 - , 0 34 .008 8 7 1 2 ,702 6 , 0 05 -1.01 , 0 22 - ,0 31 .00 8 7 41 1 3 , 7 0 1 6,002 1,02 ,265 , - ,036 ,0092 0 1 6 ,699 5 °999 2,02 l , 3 82 - , 03 9 . 00 9 6 7 15 ,70 4 6, 0 16 3 , 02: , 491 - ,042 , 01044 1 6 . 70 4 6. 0 1 7 4. 0 2 .604 -.044 . 011 29 17 . 70 0 5 . 9 95 5 . 03 , 7 2 0 - . 0 46 , 013 7g: 1 8 ,7 0 4 6 . 00 5 6, 03; , 80 6 - . 0 44 , 02 14 0 _ R U N 5 5 2 7 , 70 2 8,99 7 -1 , 00 . 0 23 - , 0 31 , 0 0 8 27 : 2 8 , 700 9 , 00 9 1 , 0 2 , 25 9 - , 0 3 5 , 008 4 0 30 ,6 9 9 9 , 00 1 2,0 3 , 3 7 2 - , 037 . 0 0 88 0 3 1 .700 9 , 0 00 3 . 0 3 . 475 -,03 9 . 0 09 2 7 3 2 , 7 01 9 . 016 4 . 0 3 . 5 8 2 -,03 q .00 9 9 8 33 . 70 5 9. 0 2 0 5. 03 , 683 - . 0 4 0 . 01215 3 4 , 70 3 9 . 004 6.0 3 . 7 80 -°0 3 8 .01571 35 , 7 01 9, 0 1 7 ,0 1 , 1 40 - , 0 32 ,0 0824 RUN 6 3 4 ,7 01 12 . 016 - 1 ,00 , 01 8 - ,03 0 °0084 1 5 ° 70 2 12, 0 29 1 ,0 4 . 26 8 - . 0 3 7 , 0088 7 6 ,70 0 12, 00 9 2, 0 4 , 3 9 3 - . 0 61 ,00 927 7 ,7 03 12,0 2 6 3, 07 ,520 1 , 0 65 , 0 1028 8 .7 0 5 12 , 048 4,06 , 624 -,04 5 °01182 9 .705 12 . 0 36 5.05 . 7 14 -,045 , 0 144 k I0 ,7 0 2 12 . 0 0 3 6.0 7 .8 1 1 - ,04 5 , 0 1 8 62 1 1 ,702 12,0 3 5 ,00 ,14 7 - . 03 5 ,0 07 89 TABLE 3. - Continued.

(a) Concluded.

Point M R x 10 -s cI c n o m o d c RUN 5 4 2 0 .758 6.008 .04 .135 - .042 . 0 12 9 4 21 .762 6.0 3 .1 - I.0 2 .010 - , 0 36 .011 3 0 22 ,762 6.0 0 6 1. 03 ,2 3 6 - , 0 4 3 , 0 17 3 5 23 . 7 64 6.008 2.03 , 3 22 -,046 ,02 6 92 24 . 7 6 1 6.019 3 .0 3 .410 - . 0 49 .0 3707 RUN 56 36 .762 9.002 .0 1 .127 -.040 .0129g 38 .764 9.022 - i .00 .014 -.038 .0112 3 39 , 7 64 9.021 1.03 .2 3 9 - ,044 .01 7 0 3 41 . 7 64 9,018 2,03 , 332 -,048 ,0248 9 4 2 , 7 62 9. 00 6 3,0 1 ,41 3 -, 0 4 9 , 03 48 3 TABLE 5. - Cont i nu e d.

(b) Free t ran s i t ion Point M Rcx 10-s u Cn Cm ,Cd , ; ,,, _ U N 41 3 .228 2 . 7 g0 - . 01 .1 1 8 - . '023 . 0 0758 5 . 223 2.7 64 -3. _0 - . 1 39 - 4 0 15 .00 711 6 .223 r21772 -- 1 .e gg -. 056 - ,0 17 .00 7 6Q 7 ,2 23 2.767 -& 9 8 ,031 -, 02 0 , 0 075 5 8 .2 23 2 . 7 69 1,07 .20 k _ -. OZ k . 00732 : q , 22 3 2.770 2 40 1 .29 Z - ,0 2 6 . 00645 I0 . 222 2.753 3 . 0 2 .3 n7 -,_ 30 . 007 3 5 11 , 22 _ 2 , 757 6.0 F .4 . 7 0 - , 029 , 00823 1 2 .271 2,7 46 5 ,0 2 , 5 6 5 - , 0 3 3 _. 008 8 2 13 .22 3 : 2 . 773 6 _ 0 3 .557 -, 03 _ . 00 9 3 5 : 14 . 22Z 2.75 8 7. 0 4 .74 _ - , 03 7 ! ,ooq q s _ 15 . 2 27 2 ,7 5 2 A, O3 ,8_ 7 - . 037 :, 010 73 ..

l b . 222 _ : 2 .761 0 . 0 3 .q 24 - , 0 4 0 _. 0 1 152 : 17 . 222 ? . 7 _6 1 0 ,02 , qq 3 -,0 3 9 ,01250 1 8 , 2 22 2 ,7 56 11 ,0 4 1.0 8 5 -,0 4Z .0 13 6 7 l q , 22 6 2 ,7 8 5 l ? ,03 " 1 ,1 3 8 - , 0 3g " " ., 01508 .

20 . 2 ? & 2 .745 1 3 .0 1 1 . 1 q 8 : - , 03 q , 0160o 21 .224 2, 7 6 2 1 4 ,01 1 , 2 6 7 -, G4 8 _ ,01 7 37 2 4 . 224 2 ;7 66 1 5 .0 2 1, 206 - , 0 84 . 040 6 4 : • _ l • R U N & q 1 . 2 24 6. 0 94 . 0 1 .120 -. 023 .0077 1 2 .222 _ 5.04 1 -2 . q q - .1 4 7 -,01 6 , 00807 3 . 7 22 6 ,052 - ? , 00 -. 05 b - , Ol q . 007 8 8 4 , 22 3 5 , 05 8 -.q q , 0 3 2. -,021 . . 00787 5 .22 3 6 . 06 4 I .QI , 2 1g -, 0 27 . 00773 6 ,_ 2 3 6 , 0 5 4 2,0 1 , 312 - , 029 . 0077 q 7 , 22 _ _ ,0 3g 3.0 1 . 40 6 - , 0 3 1 , 00 78 5 8 ,223 5. 058 4.01 .4 qq - . 034 . 0077 6 q , 22 _ 6,04_ 5 . 0 3 , 5 o0 - , C35 ,0 0e 1 7 1 0 , 223 6. 0 8 2 7 . 0 9 ;777 -, 0 4 0 , O O q l O I I . 224 6. Oq a 6 . 02 . _81 -,0 38 .008 65 12 ,2 2 2 6 , 0 6 2 q. 0 3 .8 54 - . 041 , 00 g 77 13 , 22 1 6 ,05 4 9, 02 .g 6 _ - , 0 4 4 , 01 043 14 .2 7 7 6 , 0 77 1 0. 02 1.04 1 : -.043 .0 1 133 15 .223 6 .0 8 3 1 1 .03 l , i Z 6 - , 0 4_ . 0 1 2 34 1 5 . 22 1 6.03 5 1 2 .03 l . l q l - . . 0 4 6 . 01 338 17 , 22 _ 6 .1 1q 1 3 .02 1,268 -. 05 1 , 01417 1 8 .2 _ 4 6 .11 0 1 _ .0 _ 1.321 -.053 . 015 31 lq , 22 3 : 6, 0 q? 1 _ .03 1 ,3 65 -. 055 • ,01 6 q 6 2 1 , 2 2 3 6,I 0 _ 16, 0 3 1 , 3 86 -.G6 Z . 023 q 7 22 .221 6, 0 &5 ]? . 02 1 , 3 6B - , 0 82 , 0 5 3 61 TABLE 3. - Continued.

(b) Continued.

Point M R x 10 -G c a c n c m c d 2R ,22_ _,2 3 o - 2,0 0 - ,14 7 - , 0 20 = 007 54 _ 0 ,224 0 , 1 1 = - _,00 -, 0 56 - ,022 . 007 31 _1 .22_ Q,145 - . Q8 .041 -.025 .007 3 1 92 .22_ e.ln$ 1,01 ,2Z q -,G30 . 0 0 7 2q _ 3 ,224 q , Oq q _._ ] , 3 _4 - . 0 3 3 .0 07 4 3 341 0 2_ 4 _ ' I_ _ _'01 "41 7 I'03 5 '0 0 7 57 3 5 ,226 Qol q ] 4o01 , 5 1 0 - ,0_7 , 0 0 7 72 _6 ,22_ q olT? 5,01 ,605 -,040 . C 0800 3 7 ,2 2 5 a,1 7 4 5,_ , 7 01 -,042 ,00865 3 8 ,226 9 , 1 2_ 7 ,_2 ,T q q. --1_46 ,008 83 _0 , 2 _& 0.]6_ 9 .0] ,6q7 --,066 ,00061 60 , 2 7 6 9 ,1 3 6 0,0] ,qSO - , C6 6 , 0 1 01 _ 4 ? ,_ q,l_l If ,O? 1,157 -, 0 68 ,01205 A3 ,225 q,155 I _, 0 6 1, 2 18 - ,OS l ,01 3 0 7 64 ,2 2 4 0,137 ]_,01 lo?Q_ - , 055 ,01 3 98 45 .224 901 3 1 14,0 1 1,3_2 - .058 ,O14gO 44 o22_ _,I0_ I_,02 1,3_7 -oO60 00 1 684 6 7 ,225 q , l _? 16,02 1 , 3 o 7 -, 0 7 4 , 0 2068 4 q . 2 _ q ._ o o , 0 0 ,12 q - .02 7 , 0 0 7 _ 7 oUN _0 2 5 . ? P% 12.207 .0 0 ,I_I - 0_28 ,0 0 6 0 2 _6 , 2 25 12 . 275 - _,O 0 - ,155 - ,OIQ ,0 0 7_7 7 7 , _ ? A 12 .31 _ - _,00 - ,05 5 -,_ ZZ ,0 0 71_ ?_ ,_7 5 12 . 2 8_ - .o q .0_ 7 - , 0 2 5 ,60 7 02 2 q ,2 2 6 12.2Ol l,O! .22 q - ,¢ 30 .00 7 0o 30 .225 12.25_ ?,O f , 3 2 3 -,033 .00720 _I ,_2_ I ? ,202 _,_ ? ,41 Q - ,036 .00727 3 2 . 2 26 12 . 2 5 1 4, A 2 o_1 7 --,0 3 _ ,00757 3 3 . 2 26 1 2 o 2 _4 _ , 0 2 , A I7 - ,O4 i ,60 28 0 94 0 2 2 _ [2o _61 6,8_ ,70 0 1,043 ,OO P 30 ? 5 ._ 2 6 I?,301 7,0_ o80 3 -,Cl4_ o 0 0 8 6 2 36 ' ,225 1 2 .2 3 _ 8.02 ,S q 4 - , 04_ ,oo q 2 _ 37 ,_ ? _ 12,23£ q ,02 00 0 3 - ,047 , 0 0 q 88 38 .22_ 1 2 ,i0o ] 3,_I 1,07_ -,04@ ,0]0@ I 3 9 ,2 2 & 12,1_% I I, 03 1 , 155 -,049 00_166 40 ,2 2 7 12, 3 27 I_,0_ 1, 2 3 0 - ,069 ,_I_66 4 1 02 2 5 12,2 2 0 I_,02 1,2 q 2 - ,0 5 _ , 0 1 3 72 4 Z .2 2 6 1_,_5 2 _4,0] 1, 3 4 5 -.062 ,01467 43 . 226 12 . 303 1 5 ,03 1 ,378 -, 0 64 ,0 1 746 6& , 2?= 12,_37 16,[ 3 1,411 -,0_8 ,09674 4_ . Z ? _ 1 2 .SRR _Vo C 4 Io2R2 -,C05 ,15650 TABLE 5. - Continued.

(b) Continued .

Point H R c x 10 -s u c n c m c d O UN 46 ; 7 ,227 15. 3 4 1 - 2.go - ,14g - . 0 21 ,00 7 32 : 8 .227 1 5 . 335 - 1.og -.06 0 - .022 .00 7 05 Q ,2 2 7 1 5, 3 6 3 - ,oq ,03 6 - , 02 6 _ , 00707 lO , _2 7 15 ,34 4 1,0 1 . 2 28 - , 03 1 ,00 701 11 , 227 15 . 3 58 2 ,0 2 . _2 5 - , 03 4 ,00 6 9 6 12 , 22 7 15 ,4 0 2 3 . _ i , k 2 3 -,0 37 , 00 7 30 13 ,2_6 15.318 4.01 . 5 21 - ,0 4 0 ,00 747 1 4 ° 2 2 7 1 5 , 3 81 5, 0 2 , 62 0 - , 0 42 , 00 77 0 15 ,22 7 15 , 377 6,0 2 , 711 - ,0 4 4 , 0 08 14 16 ,2_6 15 , 3 _g 7 . 0 2 ,B 1 1 - , 0 4 6 , 0 08 55 1 7 , 227 1 5 ,414 _, 0 3 ,g OB -,0 47 , O Oq05 1 8 , 22 7 15 , 30 6 q , Ol 1 , 0 0 2 - , 04 9 ,0 0 q 8 1 l q , 225 15 , 31 6 ' I 0.0 2 1.0 _8 - , 0 4 0 , 01078 2 0 ,226 15 , 3 6 3 1' 1 , 0 2 1.167 - , 050 . 01 1 4 5 2 1 ,226 1 '5,400 12,03 1,241 - , 05 3 ,0 1 269 22 ,228 15 ,479 13. 02 1 ,2 8 7 -,0 58 ,0 13 9 5 23 ,22 8 1 5 ,5 17 14,0 3 1,3 5 R - ,06 1 , 01 4q 8 2 4 ,228 15,474 15 ,0 4 1, 3 gq - ,068 , 0 1 8 71 _5 ,2 2 6 1 5 , 3 84 1 5 , 03 1 , 3 86 - , 0 7 5 , 0 4986 26 ,227 1 5, 2 6 0 : ,0 1 , 1 34 -, 029 ,0 0 6 q_ : P UN 51 4 7 ,2 2 7 2 0 ,583 -. 0 1 , 1 34 - , 0 2 9 , 006 5 6 48 , 2 3 0 2 0 , 75 8 - ?, 00 - ,1 5 6 - ,021 ,0 06 91 4 q ,231 2 0 , 7 62 . - ?, 00 - , 0 5 g - , 0 24 , 00 6 80 _ 0 ,2 2 8 20,641 - ,O q ,0 3 6 -,026 ,0066 g 51 ,23 1 2 0,4 5 2 1,01 ,2 30 -,0 3 2 ,0 0 65 9 5_ , 2 37 2 0 ,84 4 _ ,01 ,3 2 7 -,03 4 ,006 73 _3 ,230 20 , 6 q i 3,01 ,430 -, 03 8 ,0 0 6 8 5 o 54 ,2 31 20, 7 57 5, 01 ,6 2 5 - , 0 4 2 ,0074 3 =_ , 2 2_ 20,41_ ? , 0 2 ,_23 - , 0 4 7 , 0 0 8 2 0 56 ,220 20,90 9 0,0 2 1, 0 0 7 - ,04g ,0 0 0 3 7 _7 ,22o 2 0 ,6 g 2 II , 0 _ 1. 1 07 - ,0 5 _ ,0 1 100 5 8 ,23 0 20. 75 2 13,01 1 , 30 9 - ,058 ,01 2 8 3 5 0 ,22 q 20,654 _4,01 1, 3 51 - ,06 3 ,0 1417 60 ,2 3 0 20, 71 0 15,n2 1,3qo - ,0 73 ,0 1 808 61 .22 g 2 0 .562 16.0 3 1. 3 42 - ,0 8 6 ,06671 62 ,22_ 20,52_ 12, 0 3 1 , 24 7 - ,053 ,01 256 _ 3 .22 8 2 0 , 4 _2 I0,02 1 ,104 -,051 ,0 10 23 6 4 ,228 2 0 .6 1 7 A,O0 , o 16 - ,04 8 , 00 93 3 TABLE 3. - Continued.

(b) Continued.

P oint H R x 10 -_ c (z c n c m Cd ? 0 ._&l 3,059 -_,00 - ,1 5 & -,010 .00793 3V .36 ? 3.065 -2.15 -.G_2 -.C18 . U 0806 31 ,_I 3.03_ --.Q 3 .026 --,0 2 0 .00659 3 ? o_O 3 o02 2 fool ,20R --.0 7 4 ,006 ? 4 3 _ ._61 3 o024 _.f 1 _ o&16 -- , C _2 o 0 072F 3 & ._2 3 .020 S.Ol ,_ 0 8 -.03e .0083 5 _ . 3 5Q 9.09 0 _, 03 . 7 q3 -, 0 39 ,b1631 36 .3_ 3 o016 o,02 ,o65 -,042 ,01 3 28 _7 ._6A 3.006 !I.04 1.075 -.038 .01q68 9_ . 362 3.027 ]qoh ? ]+¢4 7 -.042 ,043 7 _ 9Q , _? 3 .029 l&, 0 9 i, (; 1 9 - o_ 9 6 ,09 55 6 POlN 76 44 ._I 3.014 12.01 1 .0 9 7 -,042 .021 6 5 _5 , 3 _ q 3,02g 1 3 ,_ 0 1. 0 2_ -,040 ,015R 9 4_ ,362 3,021 RoO0 o_ 7 3 - ,OGl ,0114 5 47 ,_6_ 3,07 3 6,00 o6 O _ -,0 3 7 o0 0 99 3 &Q , 96_ 9,O_l _, o 9 ,512 -, 03 6 ,00724 4o .361 3.010 ? oO0 o 31 3 - ,02_ ,00_ 7 5 50 . 3 _ 3 .024 .00 .12a -.024 .00 6 0 7

I

?7 ,. 3 #:_ 5 .. &7 7 - _.Oc -. le , l - .01 7 .O O7 a'5 _ . 3 h _ 5.4 7 t ., - .. . .

"oO0 -, 0 ' _I - 020 ,007R4 ? a •_ h 3 5 .4R0 -,c8 ,C_5 -,023 ,007_o 3 C .36_ .: 40_ 1,0! ,PlQ - o02b o t 0757 _ I ._6"_ 5. 4_'& 9,01 ,._ 22 -,030 ,C0773 "_ 2 ,'4_ 2 -_o 5 01 "_,07 • a 17 - , C3_ oC07R " _ _. .'_h? ,' . (,7'_ & . O] . = I0 - ,U33 o0(]_17 _4 o 3 6 3 5.400 5. 0 2 .603 -,0 3 5 .O0_Se _5 " , 3 hl F,('q3 5,02 o7U5 - ,C 4 J 000_77 36 ,q# ] 5,47_* 7,0 7 , 7 Q.9 -,0 3 _ ,009&2 3 7 •3 1 _ 3 5o4£ -_ q,O? .PRO -,041 oOlOOg 3_ , 36_ _.46_ 0.,02 oO7_ -.042 .0110,_ _c . 3 _- 2 5.46"_ 10.02 I,C_6 -. 042, ,Cll_O 4_ ._6& e. 00_) I I.0_ 1.111 -.04@ .0 1 7 0_.

&2 , 3 61 _, 9 57 ]2, 0 3 1,155 -.05 3 ,0146_ 4"4 . 3 t _. _ _.02_ __. 02 1,150 - o051 ,01o66 44 .363 6,01 7 14.0 2 i,i_-2 -o0_3 ,t_33_7 " _. b ,361 _, c ? , _ _ 5 , 0 2 !o177 - o052 or563[ 4_ .361 1 -.01_ I 6. n 3 _ 1.16__ -.06Z .OS t, _ =., • -? . 3 5o 5,0 9 1 !6,_ 3 i,]71 -,05 7 ,08141 4R .3 61, •, go t . 17, 0_ I,]60 -, 0 70 .i ? _ ? _ 40 , 3 ( _ 2 6o090 ,00 ,123 -- ,024 ,C0766 2q TABLE 3. - Continued.

(b) Continued .

Po i nt M R c x 10 - G u c n c m c d #f I N 7 @ 16 , 362 q ,040 ,0 0 , 119 - , 0 2 5 * 00 7 2 3 1 7 , 36_ o, 0 54 - _ , q g - .166 - *01 7 , 0 07 5 4 ] R , 3 6 2 9 , 04 7 . - 2 , 00 - ,0 74 -,0 1 9 ,0 074 5 : I Q , 362 q ,0 3 3 -,O _ ,0 2 3 - ,022 ,00 734 2 0 ,363 q , 07 6 1 , 0 1 ,2 1 7 - ° 0 27 , 007 2 3 21 ,362 0 , 0 5 8 2,01 ,31 1 -002 9 0 00 73 0 2 2 , 362 0,044 3 , 01 . 412 -,0 32 , 007 5 &

2 3 .3 6 _ 9 .075 4. 0 1 ,510 -. 03 5 , 007 _9

27 1 3 6_ 9 . 0 4 9 5. 07 1_ 1 5 -- ,C3 8 , 00 82 0 2 8 , 36 2 9 , 05 2 _,01 , 7 0 8 - ,04 0 , 00 _ 65 ?q ,36n 9, 00 5 7 , 03 ,8 00 - .0 41 , 009 26 3 0 ,3 _ 3 q ,0 81 q , O0 , 8 96 - , 04 2 , 00977 31 , 36 3 0 . 060 9 , 0 _ ,q q O - , 0 4 3 . 0 1 0 46 33 . 36 2 0 . 0 4 3 I 0 ,02 1, 0 75 - ,046 , 0 11 35 34 ,_61 9 .01 7 1 1,03 1. 1 44 - , 0 4 7 ° 01 24 7 35 .364 q.i 0 1 I ? .0_ 1.166 - . 05 1 . 01 6_i 3 6 , 3 63 9, 0 4 3 1 3 ,02 1 , 177 - .0 5R , 0 2 06 1 RU H 8 0 -- 43 , 3 6 6 9.1 06 14 . 01 1. 18 7 -.05 6 . 0 3 2 3 1 44 .3 6 3 9 , 044 1 5 . 0 3 1 , 1BA -,063 , 04 9 6 3 4 5 , 3 64 9 ,0 39 1 6 ,0 5 1 ,15 2 - ,0 5 9 ,0 78 02 46 , 3 64 9 .0 4 5 .01 ,121 - .0 25 ,0 0 7 2 8 RUN 4 T 26 ,364 1 5 ,1 9 0 - _, 9 9 - ,164 -*0 1 _ ,_ 07 1 0 2 7 , 3 6 3 1_, 133 - 2,00 - ,06 8 - ° 0 20 ,006 8 2 28 . 3 6 3 1 5 .117 - . 98 ,0 3 3 - ,023 .0060 0 71 . 3 6 5 15 .22 6 1 .0 1 ,2 29 - ,0 2 9 , 0 0 68 2 32 .3 6 _ 15.167 _,01 , 330 - ,0 3 _ ,0 0 7 00 33 , 3 6 3 15.106 3 .01 .42 7 - ,0 33 ,0 07 2 7 3 4 ,36_ 1 5 ,141 4,0 1 , 53 0 - ,_ 37 , 0 0 748 _5 , 3 6_ 15, 157 _, 0 1 ,62 7 - ,0 39 ,00 77 2 3 6 ,3 _ ? 1 5,0 8 3 6 , 0 7 , 7 25 -, 0 4 1 ,0 081 8 37 . 3 6 3 1 5 .1 3 5 7.n2 ,826 - , 043 . 0 0 8 6 0 38 ._ 6 4 15 .1 47 8.01 . q 1 8 - ,044 . 00 q 2 8 30 , 36 2 1 5 ,0 54 0 ,02 1 ,0 14 - ,04 5 , 0 1 023 4 0 , 3 61 15.015 1 0.02 I ,I01 - ,04 7 .01111 . 41 . 3 64 15.1 3 4 I I ,07 1 , 15 _ - ,048 ,0 1 2 50 42 , 3 6_ 1 5 ,13 3 1 2, 0 2 1 ,17 5 -,C Sg , 0 1 592 &3 , 3 6 3 15, 0 °0 13,02 1 , 193 -,056 , 0 2 21 4 44 . 36 4 15.116 14.0 3 1.208 -, 05 7 , 033 7_ 45 , 363 15,060 15,6 3 I, I _4 - ,0 52 , 0 5721 4 6 , 3 6 3 15,085 16.02 1 ,167 - .0 76 ,I_ 31 2 _ 7 .364 1 5 . 1 18 , 0 1 , 1 32 - , 0 2 6 ,0 0683

2 5

TABLE 3. - Continued.

(b) Continued Point M R x 1 8 -6 c cz c n c m c d 4 .£n3 3 .0o& -1.0_ ,0_0 -,021 ,00552 .500 3,00t 1,01 ,?IQ -,02b .GO_37 h .502 3.01_ Z.O ? , 31 ° - ,C_9 , ¢ 054A 7 ,5C_ 3,001 3 ,02 ,426 -,0 3 1 ,00 5 5 7 ,500 3,00 _ _,_ ? ,571 -,035 ogC602 o ,5_1 3,006 5 ,01 ,_ 2 3 -,035 ,O0_Sa ] O .50n 3 .00 2 5,O1 ,71g -,035 ,00g7g II ,603 3,000 7,Q 2 , 8 N 8 -,09_ ,01177 _ ? ,&G_ 9 , 601 _ ,N : ,_6 - ,031 ,01 4 52 13 ,&9@ ?,Wgq I0, O ] . 9 95 -,O_Q oO23_0 14 .501 90 t 04 ,00 ,129 - ,_24 ,005 3 6 P I P ' 4 2_ 2 ,5 G ? 6,0n2 - ._ ,02o -,024 ,OO 7 qo ,to2 9, g g5 1,02 ,23q -, O ag ,0 C787 ,_ 0 0 5. 9 89 _,O ? , 3 _? -,6 3 2 ,0080 7 6 ,50L 5,900 4,0] ,547 -,036 ,00813 7 ,_02 6,01Z 5,02 ,6_ 3 -,030 .0086S P ,_03 F ,O? 7 5,01 ,7_ , ) -,0 4 1 ,COO4V o ,503 6,_, 2 _ 7,_2 ,8_ 3 -, 04 2 ,61084 _O ,50_ A,045 8,0 ? ,Q 3 4 -,0 3 A ,01 3 _5 ]I ._OG 5 .c_2 . 01 . 13 _ -.b2 7 ._077q _l f u ! 1 1 2 ,50& 15,070 °O_ ,134 -,026 ,n0719 I_ ._n% if,O_! -,oo ,{ ? g -,O ? & ,00711 I_ ,5( J3 15,061 t.O_ ,2&l - ,O?q ,0071 _ .IA ,5 0 3 If,O& h ? , t _ , 3 65 -,03 3 ,0 0 7 3 2 I_ ,503 1 5 ,05 7 3 , q 2 ,&4£ -,03 5 ,0075] 20 o50_ 1_o065 &°0l o55W -,037 ,00777 2 2 .5 0 _ 15.0=2 5.01 . 6 f 3 -.640 .0081_ 2 5 ,_0 & 15.084 ?.64 0855 --,04_ 100_67 26 .500 14,q_5 m, U 2 ,CZ5 -,C3g ,01231 TABLE 3. - Continued.

(b) Continued Point M R x 10 -s c 0 c n c m c d R UN 6 9 1 . 5 98 2. 0 0 0 2.0 2 :. 3 45 - . 03 4 . 0 061 3 2 .60 0 2. 0 05 3 , 0 2 .4 5 4 - . 03 6 .0 0 64 5 3 .601 2 .006 4. 0 1 . 5 68 - . 03 9 . 00 6 7 8 R UN 5 ill .6 0 1 3 . 00 8 .0 i .14 0 - .029 .00491 16 .6 00 3,038 - .9g . 0 2 9 - . 0 26 .0 0 493 2 1 .601 3 . 0 08 I.OI . 2 3 8 -. 03 1 . 005 3 2 22 .6 01 3 .0 01 2, 0 2 . 3 47 - .0 33 .00 55 6 2 3 .60 0 2 . 9 99 3 .0 1 .4 5 6 - . 036 . 0057 6 2 5 .60 3 2.996 .01 .128 - .02 6 .00485 26 ,6 0 2 3 .0 15 4,02 . 5 6 1 - .0 37 . 00 599 2 7 .602 3 . 0 12 5. 0 1 .65 8 -,0 3 9 . 0 0825 2 8 .6 00 3 . 0 00 6 . 0 2 . 7 4 7 - . 03 6 , 0 1 0 8 1 2 q .600 2.999 7 ,02 .8 3 6 - , 033 . 0 1291 3 0 .602 3 .0 1 0 8.0i . q 4 9 -.028 .0 1 455 RUN 70 4 ,601 4, 0 0 3 1.8 0 ,3 1 q -, 033 , 00 6 83 5 .6 0 1 4.0 09 3 . 0 1 .45 0 - .0 37 . 007 16 5 .600 4 .00 1 4. 0 2 ,556 - .0 38 , 007 6 3 RUN 1 3 i .6 0 4 6,0 6 2 .01 .1 33 - . 0 2 7 . 00 66 2 3 ,6 03 5.990 -I.00 ,0 2 q - .0 2 6 . 0 0 77 6 4 , 6 0 6 6.00 7 1, 0 2 ,252 -, 03 2 ,0 0 7 1 2 5 .602 5.978 2. 03 . 3 56 - .034 .0 0 6 75 6 .6 00 5.965 3 , 0 1 ,461 - ,036 ° 0 0 7 2 4 7 .6 0 2 5.986 4.0 3 .568 - .0 38 . 00 75 8 8 .60 3 5. 9 96 5. 0 1 .680 - ,040 ,00 8 52 9 .601 5.9B2 6.0 3 . 7 8 7 - . 03 g ,00 q 5 4 I0 ,bOO 5, q 7 8 7 , 03 .8 q l - . 0 36 ,01 1 2 5 ii .603 5. 9 9 6 8. 0 1 ,995 - . 03 1 , 0 1 43 6

2 7

TABLE 5. - Con t inued.

(b) Continued.

Po i nt. H R x 18 -6 c a c n c m c d ° 7 .#_Z _,_2.J I, _c ,324 - ,0 33 .¢0Pll .6 0 1 F.0 3 7 3 .0E ,6 5 6 - ,0 3 6 .00 8 &o • #,. I N 9 "p 1 ,60 _ _.O B g .O1 .133 -,02_ .(_0785 2 .602 o.0 ? & -t.n n .025 -.026 .0078 2 3 ,601 £,01_ 1,01 ,246 -,031 ,00776 .6_& Q.nO6 4.01 .57 4 -.0 3 8 .OOPTO 7 , f 'bO @, Q q _ 5, 0 2 ,_61 -,_60 o_O q l4 .&O_ °.Ol_ 5 , 97 .795 -.039 .009q0 q ,60] p,c q n 7,02 o8 0 9 -,035 ,01142 10 .60_ o.0_I 9.¢ ? 1.011 -.U29 . ¢ 150_ II .6GI q . Og5 .CI .l&O -.02 0 .00 7 £1 _lJlq 7_ I0 ._0_ IO.62B _.0_ .34R -.034 .OOPO0 II .An4 i_.037 _.04 ._60 -.037 .OOelO _ 2 .6oi co q _l A,O_ ,f6 3 -,0 3 _ o ( }084_ Pl ._I !2.0_ - ,oo ,u2_ -,_26 ,5074 B 72 ,_0! ]2.0 3 v t.OP ,2_I -,OB_ .C074] _3 ,6 0 _ 12o0l A 2,01 . 3_0 -,035 o00766 34 ,60_ 1 7 o616 _,02 ,46_ - , ( 37 ,00 7n3 3 6 o609 11. q n 9 4 ,0_ ._7e -°0 3 9 .C082] ? 7 ,_.01 l l, q aO 5,0 2 ,6co -,061 ,OOP61 9_ ,6 u _ 12. u l a 6,01 ,7o8 -,C 4 0 ,OO q BC _ q .&O2 l]. qq z v , e° ,o1 3 -,C36 ,01111 _n .60_ 12.05_ a,01 1,0_0 -,030 ,01507 _I .60_ 12.O U _ . e l .14 J -._29 .007 3q TABLE3. - Continued..

(b) Continu e d.

Point H R x 10 -s c a c n c m c d i_q jq 4 3 4 . 60 6 1 5 . 06 2 - 1 o0 0 , OE Q - . 02 6 °00 716- 5 , 6 04 15. 0 49 ! , 0 3 ,2 48 - , 03 1 , 0 072 3 6 ,60 ? Z 5,O 3 6 Z , 02 , 3 59 - ,0 35 , 007 3 4 7 .60 Z 1 5 .0 Z 7 3, 02 . 4 6 9 - . 0 3B . 007 6 0 8 . 6 01 15.00 _ 4 .04 ,578 -,03 9 ,007 q l q ,605 1 5 .007 5, 04 , 6 8 q -,0 6 0 .008 38 10 .6 05 1 5.0 28 6 . 04 .80 4 -.0 6 0 . O O g 14 11 ,60 1 15. 00 Z ?,0 6 . 916 -.03B . OlOql I Z . 602 1 5 . 0 2 9 8.03 1 . 016 -. 0 3 0 .0 14 71 13 .6 01 15.01 3 .0 0 .136 - .OZ 8 .0 0 7 1 8 mUN 2 3 31 . 6 05 2 0 ,124 , O l . 130 -,C3 1 . 006 9 6 33 .6 05 2 0, 1 35 - l .00 , 018 -.0 2 8 .0 06Q 7 34 .603 2 0, I 0 0 1 , 02 , 2 49 -.0 35 ,0 06 9 2 35 .60 3 2 0,09Z ? .0 2 .3 6 2 - . 0 3 8 .00704 _ 6 , 603 20.0 9 1 _ ,0 2 ,47q -, 0 4 1 .0 0 719 37 .6 07 2 0. 0 7R 4 . 0 1 .5 Q 6 -, 0 6 6 .00762 38 , 6 0 6 20.03R 5 . 0 3 .706 -. 0 4 4 . 0 077 2 3 q , 6 0 _ _ O. O OO _ ,03 ,82 7 - , 045 . 0 0 8 3 2 4 1 ,604 ZO.040 7 .02 . g 30 -. 04 0 , 0 0 9 6 1 42 . 6 0 5 2 0 .0 69 8 .n 2 1. 0 2Z -. 0 3 6 .01 1 78 pv j tq 7 3 1 5 ,6 0 9 30,g 0 4 2, 03 ,3 6 6 -. 0 36 . 00 708 16 , 6 0 P 30.108 3 ,0 _ ,4 7 q -.038 ,0 0 7 26 1 7 ,604 3 0, 08 A 4,06 , 595 -.0 41 . 0 076 q PlI N 44 i i 1 4 .60 5 4 0,3 3 3 ,_ ? . 14 Z - .030 ,00630 15 , 6 0 6 4 0, 41 0 - 1,00 .O Z 8 - ,0 2 6 .00 6 33 1 6 . 6( 'J B 40,33 8 i . 0 2 • 25 9 -. 0 33 • 0 0632 1 7 , 6 0 6 4 0.3 18 Z , 0 1 ,36 q -- , 03 6 ,0 0 64 7 1 8 . 6 0 8 6 0.640 3 .0 1 . 68 1 - . 0 39 . 0 0 668 l q .6 07 40,38 0 4, 0 2 ,59 4 - . 041 , 00 6 95 ?0 ,60 5 4 0. 26 3 5.0 2, ,708 - .0 4 3 .0 0 7 38 21 . 6 0 1 _ & O , 4 0 8 8, 0 2 ,826 - , 04 3 ,OO 8 1 Z 22 , 60 q 4 0 ,47 4 7, 0 3 , 0 43 - . 0 3 6 , OO q 8 _ 23 .602 40. 15 _ Bo O1 1 .0 3 3 - .0 2 9 .01 40 5

2 9

TABLE 3. - Continued.

(b) Continued.

Point M R c x 10 -s u c n c m c d 16 ,441 ?,_7o ,('I ,143 - ,02 Q ,00553 17 ,h4_ ?.8FO - 1,nO ,02_ - ,026 ,O0_5Q I_ ,_2 2,e_O 1,01 ,245 -.032 ,0054_ 1e o 6 _9 2 .882 ? . 02 . 95_ - ,094 , C¢ 57 4 2,1 . 64 ' 3 2 . _74 _.01 . &63 - . 03 5 . OOhO0 21 ,_ 2. 8 P5 _,01 , 5 77 -, 03a , 00 6 2 7 2 2 , 6 4 2 2 ,BP3 5 . 01 ,6 7 g -, G3_ , 00 7 6P 2_ , 644 2,8P6 6 .0 2 , 77 5 - ,036 . 0104¢ l Pl l _ l q _1 . 4 41 _,OSB -.QQ ,O ? g -.0 2 7 .00641 _2 ,_41 _ . _2 _ 1.n1 , 2 50 -,O3Z .00660 5_ .647 6.04 7 2o02 .356 -. G34 . 00682 _4 , h41 h , O0_ _ , 01 , 4_5 - , 0 37 .00 7 11 55 . _4 7 6 ,006 4,01 . 5 7 & -, 0 3 g , 0066 7 _ , A44 6 . 005 _ , 01 ,677 - . 0 3 9 , O CP _q _ , _&O 6 ,011 &o01 , 7 8g -,C37 , 009a3 _Q . _47 6 , 65@ oOl , ]_2 - ,O_g ,O061g IP .h43 €.003 , 06 , 146 - . 031 , 00 7 _5 !_ ,64_ _,021 -I.O 0 ,O?g -,028 ,O0 ? m 2 20 ,h_ ? _,OaO 1.03 , 2 61 -. 0 3 4 ,_0 7 94 _! .64P 0.0_ _ , n_ . 37 h - ,037 ,00_17 2 ? ,640 g. Ol _ _ , (i_ , _Q 2 --, OaO .00 8 50 _3 .6_0 o.020 4 . 03 .506 - .0€2 .O0_Q3 24 ._4 7 g.044 5 . 03 , 7 1 o -. 04_ . OOg7?

_ . h_C Q , OI3 h , O_ , F25 - .04 1 , 01 0 4 2 2_ . _q Q.OOS 7.04 , q_ 7 -.034 , 0 1 230 PIIN I ?

5 .h a p 15 . 010 1o02 ,254 - o03 3 o 0 0 7 22 7 ,h42 I_ , 017 _ . 0 2 ,3 6 3 -.0 3 5 ,0 0 737 p ,_44 I_,6 9 _ _.0 1 .470 -, C 99 ,00765 I{; . 64_ 15 , _00 5o02 ,ho_ - . 041 , OOB_P ]I , h4_ 1 5. 00 _ 6,0_ ,811 - . 0 3 7 ,0090_ 1 7 . &aP ]5 .1 61 , 0 1 . laO -,0 30 . t 0 71 _ _ 3 ,64 0 14, G _Z 7, 0 3 ,_ 2 8 -o 033 ,O_ O g_ 14 , 6&4 !5 . 026 n,O ? 1 , 0n6 - ,028 , 015Q 5 TABLE 5. - Co n tinued.

(b) Continued.

Point H R x 10" s c a c n C m c d P UN 18 3 5 . 6 46 40 .3 7 0 .00 ,145 - ,0 3 1 , 006 33 16 .645 40.2Q8 - 1, 0 0 ,02_ - ,0 2 9 o00 6 34 1 7 . 6 47 4 0 ,3 8 5 1,0 3 ,_67 -, G34 , 006 4 & 1 8 , 64 5 & 0 • 2 77 _, 0 3 • 377 - , 0 3 8 , 0055 1 1 o , 6 45 4 0. _05 3 .0 1 , 4 qi -,0 4 0 , 00 6 77 _ 0 , 6AB 4 0,40 5 _, Ol •b ol --•04 2 , 0 070 2 2 1 •6_6 40 .313 5 . 0 1 • 70 6 -. 042 . 0 0 74 1 2 3 . 5 5 0 4 0 , 5 25 6 , 0 2 ,834 - , 0 4 0 ,{ 0 8 1 5 7 4 ,64 4 40,12 9 7 .07 .Q 5 6 - *034 , O II I Q 7 5 . 6 44 4 0 ,I 0 3 8 , 0 1 1, 0 3 0 - , 03 1 , 0 1755 Dt P J 6 32 , 6_0 2, q 9 8 ,01 . 13 9 -, 0 3 1 .00 5 17 3 3 . 681 3.000 -,9 8 ,027 - *029 , 0 C 5 1 5 34 .6 8 1 2, q g_ 1 , 0 _ . 244 -, 03 4 .0 05 46 35 ,68 0 7 .go2 ?. 01 ,35 4 - , 0 3 6 , 00575 3 6 , 6 8 0 7, 9 q 5 " _, 01 ,t' 66 - , 0 37 , O0 5 q O 3 7 ,6 80 ? , qq 4 4, 0 2 . fi 8 0 - , 039 ,0 06 7 1 3 8 , A8 2 3 . 000 5,,0 1 , 685 - , 03 q , 00602 3 q , 6 8 0 2 , q 93 A , O1 ,79 2 - , 03 8 ,0077 6 I_I | N 7 i l 4 2 ,6 82 6 , 026 - I, 00 , 025 -. 029 , 006 44 - ', 3 ,6 83 6, 02 6 1. 0 1 . 250 -. 034 ,0 0 60 8 44 ,68_ 6, 02 5 _-, 03 .36 1 - , 0 3 6 , 0063 5 4 '_ ,68 0 6, o oq 3, 01 ,4 6 9 -, 0 39 , 00707 4 6 , 68 3 6 , 037 4on? • 57 R - , 0 3 0 ,00671 € ,7 ,6 8 1 6 .0 2 1 5 , 02 ,6 90 - ,0 40 , O07ql 4 R ,67 q 6 . 0 05 € ' ,,07 ,T q O - ,0 35 ,0 0 831 4o .68 0 6, 000 . , 0 1 . 1 4 3 - , 03 1 , 00 6 27 24 , h B? 15. 05 _ , 01 ,1 4 3 - . 033 . 00 7 51 25 ,6 8 5 15,14 3 - , O q , 030 - , 030 ,007 45 76 ,68 1 15 . 052 1 ,0 1 , ? & 6 -,0 36 . 0 0 7 5 0 2 7 ,6 P 1 15 , 077 2, 01 , 377 - , 038 ,00 77 7 ?8 .6 fl3 15, 01 8 3 ,0 2 , 48 5 - , 040 ,00 807 2 q . 684 1 5. 03 8 4,01 ,5 90 -,0 41 .00 8 49 _ 0 .68 1 15 • 03 1 _. 0 2 . 706 -, 0 4 2 , 00 918 31 .6 P3 15,074 6,0 2 .8 21 -, 0 4 1 , O10 6 e TABLE 5 . - Continued.

(b) Continued.

Point M R c x 1_] -6 Q c n c m c d DtlN & 2 , R O 3 3 ,00n ,0 1 ,13 3 -. C 3 1 ,0 0 5 27 ,_q_ 3, 0 C ] - ,00 , 02 3 - , 029 , 0 052 7 = , 6 ql _,00_ t.Ol ,240 -,034 ,0 0 557 s ._qs 3.01 7 _0 0 2 .346 - o 03 6 o00_ 7 5 7 ,_q_ 3,0 0 7 o ,07 ,45 7 -,C39 oO05Qg B ,6 q 3 _o0 1 _ 4,Or o 5 77 -- o 0 40 ,006 3 F ,6 0 7 9. 0 OA 5,0 2 o_5 -o040 ,C07 0 1 P!IN lq 2 ,7_3 6,007 ,01 ,1 3 7 -.0 3 3 ,_b674 . 7 0P _.001 -,Qq ,02 3 -. 0 31 . 0 078o 4 ,701 6,001 1,0_ ,254 -,0 3 7 " ,00678 ,709 f , C l ? _oO ? 0_64 -,_49 ,O CT Z q •765 6,020 _oO] , 4 57 -,041 ,e0826 7 ,?Om 5,oea 4,01 o579 - ,043 ,% u 882 ,70_ 5,006 S,O] ,_qO -,049 ,OOqOO e ,707 6,0_0 6,0_ ,TOW -,047 .01464 ptl_ t Z 6 3 ,70_ q. O12 -,oO .020 -. C 30 .OOe0 7 ,70_ Q,OO h 1,04 ,241 -,C 3 4 ,00805 S o702 q ,025 2o0 ? ,35_ -o0_9 ,008 2 5 6 o7 0 2 8o97 3 _o02 o472 --,040 ,00880 ,70 3 Q,012 _,03 , 5 _ --o 0 42 o00 92 2 I0 ,705 g, O 16 _, 0 2 o68B - oG4_ , 0 10 2 S Ii o?0! 9,001 6,07 ,799 -,042 on] 3 _ l 1 7 .7(I! o,OB_ ._I oI_5 --o_3_ ,00706 OlI N _ 7 13 ,701 12,020 ,01 ,13 5 -,032 ,00 7 5 8 I_ ,70_ 12,040 -I,00 ,CZZ -,030 ,06_ 7 2 ]_ ,& G ° 1 ] oQQ_ 10_ ] ,7 9 ,) -o035 o00 77 _ ] .6 o 7 0 2 I ? ,OBO _,£I oB_4 -o0 3 S oOU_06 17 , 7 04 1 2 oOl_ 3o01 o481 - ,041 ,0085 2 ] a ,70_ 1 2 ,01_ 4, 0 1 ,502 -,042 ,OOgSl _ O , 70 6 1 2,0_'J 6 . 0_ , 70 3 --,O&2 , OlS qS - TABLE 3. - Continued .

(b) Conti nue d.

Point H R x 10 -s c ( 3 c n c m Cd .

13 ,703 14,q q l -=o q , 0 2 3 -,030 ,0 07 58 ] 4 . 70 2 15 .036 I =0 1 *2 55 -,036 ,00765 15 , 703 1 5 = 03 1 _ ,02 *365 -, 0 38 * 00 7 Q 3 16 ,706 15 , 06 4 3 .0 1 .471 - o G4 0 , 0 084 1 1 7 o702 15, 0 5 4 4 o 01 o 5 8 1 - o 041 o 0086 8 18 .?01 1 5.03 Q 5,0 _ .692 -.043 ,01043 l o .?05 15. 0 46 6 ._ 2 ._ 03 - . 0 4_ . 0 _ 64 3 2 1 . 70 0 15,046 , 01 , 1 4 6 -,0 33 , 007 4 8 Q tI _ ??

2 2 ,7 0 6 20,049 - , q 8 ,0 17 - , 033 ,0 0 738 2 3 ,703 2 0 , 031 1 , 0] . _ 6 2 - * 0 3 Q , 0 0 742 2 4 .703 _ 0,035 _ . 0 1 .3 _2 -, 04 3 , 0 0778 ?5 , ?0 5 _ 0 , 076 3. 0 1 .5 02 -. 0 4 7 , 0 0 837 7 6 , ?05 7 0,0 8 5 4, 01 , 6 1_ - , 0 47 ,0 0 8 q 7 2 7 , 7 03 20, 0 3 ? 5,0 2 . 7 1Z -,0 48 , G l127 ?q , 70 6 20,09 4 b , 01 , 8 1 q - , 050 , 017 12 30 , 703 _ 0 , 06 4 ,01 , 14 2 - , 036 ,0072 1 gU_ 36 ? ,7 08 4 0. 24 0 .0 1 , 15 3 - . 035 ,0 066 2 q .70 6 40, 25 3 -1 , 00 , 03 4 - , 03 _ ,0 0660 II . , 707 4 0 ,I q 4 1 , 0 1 ,22 _ - , 038 ,0 0688 1 _ , 70 4 4 0 , 1 67 2 , 0 1 , 386 -, 0 4 1 ,0071 q 15 ,706 40,14 6 3 ,01 ,491 - , 0 4 2 , _ 0 7 70 17 ,7 0 5 4 0 , 1 4 0 4 ,01 ,605 -, 0 44 ,0 0 85 0 pq M 48 51 ,7 0 6 4 0,l qq 5, 05 , 707 - , 045 ,01145 _ 2 , 707 4 0,25 4 6, 02 , 807 -,0 4 6 , 01 74_ TABLE 3. - Continued.

(b) Continued.

Po i nt H R c x ] 0-6 a c n c m c d 61 ,1 20 6. 0 6 0 - I,00 ,02_ - , 03 1 , 0 06 7 4 _2 . 7 7 1 6, 07 _ t , 0 1 ,2 4 R - ,C 3 5 , 00 683 64 , 721 6 ,0 67 _ ,0 2 , 3 6 1 -, C38 , 0065_ 6 5 , 7 27 6 , 0 41 3 , 0 1 ,469 - , 039 , 0073 1 _ U N 2 0 _ _ 04 _ 12 .7 _I 6 .0 2_ 4 . b i ,F_q { Q,IN 1 4 r 1 4 . 7 _ 0 . 0 1_ - ,qq ,027 - ,0 31 ,0 0 @ 0 2 1 5 . 7 22 n , O! _ 1, 0 _ ,25 k - , 037 ,0 0 P 5 2 1 6 . 7 2C _.0 9 _ _, 0 2 ,36 3 - , C 3 q , OO aO Z 1 7 . 7 _ ? Q.O _ 7 3, h 1 .4 7 4 - , O A1 ,01 03 _ I A ,7 2 Z Q .O07 k ,03 , 5 81 - , G42 , UI21 _ lO , 7 ] q S ,O_ ,01 , 14_ - ,C_3 . 0 0_ 03 P l f q z_o 2m , 7 2 ? 15,0 6 9 - , O O , 0 2 6 - , C 31 , 00 7 6 2 2 4 . ? ?_ 1 5 . 0 2 8 1. 0 1 ,2 5 1 - ,0 37 ,OO81 q 2 _ ,72_ 15 ,030 2,0] , 3 6 1 - ,G_O , UO Q 0 6 2 6 .72A 1 5 .021 3. 0 ] ,_6 q - .04 2 ,O O g q O ? _ . 7 24 1 5 ,0_B _ ,0 1 , 570 - ,0 4 5 , 0 1 1 2 1 ? o . 72 3 15. 0 06 ,01. ,1_ ? -, 035 ,_ OT? Q 1 3 .741 _, O Oq -I , 0 1 ,U1 7 - ,03 3 , 00 8q l 14 .74_ 6 . 015 l,n 2 ,2A 7 -, 0 3o , 0 110 3 15 , 7 40 6,000 ?,01 , 356 -. 041 ,01 ? 46 16 ,74 3 _ , 02 5 RmOP , 4 =A -- ,04_ , 0 17 06 1 7 ,7 4 1 _.011 ,0 1 ,1 3 7 - ,0 36 .O O qS_ TABLE 5. - Continu e d .

( b ) C o nti nu ed .

P o int H R c x 10 - s a C n c m c d 3 5 .742 1 5 ,037 - . 08 ,0 22 - , 0 3 3 ,0 08 Z 6 36 .7 4 1 15, 0zq 1, 0 1 , Z 53 - , 0 40 ,010 24 37 .7 4 3 1_,004 _ , 01 .36_ - , 0 4 4 ,01 2 q_ 38 ,742 1 4, q 3 6 3 ,0Z ,4 6 1 -,04 6 ,0 16 3 9 3 9 , 7 4 1 1 5o 0 4 1 , 01 , 138 -, 036 , 00908 PUN Zl _ 4 .7 60 5, 965 , 0_ , 1 2 5 - , 0 4 0 ,0 1179 15 , 799 5, q7 3 - I , 01 ,00 9 -, 0 3 8 ,0 1 04 2 17 ,7 6 5 5 . 99 5 1 . 0 1 ,Z 3 5 -*04 5 .0 139 7 1 8 .76 1 5* 99 6 _*0_ , 3 4 3 -- *0 52 * 0 1767 I q ,?63 6,009 3 , 02 , 4 34 -,060 , 032 7 0 Q[JM 7 7 I ,76 5 9 .021 * 0 3 , 0 9 4 -*0 3 5 , 0 117 4 4 ,7 6 2 9 ,022 - .9_ , 0 01 - ,034 , 0100 0 5 ,75 9 q*O 0l 1,0 2 . 2_ -- , 0 4 0 , 0 1 283 A , 7 62 9. 0 17 2, 02 , 3ZZ -,0 44 ,0 1794 ? , 763 9 ,02 7 _.O A , 4 1 9 -, G 5 2 ,02 P43 8 , 762 9 , 036 ,3 6 * 14 5 -* 0 3 8 , 011qz i R U N 7 8 q , 7 63 1 2 . 02 4 - *0 4 *0 9 6 - ° 036 ,011 0 1 ?0 ,7 6 5 12 , 0 4 2 - , ° 2 , 003 -*03 4 ,0 1 0 3 2 1 1 , 762 1 1,q q 2 _ , 0 7 ,2 70 - , 03q , 0 129 8 1 7 , 7 64 1 2 ,0 09 2, 0 4 , 3 2 3 -, 0 4 1 ,01 P 6 2 13 ,765 1 2 , 0 2 1 3, 03 ,4 1 0 -,049 , 02€Z 4 DUN 3 4 . 4 0 ,76 0 15, 03 7 , O1 , 131 - , 03 9 . 01181 4 1 ,761 1 4, 9 0 2 - 1, 00 ,01 2 -,036 , 00 97 4 4Z ,7 61 14, 9 74 1,02 , Z 4 0 - . 045 , 01 4 63 43 . 7 6 3 1 5 ,000 2 * 0 3 =336 - * 0 48 , 0 _336 44 ,764 15 , 0 0_ 3 ,0_ , 43Z - , 057 , 0 340 2 TABLE 3. - Concluded .

(b) Concluded .

Poin ' t I"1 R c x 1 0 - s a c n c m c d PWlN 3 _ I P . 7 9 3 6.0_ _ .01 .I03 - .043 . 0 211 ] !o .7_c e ,._¢4 - .gQ - .00_ - .0 3 B .01450 2n .v_ _.011 1. 0 1 . l Oq - ,04 h .02_6_ I .781 15o 0 :_ .O l .I0 7 - ° b _Z ,0 1 777 .7_ ? 1.5.051 - t._O - . 00 7 - .0_ 0 . 01_ 0 2 = . re ? 15.C 3 7 1.31 , ?01 -.04o .07722 _i .804 6,003 . 0] . 05 4 -.04 5 .0 3 _82 ? ? . P C5 t .OO7 - .oQ -,0 5 7 - ,04u ,02o6 c Z3 ._ { 2 f.ge5 1,01 .I=5 -,O_Q ,C41Sv P U _' I S 2 _ .80 C 9.021 -]..On -. 0 41 -.04_ .0 2 106 ? 5 ,802 Q,'_ U_ _ Io0 2 , 1 43 o648 o 03 601 SYMBOLS This list of symbols is applicableonly to Table 4.

ALPHA angle of attack, deg.

I C airfoil model chord, cm CC section axial-forcecoefficientfrom airfoil pressures CD1 drag coefficientfrom wake total pressure probe, Y / (b / 2) = 0.125 CD2 drag coefficientfrom wake total pressure probe, Y / (b / 2) = 0.000 CD3 drag coefficientfrom wake total pressure probe, Y / (b / 2) = -0.125 CD4 drag coefficientfrom wake total pressure probe, Y / (b / 2) = -0.3 7 5 CD5 drag coefficientfrom wake total pressure probe, Y / (b / 2) = -0.500 CDCOR1 drag coefficientcorrected for a "threshold"decrement,from wake total pressure probe, Y / (b / 2) = 0.125 CDCOR2 drag coefficientcorrected for a "threshold"decrement,from wake total pressure probe, Y / (b / 2) = 0.000 CDCOR3 drag coefficientcorrectedfor a "threshold"decrement,from wake total pressure probe, Y / (b / 2) = -0.125 CDCOR4 drag coefficientcorrected for a "threshold"decrement,from wake total pressure probe, Y / (b / 2) = -0.375 CDCOR5 drag coefficientcorrected for a "threshold"decrement,from wake total pressure probe, Y / (b / 2) = -0.500 CM section pitching-momentcoefficientabout quarter-chordpoint CN section normal-forcecoefficientfrom airfoil pressures CP pressure coefficient MACH freestreamMach number MLOC local Mach number m P,L local static pressure, psi o PT tunnel stagnationpressure,psi RC Reynolds number based on chord TT tunnel stagnation temperature, K X chordwise distance from leading edge of airfoil, cm Y spanwise distance from leading edge of airfoil, cm

TABLE4.- NACA65 1 - 213 SURFACEPRESSURE COEFFICIENTS

r EST 14_ PT 20.2 5 13 PSI CN .1 3 0_ C01 .00652 CDCORI .00 6 5 7 RUN 13 TT 15 3 . 2 _2_ K CM - . 026 h CO2 .0 0 72g CDCOR2 .0 0 7 3 7 POINT I QC 6.0620 MILLION CC .005 3 CD 3 .00 6 54 CDCOR 3 .00662 t I A CH .60 3 9 CD4 , 00737 C DCOR4 , 0 0 7 4 3 ALPHA - .01 0 2 DE_ CD5 , 00 67 6 CDCOR5 . 00 67 6 IPPER SURFACE LO , ER SURFACE SPANWISE Y l C CP P , L I PT HL.]C X I C CP P_L / PT MLDC X I C Y I C CP P_L I PT MLOC _.0030 I.I 0 _ 1.0020 O.00O0 0.0000 1.1049 1.0020 0.0 0 00 .1508 .1702 -. 3 945 .7021 .7291 .0244 •0531 .791o .5@79 ,012:7 -,2108 .738 9 .6720 ,1508 .5033 -.4196 .6971 ,7369 •0513 -.1355 .7 5 3_ .04_Z .0269 -.1734 .7462 .6b03 ,1507 .8357 -.4242 ,6962 ,7383 .0765 -.225_ ,7358 .0707 .0502 -,212_ ,7385 .6725 .1507 1,0000 -,4289 .6952 .7397 .I005 - . 3 070 .7195 . 7 022 .0 7 42 -,2316 .7 3 47 .67_5 ,15 0 8 1 . 1 66 0 -.4 1 25 ,6985 , 73 4 7 .1506 -,4123 •0985 .7346 .099 7 -.2452 ,7320 .6827 ,4984 .1708 -.5965 , 6 61 7 .7913 ._004 -.484 3 .6_41 .75 5 _ .14go -.2728 .7265 , 6 9 14 ,4_84 . 33 68 -.6193 .657 1 ,798 3 .75 ] 0 -.54_1 .6714 . 7 764 .1996 - .2015 . 7 227 ,6972 .4984 .5028 -.6 3 08 .6548 . 8 0 1 8 .2_8 -.5799 .6650 .7_62 .2 4 90 -.2q77 .7215 .6991 .4983 1. 0 0 0 7 - .6 3 96 .65 3 1 .8045 . 3 4_2 -,6166 .657_ .7975 .2g94 -.3148 .7 1 _O .7 0 4 4 .4_84 1.1667 - . 0 01g .6606 .792g .39 8 6 - .658 i ._94 .d1 0 2 .3481 -. 3 2 77 . 7 i 55 .7 0 8 4 ,7950 .17 0 5 -. 0 64 3 ,7681 .6255 .4&70 - . b632 . b _84 .811 8 .3076 -.3451 .7120 .7 1 38 .795 0 . 33 75 -,0507 .7709 .6 Z 1 2 .49_ 3 - .6350 .6_40 .8031 .4 46 7 -, 33 31 . 7 144 .7 10 1 , 7 952 ,5027 - .044 7 , 772 1 ,6 1 92 • 5466 - . 5506 .6_97 . 77 90 .4 97 2 -. 3 177 , 7 175 .705 3 .7952 .8 3 47 -•0477 . 77 1 5 °6202 .5062 -.4461 .691_ .7450 .5452 -.2768 .72 5 7 . t 92 6 ,7952 1,0008 -.0 53 1 .770 4 .6219 ,6 4 57 -• 3 411 .712_ . 71 26 .595_ -.2264 ,7 3 57 ,6 7 69 , 7 952 1 ,1667 -. 0 6 4 5 , 7 681 ,62 5 6 .6957 -.2380 .7334 .6805 .6442 -.171_ .7467 .6597 . 7 46! -.1 3 63 .7534 . 0 49 1 .h944 -.1120 ,7586 .6408 .7q52 - , 0 4 3 4 .7t23 .b16o , 7 442 -.051 3 ,7 70 _ ,6214 ._457 ,0 5 0_ .7_IZ .58S2 ,7879 ,0101 .7@30 ,6015 .g006 ,1331 ._07b .560 9 ,8444 ,0703 ,7951 ,5818 t N U D

TA B LE 4.- Continued

T ES T 1 4_ P T 6u.2:_7_ P S I CN .0293 COl .O0oF7 CDCORI .006 q 3 _IJN i3 TT [5_._ 0 44 H CM -. u 262 CD2 .00778 CDCOR2 .00788 _gl _T 3 RC _.g#02 _ILlln_ CC . 00 o 2 COX ,00764 COCOR3 ,0 077 6 :IACH .6 5 31 CD4 .00800 CDCOR4 .60_12 ALPHA -.9_70 DFG C_5 ,00735 COCOP5 ,00741 J a PEr S U PFACE LilWEK SURFACE SPAN W ISE X I C CP i,L I PT HL t )C X I C CP P_L I PT MLBC X l C Y / C CP PjL / P] MLOC 0,000_ ].u913 .4494 .02vu ¢.0000 1. 0 913 . g 994 .02 9 8 .150_ .1702 -.3113 ,7197 ,7019 .)944 . 2 357 ._£_!o .9249 .312Q -.heal .b70 i . 7 764 .150_ .5033 -. 3 2 3 2 . 7 17 3 .7056 .0513 .uOSo .7_2q .3 u l u .n26 ) -.4 u 27 .7615 . 73 01 .1507 .8 3 5 7 -.3203 .7179 .7047 •97o5 -.IOI_ .?_l_ .o3 0 1 . 0 5 0 2 -.3n26 .7055 .7239 .1507 1. C O00 -. 3 201 .717g . 7 04 6 •1035 -.l_e_ .7%42 .6 o 5U .3742 -.3722 .707 5 .7207 .150_ 1.1660 -. 3 061 .72 0 7 .70 0 3 .19)6 -.3i3_ .7i92 .7 0 2o .0q97 -.360_ .76@7 .7164 °4_4 .170_ -.56_4 .bb84 .7810 • ? 004 -.3970 .702c; .7 2 83 .149 5 -.37 Z I .7576 .7 2 67 .4_84 .3368 -.5 8 43 .6652 .7858 •_5_6 -.47u_, .5_ .7_OS .19 9 _ -.3770 .7 0 _b .7_22 .4484 .502 8 -.5933 ._634 .7886 •_a -.511_ .6 ( 9_ ._o34 .2490 -,37 2 J .767e .7 2 07 .4983 1.0007 -.5975 .b626 .7899 .343 2 -.5551 . b 7il . 7 7o9 .2QQ4 - .3_ U 2 .7059 .723 2 °4_ 8 4 i.I067 -- .5606 .66 88 .7804 •_#46 -.00_ .& 6 10 .7Q14 .3481 -.3_63 .7047 . 7 250 . 7 950 .1 7 05 -.050_ . 7 704 ._218 . 4 420 -._153 .6;91 • 2993 .397 6 -.342 9 .7034 .7271 .7450 .3375 -.0473 .7723 .6188 •4_83 -.592 2 .h_ 3 7 .7 8£2 . 4467 -. 3 84 3 . 70 51 .7244 . 7 952 .5027 -.0427 .77 3 2 .617_ .5 4 %& -.526Q . 0 76 7 .7o82 .4 9 72 -.3h3 3 . 7 C93 . 7 180 .7952 .834 7 -.0426 . 7 733 . 6 1 73 .596 2 -.4235 .6wbq . 7 371 .545 2 - .30 7 2 . 7 205 . 7 0 06 . 7 952 l.O)OS -.6457 , 77 27 .6183 •6467 -.3265 .710o . 7 0o7 .5953 -.2522 .7 3 19 .683b .7952 1.10 6 7 -.0536 .7711 .6208 .5_57 -. 22 _ .7 3 b0 .o764 .644_ -.lqZq . 7 433 .0650 . 7 4&I -.1337 .7551 . 5 40_ .694 4 -.12 9 3 . 7 560 ._44 Q .7952 -.04 2 _ . 7 734 .517i .7442 - .0655 .7647 .b24_ .q457 .04 99 .791_ .58 7 4 .7879 -.00o 7 . 7 81 b . b 038 .90)& .13o_ .S u _,_ .5 5 8o ._444 .O b I 7 ,7 9 41 .5_35 TAB LE 4 .- C o n t i nue d .

T E_T 148 P T 20.2922 P S I CN .23 10 CDI .00 7 5 1 C O CORI . 0 0 7 59 _UN 13 T T 1 54.62 7 8 K CM - .0 3 2 1 C02 , 007 85 C D COR2 ,0 07 96 P_IN T 4 RC b . O0 7 Z MI L LION CC .0 03 4 CD 3 . 00 699 CDCDR 3 . 007 12 MAC H . 6 05 5 CD4 . 0 0 73 5 C DCOR4 . 0 0 7 4 6 A L PHA 1 .01_ 3 DEG CD5 . 00 665 COCOR5 . 00 6 70 J PPER SURFACE LOWER SURFACE SPANWISE X / C CP P_L / PT HLOC X / C CP P , L / PT MLOC X / C Y / C CP PpL / PT MLOC 0.00 3 0 1. 07 0 0 .9_46 . O _ b 3 0 .00 0 0 1. 07 0 0 .9948 . 08 6 3 .15 08 .1 7 02 - .525 0 .6 733 . 7735 • 0244 -.1504 . 7 48_ . 6 36 3 .0 1 29 .0 77 8 . 7 9 4_ .582 3 . 1 508 .50 33 -.54 7 0 .668 8 . 7 60 3 .051 3 - . 308 4 . 71 5 9 . 7 0 6 1 .026 3 .024 0 .7B41 .5 q 98 .150 7 .8 3 3 7 - . 53 69 .6 7 0 9 . 777 2 .9 7 5 5 - . 3 8 13 . 7 _22 . 7 289 .0502 -. 0 54 7 .7 6 81 .6256 . 1 5 07 1 .0 0 0 0 - .5 3 95 . 6 7 0 3 . 77 80 .I035 - .445 4 .6_ 9 3 . 74 _ . 07 42 - .09 7 8 .75 9 4 .639 5 .1508 1.166 0 - .52 0 2 .6 7 4 3 . 77 20 .1506 -.5 3 79 .6 7 0 7 . 777 5 . 0 9 9 7 - . 1 2_4 . 7 5 3 2 .649 3 .4984 .1 7 0 8 - .6518 .64 77 . 81 28 ._0 34 - .59 6 _ . 6595 . 7 9_7 .14 q 5 - .16 7 9 .745 3 .66 1 9 .4984 .3 3 68 - .68 0 6 .6419 .821 7 ._5 3 0 - . o 506 .64_ 0 .9 1 24 .19 9 6 -.2110 . 7 366 .6 7 55 .4 9 84 . 5 02@ - .6925 .6 3 95 .82 54 . 79 88 -._127 . 6 7 57 . 7 69 7 .24 q 0 - .22_5 . 733 0 . 6 8 1 0 . 4 98 3 1. 00 0 7 - .6 7 95 . 6 4 21 . 8 21 3 .3492 - . 7 019 . 0 3 7 6 ._2d3 .2 q9 _ - .25 3 2 . 7 281 . 6 888 .4_84 1.166 7 -.64 77 . 6485 .81 1 5 . 3 9 8 6 - .7 3 60 .6307 ._389 . 3 481 -.272 7 .7241 . 6 949 .7930 . 1 7 0 5 - . 0 9 0 5 . 7 6 09 .6 37 2 .447 9 -.73 1 9 .fi3i_ ._ 3 76 . 3 q 7 6 -.290_ . 7 205 . 7 00 6 .7950 . 337 5 -.0 7 48 . 7 640 . 6 321 .6 q 83 - ._94 .640 1 .8264 .44 6 7 - .2 9 56 . 71 95 .7 0 2i .7952 .5 0 2 7 - .06 7 4 .7655 .629 7 . 5 4 5 6 - . b 055 .65 7i .798 4 .49 7 2 - .2_ 7 2 .7212 .6995 .7 9 3 2 .8 3 4 7 - . 0 666 .7637 .62 9 5 • 5q 6 2 -.487 4 .6808 .7020 .5452 -.2405 .7306 .6848 .7952 1.0008 -.0734 .7643 .6317 .6457 -.3760 . 7 0 3 3 .7272 .5953 -.1960 .73 9 6 .6708 .7952 1.1667 -.0905 .760 9 .6372 .69_7 -.2 6 7 2 .7232 .6932 .6442 -.1463 .7496 .6550 .7451 -. 1 6 33 .7462 . 6 604 .6944 -.0 9 12 .7607 .6374 .7952 - . 0 6 oi .7o5_ .62 9 3 .7442 - . 03 4 7 . 77 2 1 . 6 1 9 2 .84 57 . 0 290 . 7 _50 .5 9 64 . 7 8 7 _ .02 3 4 . 7 8 3 8 .60 0 2 .q0 0 6 . I173 . 8 02_ .5 6 90 . B 444 . 0 804 . 7 95 3 .5814 TABLE 4 .- Continued.

TEST 145 _T 2C.2_10 uS[ CN .3_ 77 CDI .00766 CD C ORI . 0077 2 _' I _ 1 3 IT 154._78 K CM -,(:343 CD2 . 00 742 CDCCR2 °0 07 52 PQINT 5 _C 5.97 7 8 M]LIIO_ CC -.0023 CD3 .006 6 5 CDCOR3 ,006 7 5 _ACH .601Q CD4 .00 7 45 CDCOR k .0 07 54 _ L #H_ 2.02 7 9 OFG CD5 .00666 CDCO_5 ,00669 ,JPPER 31JRFaCE L_ER SURF A CE SP&NWISE _IC CP P,L I PT MLJC XIC CP P_L / PI MLOC X l C Y I C CP P_L I PT MLOC O.O00n .w6_H .g 7 52 .ic_5 9.09n0 .9 6 _8 ._752 .1895 .150_ ,1 7 02 -, 6 350 .65 7 2 , 7 981 .q_%4 -.3_54 . 7 0h7 . 7 220 .012_ . 3 160 ,_45U .4G4 q .1508 .50 33 -.6 53 8 .65 3 5 .803 q .051_ -.48_9 .0_02 .7530 .0260 .20gO ._247 .5319 .1507 ,8 3 57 -. 6 620 .65 1 9 , 8 06 3 .0 7 65 -.535 7 . 6 7 6_ . 7 o 7 9 .0502 .C_o .8 5 07 . 57 24 .1 5 0 7 ],OO O 0 -.6546 , 0 5 3 3 ,8 0 42 .1005 -.5856 . ht ) T u .7o3 1 .0 7 _2 .6263 . 7 884 .59 L d .150_ 1.1660 -.6 3 20 . 6 578 , 7 9 7 2 .1506 -.o530 .o ) 37 .803 6 .0997 -.01 7 8 . 7 796 .6071 ,498_ ,1708 -.673 7 , 6 496 .8 C gg .?004 -.flg4b .O&5_ ._i 6 3 .14q5 -.0_15 .7o 7 0 .6274 ,4 q 84 .33 6 _ -,715Q .6412 ,8228 ._500 -. 7 365 ._371 ._2 9 1 .1990 -,1 3 0 0 ,7574 .6427 .4984 .5028 -.7282 ,6388 ,_265 .2g@8 -.74o : .6352 .8320 . 2 4g0 -.ib7b ,7519 .6514 .4983 1.0007 -, 7 11g .6420 .8216 .34)2 -.765 7 ,63i3 ,6380 . 2qg4 -.18gO . 7 457 . t 613 .4984 1,1667 -,6691 . 6 505 ,8085 ._9_6 -.7917 ._2o2 ._459 .3481 -.2138 .7407 . h 6QO .7950 ,1705 -,i008 ,7632 ,6335 .447 q -.7787 . 6 2C7 ,d4lg .3 q 75 -.23d 0 . 7 35Q .67o5 .7 9 50 ,3 3 75 -.0840 ,7665 ,6282 .&gq_ -.7277 ._3_6 . : _264 .4467 -.2464 .7343 .6791 .7_52 ,5027 -,0768 ,767g ,625g .5406 -.6347 .6573 ,7_dO .4072 -.2434 .734_ .67 @ 2 .7952 ,8347 -,0774 .7678 .6261 .5qo2 -.509v .6_20 .7 b OO .545_ -.2052 .7425 .6063 .7952 l.O00S -.0876 ,7658 ,6293 .6457 - . 5 934 . 7 051 .7244 .595_ -.IC6 O . 7 502 . 6 540 ,7952 1.166 7 -.i194 . 7 595 .6 3 94 .695 7 -.280_ .7275 . b bg7 .644_ -.1216 . 7 5g0 . 6 401 . 7 4 61 -.1 7 3_ . 7 48 7 .05 5 5 .6944 -.0712 ,7690 . 0 241 .795 7 -.0747 , 7 bOB . 5 252 .7442 -.0193 .77 q 3 .60 7 5 ._457 .0213 .7_7q .5044 .7H79 ,0352 .7901 .5 89 q .g036 .i047 .8)39 .9671 ,_444 .GE8Q . 9 00 U .5 7 24 Jz_ bo • • • o TABL E 4 . - C ontinued.

TEST 148 PT 20.2)31 P SI CN .4614 CO L .00 773 CDCORI • 0077 g PUN 13 I T 154.o550 K CM - .0 3 64 CD_ . 0073 8 CDCOR2 . 007 4 g o O I N T 6 RC 5.965 3 MI L LION CC -.01 0 8 C O 3 . 00 713 CDCOR 3 .0 07 24 MACH .Sggg CD4 . 007 8 5 CD COR4 .0 07 9 6 ALPHA 3 .0141 DFG CD5 .00 7 31 CDCOR5. .00 7 34 J PPER SURFACE LOWER SURFAC E SPANWISE X I C CP P , L I PT MLQC X I C CP P , L I PI MLOC X / C Y I C C P PpL I P T MLOC 0.0000 .801 3 .9_2 3 .2925 0. 0 0 0 0 .801 3 ,9423 .2925 .150 % .1 7 02 -, 7 49 3 ,6 3 59 ,8 30 q .0244 - .6429 ._6g , 7 98_ .0129 .51_8 , d8 6 5 .41 8 4 .150_ .5033 -, 7 718 .6 3 14 .83 7 8 . 0 51 3 - , 07 8 3 .6499 .8 093 . 0 260 . 371 4 ._5 7 4 ,4 7 4 0 . 1 5 07 .8 3 5 7 - , 7 796 ,6299 . 8 4 0 2 .0 75 5 -.6945 .6467 .8144 ,0502 .212 3 ,8259 .5298 . 1 50 7 1.0000 -. 77 06 .6 3 16 ,8 37 5 .i005 -. 7 281 .o_OI . d 2_5 .0 7 42 .i 3 _2 .8105 •556 1 .i508 1.1 o 60 -. 7 426 ,63 7 2 ,82 8 9 .150 6 -, 77 1i , 6 31 0 ,_3 7 6 .Ogg 7 ,0 77 8 . 7 9 93 ,5 7 48 ,4984 .i 7 0B - , 70 16 . 6 45 3 .8164 ._094 -• 7 949 ,6269 ,8 4 48 ,1496 - ,0060 .782_ .60 1 9 . 4 98_ , 33 6 6 - . 7 50 3 .6 3 5 7 ,8312 .2590 - ,8222 ._215 .8531 .igg b -,055g , 7 729 .6 17 9 .4984 ,5028 - , 7 620 ,6 33 4 ,8 3 48 ._9_8 -.81 7 8 . 0 223 .8518 .2 4 90 - ,0919 , 7 6 58 , 6 293 .498 3 1.000 7 -. 74 1g ,6 37 3 .828 7 .34Q2 -•8283 .0203 •8550 .2904 -.12_3 .7586 .6407 .4Q84 i.i 0 67 -.6872 .6482 .8121 ,3986 -.B454 ,o169 .8602 .3481 -,15 7 1 .7529 .6 k 98 , 7 950 ,1 7 05 -,I161 , 7 610 ,6 3 69 .44 7 9 - .822 7 .o2 1 g .8533 . 3 9 7 6 - .Id6 7 . 7 4 7 1 .65g0 . 7 95 0 . 3 3 7 5 - , 0 9 33 , 76 55 .629 7 .4q_3 -, 7 015 ._335 .8 3 4 7 .446 7 -.1 9 8 7 .7447 ,6628 ,7952 .502 7 -.0 83 8 . 7 6 7 4 .6267 .5456 - ,66 0 _ .65 3 4 , d O40 .4 972 - ,200g .744 3 ,6635 , 7 _ 5 2 ,834 7 - , 0 84 3 .76 73 .62 6 g ,596 2 -,52gi ,6794 .7641 . 5 452 -,165g .7506 .65 3 5 ,7952 1. 0 0 0 8 -,0974 ,7647 .6 310 ,6457 -._0 7 6 , 7 034 . 7 2 7 1 .5g53 -.1353 . 7 5 7 2 .64 3 0 ,7952 1.1667 -.1468 ,7550 ,6466 .695 7 - .2912 , 7 264 .6914 ,6442 -.0948 .7652 ,0302 ,746I -,i816 .7480 •6575 .6944 -.0487 .7743 .6156 . 7q 52 -.0811 . ? oTg ,6259 ,7442 -.0007 ,7838 .6002 , 845 7 .O l b 2 . 7 8 70 ,5951 . 7 8 7 _ . 04 95 .79 37 ,5840 , q0 06 .OgSO .8u2 7 .5 6 gi .844 @ ,Og_g .80 37 .56 7 5 L ;q

TABLE 4- Continued

TEST 14_ PT 2 5 .3£ 9 9 PSI CN .JTLO CDI .00800 CDCORI .00805 eU_ 1 3 TT 1_4.0_42 K C_ -. 0 383 CD_ o00 777 CDCOR2 .00 7 8 7 _I_T 7 _KC ).9_3 MILLIO_ CC -.GZ2G CD3 .007 4 6 COCOR3 .00758 '4ACH .bOl T CD4 . 00 7 46 CDCDR4 .00756 ALPHA 4 . 0327 D E G CD 5 .00760 CDCOR5 .00 7 63 J_ P ER SURFACE LO a FR SURFACE SPA_WISE Y lr CP P,L / P[ _LJC X I C CP P , L I PT MLUC X I C Y I C CP P , L I PT MLOC £.) 9 33 .5 5 7v ._v 5 7 .3 9 9_ (;.0000 ._6 79 ,_ 9 57 .3q9 5 .150_ o1702 -. 8 80q .6082 .873 6 •024_ -.g k Ol ._;6 5 ._919 .012_ .6_16 .9182 .351 1 .150_ . 5 03 3 - ._044 .60 3 6 .6_0 9 .0513 - ,_ q 91 ,604o ,37_2 ,0269 . 5 140 .68 50 ,4214 ,1 5 0 7 . 83 57 - .9013 , 6 042 ,8799 •07 55 -.d 7 7_ .oJS_ .d727 . 050_ .3323 .548_ .4_93 .1507 1.0000 - .3869 .607 1 .87 55 •1035 -.og21 .6_6U ._7 7 1 ,0742 ,2&0 3 ,8 30 7 ,5210 ,lJO0 i. I660 --.8 5 37 .61 36 ,86 5 3 .[506 -._0_ . u 034 ._12 .0 q 9 7 ,1 73 5 ,8174 ,D44 3 .4984 .1708 -.72 5 2 .6 3 91 ,82 5 9 •?004 - .g0 6 7 .D52_ .oe20 .1496 ,G709 .7g71 . 5 75 5 ,4 q 84 . 3 368 -.7861 .6271 .8445 .2500 - .9213 .6002 .8_61 .l_Ob .01 5 5 . 7 _61 . 5 0b 9 .4_84 . 5 028 -.80 2 1 .6 7 3 9 .849 5 •_ q _ -, 7 [_I . b _O_ . 52 3 2 .Z4QO -,0291 . 7 772 . r i O9 .4_83 1.0007 - .7_1 3 .6280 .8431 • 3 4_Z -,gOll .t)42 ,B7Q£ . / gg4 -.0721 .76_7 ,6246 ,4 q 84 1 .1667 - .7203 .0401 .824 5 . 3 9q6 -.9063 ._028 ._21 ._481 -.1062 .7_19 ._ 3 U 9 .7_ 5 0 ,170 5 -.1478 .7 5 37 .6486 ,4_79 -,073_ .6097 .8714 .3976 -.1%09 .7 5 9 1 .0464 .7950 .3_75 -.1099 .76 1 Z .6366 ,498_ -.601_ . 62 40 ._49 3 ,446 7 - . 1 5 S2 .7 5 1 6 . 6 918 . 7q 5 _ , 5 027 --,0904 .7 5 3 9 .6 3 24 •5456 -.69ib .t45_ .@i67 .4972 -.1658 . 7 501 ._ 5 42 .7_5Z .8347 --.0948 .764Z .6319 •_962 -,5531 ,673i .? 7 37 .545_ -. 1380 . 7 5 5 _ . 645 5 . 7 _ 5 2 1 .00 0 8 -.I09 7 . 7 6 1 2 .6 3 66 ,6457 -.4269 .6983 .734W ,5953 -.lOgl .7t14 ,_364 .7 q 52 1,1667 -,i_80 ,7496 .6551 • 69 57 -.3 0 62 ,7223 ,6979 .644_ -.0727 .70_0 ._Z48 • 7 4_] - . 1 9 4 2 .74_5 . 6 631 .6 q 44 -.0 3 0 2 . 7 7 7 0 . b i 12 .7952 -.0924 . 7 t 4 7 ,531 1 , 7 442 ,0145 ,7059 " ; 5 969 ._457 ,0035 . 7 _37 .600 4 .7_7_ .G_03 .7_ 5 0 .5SI_ •903_: .b80_' . 7 990 .D 7 92 ,8444 .i073 .504 3 .5_o5 j J . a • o TAB LE4 -.- C o n tinu e d.

TE S T 14 8 P T 2 0 . 3 216 PS I CN . 6 76 1 C D 1 , 00907 CDCOR1 . 009 1_ R UN 1 3 TT 1 5 4o 0597 K CM - , 03g9 CD 2 . 008 6 2 CDCOR2 , 00 8 7 4 POINT 8 RC 5 , g q 57 MI L LIDN CC -.034 8 CD 3 . 00 8 3 9 CDCOR 3 . 0 0 85 2 _ACH .60 3 0 CD 4 ,0 0 8 0 6 CDCOR4 , 008 1 6 ALPHA 5 ,0100 DEG CD 5 ,0 08 02 CDC D R 5 °00804 J P PE R S U R FAC E LOWER _ U R F ACE S P ANWI SE X I C C P P , L I PT _LOC w / ¢ CP P , L I P T MLOC X I C Y I C CP P , L I PT MLOC 0.0000 ,310_ .84 3 0 ,4 9 99 0.0_00 .3108 ,84 3 0 . %g g g .15 0 8 .17 0 2 -,9 9 1 7 . 5 823 , 9 140 .0244 - I.2 7 65 ,52 53 1. 00 4 9 . O 12 g .8120 .g4_4 ; ,28 9 7 . 150 8 . 5033 -I, 03 8 2 , 573 0 ,g286 • 05 1 3 -I,1 203 , 5 5 8o .954 6 .0 2 6 0 .6 3 2 3 , g07 4 . 3751 . 1507 ,8 357 -1. 033 4 . 57 40 .9271 .0755 -i.0554 .5696 .g341 ,0502 .44 06 . 8 6 g0 ,_22 . 1 5 07 1 , 0 0 00 -1.0 1 43 . 577 8 . 9 211 .I095 -I.0543 , 569 8 .9 33 7 ,074_ ,33 97 ,8488 ,4 8 9 5 ,1508 l,l bb O -, 977 6 ,5852 , q 0 9 b ,1506 -1.03 0 9 .5 73 3 , 9 28 2 .O qg ? , 2 66 7 ,8342 .5154 .4 9 84 .1 7 08 -. 7 405 .6 3 26 ,8360 ,20 0 4 -1.0166 .5 7 73 , g 218 ,1496 .1482 . 8 105 ,5561 ,4984 ,3368 -,8112 ,6185 .8578 ._500 -I,0125 .5782 .9205 .1995 .0876 ,7984 . 5 763 ,4984 .5028 -,8317 .6144 ,8641 .2g_R -,g748 . 5 85 7 . 9 0 4 7 .2490 .0362 .7881 .5932 .4983 1,0007 -.8070 .6193 .8565 .3492 -, g 62 7 . 5 681 . gO 4 g .2 gg 4 - . 0134 , 7 7 8 2 , b O g 4 .4 9 84 1,16 6 7 -, 7 3 5 0 , 6337 ,8343 ,9 9 86 - ,9 59 h ,58 87 . g 040 ,34 8 1 -.0530 , 77 02 ,6222 .7 95 0 ,1 7 0 5 -.1 70 6 . 7 467 .6 596 .447 q -.91 3 3 .5980 ,8895 .3975 -.o g 02 . 7 628 ,6341 ,7 9 50 ,3375 -,1210 .7 5 66 .6439 ,4 9 8 3 -.8299 ,614 7 ,8636 ,446 7 -.I149 . 7 5 7 8 ,642 0 ,7 9 5 2 ,502 7 -,1051 ,7598 ,638 g ,54 6 6 -.7119 .6383 ,8272 ,4q72 -,1280 ,7552 ._462 ,7952 .8347 -,1034 .7601 ,6983 ,5 9 62 - .56_4 .6671 , 7 830 .54 5 2 -.i0 3 1 , 7 6 0 2 .6382 ,7 95 2 1 . 000 8 -,1196 , 75 69 ,64 35 ,6457 -.4372 .6933 .742 0 .595] -.0789 ,7650 .6305 .7952 1.1667 -.1930 ,7422 .6667 ,6957 -.31 3 6 ,7180 ,7044 .6442 -,0482 . 7 712 ,6206 ,7 4 6 1 -. 2 00 7 . 7 40 7 .6691 . 6 9 44 -,0105 . 7 78 7 . 60 85 . 7 952 -,I001 .7608 .63 7 3 , 7 442 ,0305 , 7 66g ,5951 ,8457 -,007 5 .7 7 93 .6075 , 7 87g ,07 3 1 . 7 955 . 5 811 .gO06 .0619 , 7 932 , 5 848 , B 444 .i165 ,8042 . 5 66 7 U-I TABLE 4 .- Continued .

TESt 14_ PT 2 u .3ZI8 oS[ CN .78 3 2 CDI .O102 g COCORI . 0 1036 o , I _ 13 TT 154._16 K CM - .0382 CDZ .00 q 62 COCOR2 .009 73 _]INT O RC 5.g_19 MILLIOI CC -.0542 CD3 .00942 CDCOR3 ,00954 i_Cd . b )09 CD_ .0 0 8Q 3 CDCOR4 .oo go l aLPHA o. £ 25_ DrG CD5 .00880 CDCOR5 . 00 8 7 8 ]_PER SURFAC_ LOWER SURFACE SP A NWISE W l C CP P , L I )I HL{]C x / C C P P _ L I P[ M LQC X I C Y I C CP P , L / PT M L OC 0. 0 0 3 0 .012_ .7 : _)_ ._ q 7 6 0 .0 3 00 .0129 . 7 654 .5970 .1508 .1 7 02 - I.120H ,5604 ,9486 .0_44 -l._ u 2 . 3 _3_ 1.2353 .0129 .q085 . qt B 2 .2 3 1g .150_ .50 33- i.1731 .5500 . g 651 .9513 -l.2_Z U .52a4 . q vgq .02 h 0 .733 0 . 9 285 .3272 .1507 .8 3 57 -1.1751 ,54W e . 9 65 7 .0 7 55 -1.2439 .53 0 0 ._79 .0_07 . 5 34 8 .38g0 .4133 ,15u7 1.0000 -1.15 3 6 ,55 3 g . g 58g - .100% -1.232E .53 : _2 .g b k l .0 7 4_ , 4 275 .8o77 .45 4 7 ,1508 1.1660 -I.Ii00 .5624 , 9 4 53 1506 -I.1740 ,54_6 ,9 5 54 .3 q g7 .34gi .@5_2 .4835 .4_84 .1708 -.7558 ,632g ,8 35 6 _5 ; 10 -I. ± 014 .Sb4 Z .9425 .1996 .15 3 6 .81 3 4 .5512 .4 9 84 .5028 -.85 3 7 .61 3 4 .8656 ? '_ g _ -].u4bl .D 7 54 .9246 .2490 .09 5 5 ._] 0 20 .5703 .4 9 8 3 1,0007 -. £ 320 .6177 .858g 3 4Q 2 -I.02u5 .5 1 _03 .glTZ .2_94 ,0416 .7911 .58_3 .4 9 84 1,16 0 7 -, 75 8 5 ,6 3 2 3 ,8 3 64 30 86 -1.005o .5333 .9125 .3481 -.0622 . 7 824 . 8 025 .7 9 50 .1705 - .1887 .7454 ,6 5 16 _004 -1.125 = .559] . g SOl .14 g 5 . 2 326 .d290 .5244 ,4 9 8 k . 33 68 -._ 3 2 0 ,6177 .858 9 44 7 Q - . g 47 5 .SV_R .6944 . 39 75 - .046 g . 7 736 .61o8 ,7 9 5 0 . 3 3 7 5 -.1 3 01 , 7 5 7 1 . 8 4 3 2 •498 3 - .u5_5 .613_ ._O b l .446 7 - .0705 . 7 68g .6246 .7 9 52 ,5 0 27 -.I121 .7 o 06 .6375 .5466 -. T i 6 t ._:$_ 3 .32 73 .4 97 2 - .0884 . 7 _53 .6300 . 79 52 .8 3 4 7 -.II07 . 7 60 q ,6 37 1 .5 9 52 -.976D .6_81 .7515 .5452 - .0739 . 7 o82 .6254 ,7 9 52 1.0 0 08 -,1295 . 7 5 7 2 ,6430 .6457 -.44 3 _ .n_4_ . 7 40 Z .595 3 -.0545 . 77 21 .6192 .7 9 52 1.1067 -.211 q .7408 .668 9 ._957 - .3172 . 7 1_9 .7Oi J .644_ -.0235 .77 7 2 .blOg . 7 461 --. ? 042 . 7 4 Z 5 .0 5 65 .694 % .C042 . 7 63 7 . 6 G04 .7g5 7 -,IUO2 .7olo .5357 . 7 447 .0414 . 7 911 : .5883 .qG57 -.0193 . 7 7Q I . h OT g . 7 87 g .07 97 . 7 _6 7 .5 7 58 . q 09_ ,0402 .7NOg .56_7 .8444 .I190 ,_065 ,562_ J: r • i I i TABL E 4 .- Continued.

TEST 148 P T 20. 3 200 P Sl CN ,89 3 4 CDI ,01222 C OCORI .0 1 2 31 _U N 1 3 T T 154. 0 4 9 2 K CM - ,0 3 6 2 CD? ,0111 9 CDC D R2 °01132 POINT I0 RC 5,9 77 9 MI L LION CC -,0 7 4 3 CD3 , 0 1110 CDCOR 3 ,01125 MACH .6005 CD4 .01045 CDCOR4 ,01055 A L PHA 7 .0312 DEG C05 .01019 CDCO R 5 . 0 1 0 1 8 JPPER SUR F ACE L OWER S U R F ACE SPANWISE X I C CP P , L I PT MLnC X I C CP P , L I PT MLOC X I C Y I C CP P , L I PT MLOC 0.0000 -,23 6 9 . 7 3 6 8 . 6 7 52 0.0000 - .2 3 6 9 . 7 3 6 8 , 6 7 52 . 1 508 ,1 7 02 - 1 .2 3 05 ,5401 .9809 , 0 244 - 5,3 7 6 7 . 313 _ 1.402 4 , O 12q .9 7 62 . 97 6 8 . 1 8 3 4 . 1 508 ,503 3 -1 .25 6 8 ,5 3 49 , 9 89 3 .051 3 - 2.20 6 2 . 3 4 7 1 1.328 9 ,026 0 .8094 .94 3 8 ,28 8 6 .150 7 .8 3 5 7 - 1 .2482 , 53 66 .9866 .0 7 6 5 -1.715Q ,4441 1.1426 .0 5 02 .6 0 9 4 .9042 . 3 819 .1 5 07 1 . 000 0 -1.22 7 3 , 5 408 ,9 7 99 .I005 -I,19 6 4 .54 6 9 ,qTOl .0742 .498 6 ,882 3 .426 7 .150_ 1.1660 -i,2048 ,5452 .9728 ,1506 -1.2543 .5354 .9885 ,0997 .4153 ,8658 ,4583 ,4984 .1708 -,7712 ,6310 ,8384 .20 0 4 -1 .2214 .5_l q .9 7 80 . 1 4 q 5 .29 13 .84 13 .50 30 ,4984 . 33 68 -,8 5 5 3 ,6 1 44 .8641 .25 0 0 -I.187g ,54_0 .9674 ,Iggb °2065 °6245 °5323 °4984 ,5028 -o8811 ,6093 ,8720 .2 q 88 -1.0273 o5803 .9171 .2490 .1431 .8120 ,5536 ,4983 1,0007 -.8571 ,6140 ,8647 .3492 -l.O_Ib .5 6 q6 .9341 ,2994 ,0838 ,8002 ,5733 .4984 1,1667 -.7832 .6286 .8421 . 3 986 -1,0570 .5745 .9263 ,3481 ,0360 .7908 .5889 ,7950 .1705 --o2237 ,73 9 4 ,6711 .44 79 -,987 7 ,5 d 82 , g O4g .39 7 6 -, 0 098 . 78 1 7 .60 37 .7950 ,33 7 5 -.1484 ,7543 o647 7 •49 8 3 -,8835 ,608_ .H728 ,4467 -.0421 .7753 ,6140 ,7952 .5027 -.1284 .7582 . 6 414 ,5466 -, 7 503 .6352 .8320 ,4972 -.0645 . 77 09 ,6212 , 7 _5 2 .8 3 4 7 -.1 2 45 , 7 590 . 6 4 0 1 .5962 -.593i .6663 .7843 .5452 -.0501 .7737 .6166 ,795_ 1.0008 -.I465 .7546 .6471 . 6457 - . 45 3 9 . 69 3 _ . 7 419 .5953 -,0354 . 77 66 . 6 119 .7952 1.166 7 -.22 7 0 . 73 8 7 .6 7 22 .6957 -.32 6 0 ,7_91 .7027 ,6443 -.0138 ,7809 .60_0 .7451 -,2143 .7412 .6682 ,6944 ,0148 ,7866 .5958 . 7q 52 -.1212 . 7 59 7 . 6 391 . 7 442 .04 7 9 , 7 931 ,5850 .8457 -,042 7 . 77 52 ,6142 .78 7 9 .0824 . 7 ggg .5 737 . q 096 .0046 .784o ,5990 ,844_ .I182 .8070 .S b lg ", 4 TABLE 4 .- Continued.

T EST 14B PT 20 . 3210 PSI CN . _ 9 23 CD [ .0 1 528 COCORI . 0 1524 RUN 13 IT _5_.6Z_1 K CM -.e30_ CO2 .01419 CDCOR2 .01428 Pi]l _T Ii _C 5.9 q 56 MILIlO_ CC -.0_2_ C03 .01426 COCO R 3 .01436 _ACH .6J27 CD4 .0 1 326 CDCOR4 .01 333 ALP rI A _.UZ3Q DF_ C D5 .0 13 0 3 CDCOR5 .0 12 99 'lPF E R SURFACE L O_ER SURFACE SPA N WISF _ I C CP P,L / PT MLJC _ / C CP P , L Z PT MLOC X I C Y / C CP P , L / PT MLOC 0.0910 - .4_V_ .6 q T b .73o2 O.Ou O 0 - .41 9 2 .69 7 5 . 7 3_2 . 1 508 .1702 - I.12 1 9 .5571 .g5 3 6 .0244 -2.551u .271o 1.5029 .012_ 1.0227 .9856 .143g .1508 .5033 -i.ig75 .5420 .977g .0513 -2.4473 .2 q 23 _.45 1 4 .0260 ._o8 0 .9547 .256i .I} 0 7 .8 3 57 -1. 30 45 . 5 2 0 6 1 .0 1 26 .0755 -2.3217 .317q 1.3932 . 0 502 .o740 .g 1 59 .3503 . 1 5 07 1.0000 -1.1782 .5459 .9717 .I005 -2.23ol . 3 34 i 1.3565 .074_ .5015 .6935 ,4043 . 1 506 i.i660 -1. 0 667 ,568 1 .9 3 6 3 .1596 -1.34_ .511_ 1.027i .0 9 97 .4757 .8 7 03 .4383 .4984 .170_ -.7445 .6 3 25 .8 3 6 1 ._034 -I.0_9_ .5_44 .9422 .1495 , 3 4 7 6 .B507 .4861 .4984 . 33 68 -.6550 .6104 .8 7 02 .2500 -1.1543 .5 5 0o .904_ .iOg6 ,25 5 9 . e 3 30 .5175 ,4gS& , 5 028 - .8915 ,60 3 2 .8B15 . 2 oqR -1.1222 .5_70 .953W .24 0 0 .1917 .8196 .5407 .4983 1.0007 -.8 6 64 ,6082 ,8738 •B492 -I,0967 .5o2 2 .g458 .2994 .12_g . 8 0 7 0 .951g .4q84 1.1667 -. 7 858 ,624 3 ,8489 .Bgq6 -1.0 7 2_ .5o 7 1 .93_0 .B481 .0782 . 7 gog .5788 .7950 .1705 -.2 9 6 3 ,7221 ,6981 .44 7 q - ] .00 0 0 .D8 1 5 .9 1 53 oBq7b .0 3 0o ,7574 .5944 .7950 .3375 -o 1 724 ,7468 , 6 594 .49q 3 -.8V30 .602_ .8820 .4467 -.0079 .7797 .6069 .7_52 ,5027 -,1403 ,7532 ,6493 .5456 -,7 h 15 .o291 .8414 .4Q72 -.0B47 .7743 ,6156 .7952 .8347 -,1303 ,7552 ,6461 .So_ ? -.0070 .0000 .7w3g .5452 -.0208 ,7771 ._IIi .7952 1,0008 -.1549 .7503 ,65B9 .6457 -,_651 ._677 ,75[ 2 .5 q 53 -.0099 . 7 793 .6070 . 7 952 1.1667 -.2574 . 7 298 ,6861 .6_5 7 -.3403 .7133 . 7 118 ,6442 .00 7 8 , 7 82_ .o018 .7451 -.22 h b .7300 .0764 .6944 .0324 .7878 .5938 .795 ? -,1297 .755_ .045_ .744Z ,0o24 ,7937 ._40 ._457 -.0457 .712 Z .bl_l .TST q .0938 .SO00 .5736 ._0_6 .00_3 .7_3 1 .001 3 .8444 . I Z59 .8066 .56 2 o x :: oo TABLE 4.- Continued.

148 PT PS I eN .1389 .00752

TEST 20.3247 COl .00745 COCORl RUlli 154.5309 K -.0284 .00148 .00759 13 TT CM CO2 COCOR2 POP-IT 12 RC 6.0209 CC .0057 CD3 .00690 CDC DR3 .00701 "'ILLIO~ rUCH .0053 CD4 .00725 CDCDR4 .00736 ALPHA CD5 .00615 .00680 .0102 OEG COCOR5 JPPER LOWER SPAIIIWISE SURF AC E SURFACE XI':. CP P,lIPT MLOC X/C CP P,LlPT MlOC X/C Y/C CP P,l/PT MlDC 0.0000 1.1007 O.OOOu 0.0000 1.0011 1.1007 1.0011 0.0000 .1508 .1702 -.4065 .6986 .7346 .:>244 .0542 .7910 .5884 .012Q -.1976 .7405 .6694 .1508 .5033 -.4257 .6947 .7405 .0513 -.1431 .7')14 .6521 .0260 -.1655 .7469 .6592 .1507 .8357 -.4143 .6910 .7310 .6801 -.2037 .6954 .7394 .01':15 -.2318 .7336 .0502 .7393 .6113 .1507 1.0000 -.4221 .1005 -..:l083 .71&3 .7041 .0142 -.2242 .7352 .6777 .1508 1.1660 -.4052 .6988 .7341 .1506 -.414ti .6969 .7371 .0997 -.2371 .7325 .6820 .4984 .7948 .1708 -.6016 .6594 .2004 .149':1 -.2659 .7268 .6908 .8014 -.4860 .6325 .7594 .4984 .3368 -.6230 .6551 .2500 -.5503 .6697 .7190 .1996 -.2850 .7230 .6968 .4984 .5028 -.6334 .6530 .8046 .2988 -.5815 .6634 .7886 .2490 -.2916 .6989 .8048 .7216 .4983 1.0001 -.6341 .6529 .3492 -.6184 .6560 .8000 .2994 -.3082 .1183 .1040 .4984 1.1667 -.5980 ".6601 .7937 .3986 -.b5tj7 .6479 .8124 .3481 -.3214 .7156 .7081 .7950 .1105 -.0656 .7670 .6214 .4479 -.6628 .6471 .13136 .3976 -.3350 .7129 .7124 .7950 .3375 -.0538 .7694 .6236 .'.9133 -.6307 .6536 .8038 .4467 -.33.20 .7135 .7115 .7952 .5027 -.0480 .7705 .6217 .5466 -.5564 .6685 .7809 .4972 -.3180 .7163 .7011 .1952 .a341 -.0474 .7706 .6215 .7476 .5452 -.2677 .5962 -.4487 .6901 .7264 .6914 .7952 1.0008 -.0510 .1699 .6227 -.3440 .7152 .5953 -.2182 .6758 .7952 1.1667 -.0614 ."457 .7111 .7364 .7678 .6260 .6Q57 -.2409 .7318 .6830 .6442 -.1641 .7472 .6588 .7461 -.1414 .751 il .0510 .6944 -.1048 .7591 .6399 .7952 -.0474 .1706 .6215 .7442 -.0449 .7712 .6207 .u4,o .0167 .8451 .7d93 .5913 .787'1 .7835 .6007 .9006 .1341 .8071 .5618 .8444 .0760 .7954 .5d12 TABLE 4 . - Continued .

TEST 148 PT 35.2668 PSI CN .i35g COl .00 7 2 7 CDCORI .00 7 35 RUN &3 TT 120.1061 K CM -.0283 C02 .00 7 04 C DCOR2 .00 7 1 6 POINT 3 PC 15.0280 MILLION CC . 0 0 5 2 CD3 ,00702 CDCOR3 , 0 0 7 16 MACH .6045 CD4 .OObgI CDCOR4 .00704 ALPHA .0204 DEG C05 .00687 CDCDR5 .006 9 2 UPPER SUR F ACE L OWEQ SURFACE SPANWISE X I C CP P_L I PT ML_C x I C CP P, l l PT MLQC X l C Y I C C P P_L I PT M L OC 0.0000 1.0 9 9 5 1.0008 O.OOO0 0.0000 1.0g g 5 1.090_ 0.0000 .1508 .1702 -.3878 .7025 .72 9 3 .0244 .0742 .7952 .5_23 .OI2Q -,2032 .7395 .6716 ,150B .5033 -,4160 .696g .7380 . 0 51 3 -.125 3 .7552 .64 7 0 .0260 -.1656 . 7 4 7 1 .659B .15 0 7 .8 3 57 -.4 1 28 .6975 .7 3 7 0 .0 7 65 -.2227 . 7 356 ,67 7 8 .0502 -.204g .7392 ,6 7 2Z ,1507 1.0000 -.4068 . 6 98 7 , 73 52 .I005 -.3035 .7194 ,703i .0742 -.2243 .7353 ._783 .I508 1,1 6 60 -,3881 ,7024 ,7294 .i506 -.4133 .6974 .7372 .Ogg7 -.2382 .7325 .6826 ,4984 .1708 -.5990 ,6 6 01 ,7945 •2004 -.4858 .6128 .759 6 .14g b -,2700 .72 6 1 .6926 .4984 . 3 368 -.6276 .6 5 44 . 803 4 •2500 -,5501 ._ h g9 , 77 g5 .1996 - .2868 ,7228 . 6 979 .4994 .5028 -.6324 , 6 5 3 4 ,8048 .2088 -.5_3i .6633 .7896 .24g0 -.2934 .7214 .6ggg .4983 1.0007 -,6250 , 6 549 .8025 •3492 -,6210 .6557 .8013 .2994 -,307i .7187 .7042 .4984 1.166 7 -,6070 .6585 .7970 • 3 Q_6 -,_5Q8 .64 7 9 .81 33 . 3 4SI - , 3231 , 7 155 . 7 092 . 7 95 0 .1 7 05 -, 0 7 1 8 , 7 659 .6 2 98 ,447g -.6613 .6476 . 8 1 3 8 . 3 976 -. 3 4 13 .7118 .7148 .7950 . 33 75 -. 0 588 .768 5 ,6257 •4983 -.6327 ,6534 ,804g .4467 -,336e .712 7 . 7 135 , 7 952 .50 27 -.0499 , 77 03 , 62 28 .5&_6 -.56 3 5 , 6 _7 3 . 7 8 3 6 .&g 7 2 -,3226 ,7156 . 70 90 . 7 9 5 2 ._34 7 -.0470 ,7 7 09 .6219 •5g02 - .4 530 .6_94 , 7 495 , 9 452 -,2 7 22 . 7 2 5 7 ,6933 , 7 952 1,0 00 8 -,053 6 , 7 6 9 5 , 6 240 ,6457 -. 3 462 ,7109 ,7164 . 5 953 -,2247 .7 3 52 , 5 784 ,7952 1,1667 -,0 5 86 ,76 85 , 6 2 5 6 .6957 -.2448 ,7312 ,6847 .6442 -.1679 ,7466 ,6605 .7461 -o1471 .7508 ,6539 .6944 -o112 1 .7578 ,642 8 ,795 ? - .046g , 7 705 . h 225 , 7 442 - .0494 .7 70 4 .6226 .8457 .0437 .78gi .5923 .787g .0122 .7827 ,6027 .90 3 6 .I320 .8068 .5630 .8444 .0740 ,795I .5823 C D TABL E 4 .- C ontinued.

TES T 14 8 P T 3 5 . 2 057 PS I C N .0 2 8 7 C 01 , 00723 COC OR1 . 00729 R UN 43 TT 119 , 8 7 00 K C M - . 02 58 C D 2 , 007 0 8 CDC O RZ ,0 0718 P OINT 4 PC 15.0 6 8 6 MILLI B N CC . 0066 C03 .007 01 CDC O R 3 ° 007 14 M A CH ,6 057 CD 6 = 00 696 CDCOR 4 , 00708 AL PHA -. 99 7 9 OEG CD5 , 00 6 9 8 COC O R5 = 00702 UPPER SURF A C E LOW ER SURFACE S PA N WI SE X / C CP P _L / PT HLO C X l C CP P ; L I PT MLO C X l C Y I C CP P _L I PT H LO C 0 o0 000 1 .0 9 1 6 ,9992 .03 33 0 ,0000 1, 0 9 1 6 ,9992 ,0 333 , 15 0 8 , 1 7 0 2 -* 2 9 36 . 7 2 1 3 , 7002 ,024 4 ,2487 , 83 01 , 5 2 3 2 , 01 29 - , 53 94 , 671 9 , 7766 ,1 508 , 503 3 -, 309 7 , 71 8 0 , 7052 .051 3 .0 2 3 9 .78 5 0 .5 9 9 0 .026 0 - .38 8 0 .7023 , 7 296 . 1 50 7 . 8 357 - .30 6 0 .7188 .70 41 • 0 7 6 5 - , 0 89 9 . 7 6 2 1 .63 5 8 . 050 2 - .3 7 33 . 7053 . 7250 .1 50 7 1 . 0000 - .3 0 1 8 ,7196 .70 28 ,1 00 5 - .1 80 4 .744 0 , 6647 .07 4 2 -. 36 42 . 707 1 , 7222 .1 508 1 ,16 60 -.2 85 1 .72 30 .6 9 76 , 1 5 06 -. 30 6 6 o 71 8 7 . 70 4 3 , 09 97 - , 35 9 3 , 708 1 , 7207 ,4984 ,17 0 8 -, 5 6 02 ,66 7 8 ,7 8 28 , 2 004 -, 3 q 07 ,7 0 18 , 73 04 , 1 496 -, 3 678 ,7 0 64 , 7 2 3 3 ,49 8 6 = 33 6 8 -, 58 2 3 ,66 33 ,789 6 , 2 500 -,4643 ,6870 ,75 3 2 ,1996 -. 3 695 ,7060 , 723 9 ,4984 ,5028 -,5 853 ,662 7 , 7 9 0 6 , 29 88 - . 50 6 5 .6 785 . 7 66 3 .249 0 - , 3 648 . 7070 , 7 224 °49 83 i .0 00 7 -= 5 78 0 ,6662 ,7 883 . 3 492 -,5 5 14 .66 9 5 , 7 8 01 .2994 -. 3 69 7 . 70 6 0 , 7 2 3 9 .49 8 4 1 . 1 66 7 -.5622 ,6 6 7 4 , 783 6 , 3 986 - .5 962 . 6 50 5 . 7 939 , 3 48 1 - . 3 79 0 , 70 4 1 ,7 2 68 .79 50 , 1 7 05 -, 0551 . 7 691 .6 2 4 7 ,44 7 9 -,60 5 4 ,6 5 87 , 79 6 8 , 3 9 7 6 -, 3912 ,7 01 7 ,7 30 6 ,795 0 , 3 37 5 -,06 5 6 ,7 7 1 0 ,6 2 16 , 4983 -,5851 ,6 6 28 ° 7 90 5 ,646 7 -,3809 , 7 038 * 7 274 , 7 9 5 2 ,5 02 7 -,03 7 9 , 7 726 , 6 19 1 .546 6 -. 5 25 5 ,6747 .7 7 21 . 49 7 2 -, 3 6 0 5 ,70 7 8 . 7211 .7 952 =8 3 67 -. 0 348 ,77 3 2 =61 8 1 • 5 9 62 -,4 22 7 .69 5 4 ,74 0 3 , 5 45 2 -. 30 4 1 . 7 19 2 .7 035 ,79 52 1 . 0008 -, 0 6 0 7 , 7 7 20 ,62 00 . 6 4 5 7 -,3 22 1 ,71 55 ,7091 • 59 53 -. 2 495 . 7 301 . 6 8 6 6 ,79 52 1,16 5 7 -,0661 , 77 13 , 6 211 . 5 9 5 7 -.2259 . 7 348 ,6 7 90 .6442 -,18 9 5 .74 22 ,667 5 .7461 -.13 22 . 7 536 ,6694 ,6 9 44 -.1 2 9 5 .7 5 4 2 ,648 5 .79 5 2 - , 0371 ,7 727 . 6 189 *7 44 2 - ,0 633 .7675 , 6273 ,845 7 ,0531 , 7 908 ,5894 , 7 _ 7 9 , 0 01 5 ,7 80 9 , 6 06 3 ,9006 ,1401 ,8 0 83 , 9 6 0 5 ,8444 , 066 0 ,7 93 4 ,58 5 2 U3 F -= TA B LE 4 . - Continued.

TEST 148 PT 35 .206_ PSI CN .Z4 7 8 CD1 .C0 7 3 2 CDC O RI . 0 0 7 4 0 RU_ 4 3 TT IIO . 7 8 7 6 K CM - .0 3 1 3 CD 2 . 00 7 0 2 CDCOR 2 .00 7 13 POINT 5 RC 15.0492 _ILLION CC .0035 CD3 .00708 CDCOR3 ° 007 2 3 MACH .60 3 8 CD4 .00 7 01 CDCOR% .00 7 14 ALPHA 1.0285 DEG CD5 .0069 9 CDCOR5 .00 7 0 3 UPPFR SURFACF LDWE_ SURFACE S PANWISE £ 1 C CP P , L I PT MLO C X I C CP P , L I PT MLOC X I C Y I C CP P , L I PT MLO C 0•0000 1.070g .995 4 .0_17 O•OO O O 1.0709 . 9 954 .0817 .1508 .170 2 -. 4 958 ° 6 8 3 6 .7585 .0244 - .123 3 . 7 57 0 .642 7 .0129 .0929 ._009 .5729 .1508 . 5 033 -.5308 .6768 .768 9 .0513 -.2946 .7238 .6_63 .02 5 0 .0470 .7917 .51_0 .1507 •8357 -.52 9 0 .67?2 .7684 . 0 7 65 - . 3 6Q9 . 70 8A , 7 1_6 ,0 5 02 - .0446 • 77 35 ,6176 , 150 7 1• 0000 -.5217 ,6 7 86 ,7 66 1 • i00 5 -,4 3 _4 ,6 9 52 , 7 406 ,0742 - ,0885 , 76 48 ,6 3 16 ,15 0 8 1.1660 - , 5 026 , 6 824 , 7603 ,1506 - .52_5 ,6773 ,7682 ,0997 - .11 93 •7 5 87 ,6414 •49F4 ,1708 - ,6 3 63 ,6 55 8 ,80 1 2 ,2 0 06 - , 5 569 ,665 7 . 7 86 1 , 1 496 -.1 717 .7482 .b 5 79 .4984 •3 3 68 - •6 70 4 ,64 91 , 8 116 • 25 0 0 -•6404 . 6 550 •8024 ,1996 - ,2020 , 7 4 2 2 .66 7 4 •49_4 .5 02 8 - ,6769 .64 7 8 ,81 3 6 •2988 - .6627 . 6 5 0 6 .80 q 2 .2490 -.2193 .7 3 88 .6729 .4g_ 3 1.00 0 7 - .6686 .6494 . 8 11 1 • 3 492 - , 6 91Q , 6 448 ,8 1 82 •2 q 94 - .2407 ,7 3 4 5 . 6 795 ,4984 1.1 6 67 - , 6 4 6 5 , 6 53 8 , 80%3 . 3 9 86 - •72 3 4 ,6 3 R5 ,8278 • 3 4ai - ,262g ,7 3 01 •686 5 • 7 9 5 0 , 1 70 5 - ,08 53 ,76 5 4 ,6 3 06 , 4 479 - .7 1 60 •6400 .8256 , 3 9 76 -•2867 . 72 5 4 .69 3 8 .7 9 5 0 . 3 37 5 - .070 1 , 7 6 8 4 ,6 258 •4g8 3 1 .677 9 ,6476 .8139 .4467 - ,287 5 .7252 .6 9 4 1 ,7952 ,5027 - . 0 608 .77 03 ,6228 .5466 - .5_gg •663 1 . 7 900 ._ 97 2 - . 279 1 . 7 269 .6915 . 7q5 2 .8 3 4 7 - . 05 8 3 . 7708 , 6220 •5962 - .4_ 1 1 .68 6 7 . 7 537 . 54 52 - .2 35 6 . 7355 .6 779 . 795 2 1 . 000 8 - .06 6 7 . 7 6 91 .6 2 47 ,6457 - ,3685 ,70g l ,7 1 9 1 , 5 9 53 - .l q3 6 .74 30 ,6648 ,79 5 2 1, 1 667 - ,07 53 ,7 6 74 , 62 74 ,6Q 5 7 - ,2622 , 730 Z ,6962 ,644Z -,1422 •75 4 1 .64 8 7 •74 6 1 -,16 0 7 .7 50 4 .654 5 •6944 -,O glO •764 3 .6 3 25 , 7 9 52 -,05 q 7 •7705 ,6225 .7442 - .0325 . 77 5 9 ,6137 ,8457 .0351 ,7894 ,591g .7879 ,0256 .7875 ,5 0 50 ,g006 ,12 2 6 ,8068 .5630 •8444 .0842 ,7991 •5758 L 7 1 D,O TAB LE 4 .- C ontinued.

TEST 148 PT 3 5 , 2244 PS I C N , 3588 CD Z , 007 4 9 C DCO R 1 , 007 5 6 RUN 43 TT I1 9 . 75 1 9 K C M - , 0350 CD2 , 0 0 71 1 C DCOR2 , 00720 POIN T 6 RC 1 5 , 035 5 MILLION CC -, 0 012 CD 3 ,00 7 21 CDCOR 3 , 0 0 7 3 4 MACH ,602 3 CD4 ,00 7 10 CDGOR4 ,00 7 22 ALPHA 2,31 6 2 DEC CD5 .00712 CDCORS. , 0 0 7 15 UPPER SURFACE LOWER SURFA C E SPANWIS E X I C C P P _L I PT M L OC X l C C P P _ L I P T M L OC X / C Y / C CP P p L / PT M L O C 0 . 0000 , 97 2 8 , 9 7 59 ,18 70 0 , 000 0 ° 9728 ° 9759 . 1870 ,1 508 , 1702 -, 6130 . 6 6 1 1 , 7930 , 0 244 - , 333 1 ,7 1 6 7 , 7073 , 0 1 29 , 3 2 72 , 847 B ,4 92 0 , 150 8 , 5033 - , 6506 , 6537 , 80 4 5 . 0513 - ,4 73 6 , 6 8 8 B , 75 0 5 . 0250 . 2263 , 8277 . 5273 . 1507 . 8357 - . 6458 . 654 6 , 8031 . 0765 - . 5240 .67 88 .7659 , 050 2 , 0983 . 80 2 3 °5704 ,1 507 1 . 0000 - , 636 1 , 6565 . 8001 . i005 - . 5 77 0 ,668 3 . 7 821 ,07 4 2 . 03 41 , 7896 , 5915 , 1 5 08 1 , 16 6 0 - ,6 131 ,6 611 , 7931 ,15 0 6 -,64 7 6 ,6 5 4 3 ,8 03 6 ,099 7 -, 01 0 6 , 7 8 0 7 ,6 0 6 0 ,4 98 4 , 170 8 - ,6 755 , 64 8 7 ,81 2 1 . 20 04 - .69 0 8 ,64 57 ,8168 ,149 5 - ,07 55 ,76 7 8 ,6 268 ,4 9 84 . 33 68 -.71 60 .64 07 , 82 4 5 • 25 00 -.73 2 9 ,6 3 73 .82 9 6 ,199 6 -.12 30 . 758 4 , 6 4 1 8 ,49 8 4 ,5 0 28 -, 72 48 , 6 389 , 82 7 2 ,2988 -,7446 ,6 350 ,8 33 2 , 2 49 0 - , 150 4 ,7 5 2 9 , 6 505 ,498 3 1 , 0007 -, 7 1 00 ,6419 , 822 7 , 3 49 2 -, 7 6 4 6 , 63 1 0 ,8 3 93 , 29 94 - .1788 ,747 3 ,6 5 9 4 ,4984 1 , 1 667 -,6 7 9 8 ,6 4 79 , 813 4 , 3 985 - , 7 8 q i , 6 262 .8459 , 3 481 -,2 0 69 ,74 1 7 .66 8 2 ,79 50 ,17 05 -, 10 95 ,76 11 , 6 3 76 ,4479 -,77 3 7 ,62 9 2 .8421 ,3976 -,234 3 ,7 3 63 ,6767 ,79 5 0 , 33 7 5 -,0868 ,76 5 6 ,6 3 04 •498 3 -,72 3 9 ,6 3 91 ,8269 ,4467 -,24 3 9 ,7 3 44 ,67 9 7 ,79 5 2 , 5 027 -,07 53 ,7579 ,6267 , 5 466 -,6 3 86 ,6 5 60 ,8008 ,4972 -,2411 .73 50 ,6788 ,79 5 2 .8 3 47 -.0712 .768 7 ,62 5 4 . 5 962 -. 5 121 ,6812 .7622 , 5 4 5 2 -,1999 ,74 3 1 ,6660 ,7 95 2 1,0008 -,0812 ,7667 ,6286 ,6457 -, 3 9 3 5 ,7 0 47 ,7259 .59 53 - ,16 33 ,7 50 4 ,6 5 45 ,79 52 1,1667 -, i 0 00 ,7 6 30 , 63 46 , 6 9 5 7 -, 2 8 25 , 72 6 7 , 6 917 , 6442 - ,i1 6 8 , 7 59 6 ,6 3 99 , 7 4 6 1 -,1 7 73 ,747 6 ,6 5 8 9 ,694 4 - , 070 1 ,7 69 9 , 6250 ,7 9 5 2 - ,073 7 , 7 6 82 ,6 262 , 7 4 42 -,01 5 6 , 779 7 ,6076 . 8 4 57 . 023 2 , 7 874 ,5 950 . 7 8 79 . 03 91 ,7 90 6 . 5 8 99 , 9 006 , 111 7 , 8050 , 5 5 6 0 , 8 444 ° 0 944 , 80 1 5 , 5717 u1 LN TABLE 4 - Continued.

TE ST 149 PT 35.2442 P SI C N ,4688 C DI . 0077 9 C DC O R I . 007 86 RUN 43 TT 119.8299 K C M - .0 377 C D2 .00 7 32 CD C O R2 .00 7 4 2 POINT 7 RC 1 5 .0270 MILLInN CC -.OOg5 CD3 .OC T k b C D COR 3 ,0 07 6 0 MAC H ,6022 CD4 ,00 73 1 CD C ORk ,00 7 4 2 ALPHA 3.0243 DEG C D5 .00 72 4 CDCDR5 .0 072 5 UPPE_ SURFACF LO_ER SUQF_CE SPANWISE Y / C CP P , L I PT MLOC X I C Cp P,L f PT MLOC X I C Y I C CP P_L I PT MLOC 0,0000 .80fi4 .9425 ,2925 O.OOO0 ,8054 ,9425 ,2925 ,1508 ,1702 -.7367 ,6355 ,83Z5 .0244 -.5n58 .6 6 55 . 73 0 3 . O12g .5234 .B863 ,4192 ,1508 .50 3 3 -, 77 85 ,6271 ,8454 • 0513 -,6712 ,0485 ,8125 .02 5 0 .3827 ,8583 ,4 7 28 .150 7 ,8 3 5 7 -. 773 4 ,6281 ,84 3 8 , 07 65 - .6 93 2 .6441 ,8 1 92 .0502 .2296 .82 7 _ .5272 . 15 07 1 .00 00 - ,7 618 ,6 30 4 , 8 40 3 .I005 -, 7 292 .636g ,_303 .0 7 42 .1494 .SIig .5544 .i508 i. I660 -. 73 6 7 .6355 .8325 .1506 - .7744 .627g .844I .0997 .G927 ,8006 .57 33 .4984 .1708 - .706g ,6414 . 8 2 3 4 ,2004 - . 7 996 , 6 229 .85 1 9 .1496 . 0 026 , 7 826 .602_ .4 9 84 , 33 6 8 -, 7 58 0 ,6 3 12 , 8391 ,2500 -.828 6 ,6172 ,8608 ,Igg6 -.0 4 6 0 .7730 ,61_5 ,4984 ,5028 -,7695 ,6289 ,8426 •2988 -,8266 .61 7 5 .66C2 .24g0 -°0 % 2 3 .7657 ,6 30 1 ,49 8 3 I .GOOT - ,75 30 ,6 3 22 , 83 7 5 . 3 492 -.2369 .6155 .863 3 .29 9 4 -. I I75 .7587 .6413 .4g84 1. 1 667 -.7122 .640 3 . 8 250 • 3 986 -.85 3 2 .6122 .8684 . 3 48i -.1512 .7520 .6520 .7g50 . 1 705 -.i 3 51 .7552 ,6469 ,447g -.62 7 g .61 7 3 ,8606 .3 97 6 -,1835 . 7 456 .6621 . 7 950 .33 7 5 -.1030 ,7616 ,6367 ,4983 -.?680 .6292 ,8422 .4467 -.1984 .7426 ,6668 ,7952 ,5027 -. 0 882 .7645 ,6320 .5466 -,6732 ,6481 .8131 ,4Q 7 2 -.2010 . 7 42i ,66 7 6 ,7952 . 83 4 7 -, 0831 , 7 656 ,6 30 4 .5962 - .5 3 98 .6 7 4 7 . 7 722 .5 k 52 -. 1 655 . 7 k 92 ,6565 . 7 952 1. 0 008 - , 0 94 7 .76 33 .6 3%1 .6457 -.4156 .69 9 4 , 7 34i .5953 -.1 3 41 . 7 554 .6466 . 7 952 1.1667 -.1251 . 7 5 7 2 .643 7 .6957 -,29 9 9 ,7224 ,6984 ,644Z -.0 9 26 ,7537 .6334 .7461 -,Ig13 ,7440 .6646 ,69 k 4 -.0504 .7721 .619g . 7 952 -.0853 , 7 051 , 6 311 ,7442 .0001 . 7 821 ,6036 ,845 7 .0130 ,7867 ,5995 ,787_ .050g .7922 .5871 .gO06 ,1011 ,8022 ,570 6 .8444 .I0 3 0 .8026 .569g t;1 J_ TAB L E 4 .- Continued.

TES T 1 48 PT 3 5 . 32 6 0 P SI C N . 5 777 CD1 . 0 080 9 CDC O R Z .00 81 8 R U N 43 T T 1 2 0 . 07 9 6 K C M - . 03 9 2 CD2 . 0076 6 CD C OR2 .00778 POINT 8 P C 1 5 .0 0 16 MI LL ION CC -. 0207 C D 3 , 0 0 7 74 CD C OR 3 .00 7 91 MA CH . 601 4 CD4 . 00753 C DCO R 4 , 00767 AL P HA 4,0381 DEG C D 5 ,00 7 47 CDCOR 5 ,007 5 1 U P PE R S U R F ACE LOW E R SU R F AC E S P A N WIS E X / C C P P , L I P T M L OC X l C CP P , L I P T M L O C X I C Y I C CP P , L I PT MLO C 0 . 0 0 00 .572 3 . 8 96 5 .3 g 8 5 0 . 0000 " .5723 .8965 .3 985 .1 5 0 8 .170 2 -.8 6 50 . 6 1 1 3 .8698 .0244 - .8 7 9 5 .608 5 .8742 .0129 .6882 .9 1 9 5 .348 6 .1 50 8 . 5033 - .9 0 9 3 .6 025 . 883 4 . 05 1 3 - .8 9 01 . 6 0 6 3 . 87 75 .026 0 . 5 2 17 . 8 865 . 41 89 .1 507 . 8357 -.9 078 .6 0 2 8 . 88 3 0 . 0 76 5 -. 8757 .6 0 92 .8 73 1 . 0 5 0 2 .3521 . 85 28 .4 8 29 .15 07 1.0 0 0 0 -.8933 . 6 057 . 8 7 85 • 1005 -.893 8 ° 6056 . 87 8 7 .0 7 42 . 2 5 70 .83 3 9 . 5 165 .1 508 1. 1 6 6 0 - . 8 6 2 9 . 6 1 17 . 8 69 2 .1 50 6 - . q 07 2 . 6 03 0 .682 8 . 0 99 7 .19 01 .82 0 7 . 53 9 5 .4 9 84 . 1 7 08 -.72 8 2 .6 385 .82 7 9 . 2004 - .9106 . 6 0 23 .88 3 8 . 1 4 9 6 .0 9 10 . 8 0 10 .57 2 6 . 4 9 84 .33 6 8 - .7 907 . 6261 . 8 4 70 • 2 5 0 0 -.9 236 .5 997 .8 879 . 1 9 9 6 . 027 9 . 7885 . 5 9 33 . 4 9 84 . 5028 - . 8058 . 6 2 3 1 . 85 1 6 ,2988 - . 9056 ,6 0 33 ,_82 3 ,249 0 -, 0 1 6 2 , 77 9 7 .6 075 , 49 83 1, 0007 -, 787 5 ,62 6 7 , 8 46 0 • 3 4 9 2 -,9 05 1 ,6 03 4 , 88 21 ,2 9 94 - , 0580 , 771 4 , 6 2 10 ,4 98 4 1, 16 6 7 - , 73 4 9 " ,6 3 7 1 , 8 29 9 , 3 9 8 6 - , 9 1 2 2 ,6 0 2 0 ,884 3 , 3 48 1 - , 0 967 .76 38 ,6 333 ,79 5 0 .17 05 - , 1 6 2 4 , 75 07 ,6 5 4 0 .44 7 9 - . 87 64 .6 0 9 1 .8 733 . 3 9 7 6 - . 1351 . 75 6 1 .64 5 4 .79 50 . 3375 - . 117 2 ° 7597 . 63 9 8 •49 83 - . 807 1 ,6228 , 8 52 0 ,446 7 -,1529 ° 7 526 ,65 10 , 7 952 ,5 0 2 7 -, 0 9 8 6 . 7 6 3 4 ,6 339 . 5 466 - . 703 4 . 6 4 3 4 .820 3 .4972 - .16 0 9 .7 510 .6 535 . 7952 . 83 4 7 - . 0931 . 7 64 5 . 6321 • 5962 -. 5 6 18 .6 715 . 777 1 . 5 452 - . 1 331 . 7 56 5 . 64 4 8 .7952 1 .0 008 -. 1090 . 7 6 13 . 6 37 2 .645 7 - .4 3 22 .6 97 2 . 7375 .5953 - .1 07 0 . 7 61 7 .6 3 65 . 7 9 52 1 . 1 6 67 - . 155 1 . 7 52 2 .6 517 . 6 9 57 -.3132 .720_ . 70 09 . 6 442 -.069 8 . 7 691 .624 7 ,7461 - ,2020 , 7 429 .6664 .6944 - . 03 2 3 . 77 65 ,612 7 • 7 9 5 2 - , 0 942 , 7 64 3 ,6 3 2 5 , 7 442 , 0 146 , 7 8 58 , 5 9 7 6 , 845 7 , 004 9 ,7 83 9 , 6007 , 787 9 , 06 1 2 , 7 951 ,5 82 4 ,9 0 06 ,08 7 8 , 80 04 , 5737 ,8444 , ii 0 1 , 8 048 , 5663 t n t n TABLE 4 . - C ont i nue d .

TEST 148 PT 35.41 6 7 PSI CN .6893 CDI .00858 CDCORI .00865 RUN 43 TT 120.5 6 9 2 K CM -. 0 401 CD2 .007 9 6 CDCOR2 .00807 POINT q RC 15.0073 MILLION CC -.0356 CD3 .008 2 3 CDCOR3 .00838 MACH .5045 CD4 . 0 0 7 92 CDCOR4 . 0 0806 ALPHA 5.0352 DEG CO5 .00784 CDC O R5 .00787 U P PEP SURFACE LOWER SURFACE SPANWISE x l C CP P , L I PT MLOC x / C CP P , L I PT MLOC x I C Y I C CP P , L I PT MLOC 0.0000 .2 6 27 .8334 .5174 0.0000 .2627 .8334 .5174 .1508 .1702 -.g 9 75 .5813 . 9 166 .0244 -1.1882 .5431 .9 7 71 .01 2 Q .82 8 9 .94 6 7 .280g .150e .5033 -i.044 6 .5 7 1g . 9 314 ,0513 - 1.1243 .555g .9567 .0260 ,6542 .9118 , 3 659 ,150 7 ,8 3 5 7 - 1.04 6 4 .5715 , 9 320 •0 7 6 5 -i.0657 ,56 7 6 .9381 .0502 .4715 .8 7 52 .4 4 09 .1507 1,0000 -I.0289 .5750 .9265 •I005 - 1.0662 .5675 ,9 3 8Z .0742 . 3 670 .854 3 .48 01 . 1 508 1,166 0 - ,9927 , 5 822 ,glS l .1506 - 1.0422 .5 7 2 3 .93 0 7 .0997 .2920 .8 3 93 .5 07 1 .498 4 .1 70 8 -.7476 .6313 .8 3 89 •2004 - 1.0212 .5 7 6 5 ,9240 ,149 6 .1824 ,81 7 4 .5451 ,4984 ,3 3 68 -,R164 .61 7 5 .8 60 2 ,250D -1.0172 ,5 773 ,0228 .1996 ,II02 ._029 .569 4 ,4984 .5028 -.8 3 29 .6142 ,8653 .2988 -. 9 78 6 .5851 .gI07 .2490 .0598 .7928 .586i .4983 1.0007 -.8140 .6180 .8594 , 3 492 -.967 7 ,58 7 2 ,907 3 .299 4 ,0118 . 7 832 , 6 018 .4984 1.1 6 67 - , 7 5 3 4 ,6 30 1 , 8 4 0 7 . 3 986 -.9641 ,588 0 .9061 .3481 - ,0 3 12 . 77 46 .6158 . 7 950 .1 7 05 - .1684 ,7472 ,6596 .4479 -. q 154 ,5Q77 .8909 . 3 9 7 6 -,0 7 61 ,7656 .6 3 02 .7950 , 33 75 -, i1 47 .7579 ,6426 •4983 -._ 3 59 . 613 6 .86 6 2 .44 67 -, 0 Q 47 , 7 619 , 636 2 ° 7 952 , 50 27 -,0947 , 7 6 1 9 , 636 2 .5466 -.7210 .6366 .9307 .4972 -.1081 .7593 .6404 ,7952 .8347 -.0904 ,7628 ,6348 •5962 -.5712 ,6666 ,7846 , 5 452 - , 0 893 .7630 ,6 3 44 .7952 1.0008 -,1091 ,7590 ,6408 ,6457 -,43 5 9 .6Q 3 7 ,74 30 .5 q 5 3 - .0676 ,7674 .6275 ,7952 1, 16 6 7 -,170 1 ,7468 ,6601 , 6 957 -,312g .7183 ,704g .6442 -.0350 ,7739 ,6170 • 7 461 -.I q 88 . 7 411 .6592 .6_44 -.00 2 1 . 7 804 ,6064 , 7 952 -,O S g5 , 76 30 ,6345 . 7 442 .0413 ,7891 ,5922 ,R457 ,OOg8 ,7828 ,b025 .7879 .0842 .7977 ,5780 ,9006 ,0 8 89 ,7987 .5765 .8444 ,1295 ,80 6 8 ,5629 %Jl TA B L E4. - Continued.

TE ST 148 PT 35. 41 80 PSI CN , 8 035 C 01 .00943 CDCOR1 , 0 0 95 0 R UN 4 3 TT 1 2 0,5 42 4 K C M -.03 9 6 C D 2 ,00869 CD C OR 2 .00881 P OIN T i 0 RC 1 5. 0 2 7 6 MIL L ION CC - ,054 9 C D 3 ,00898 CD C O R3 , 00 9 14 MACH .6 0 54 C0 4 , 008 5 7 CDCO R4 , 0087 1 ALP HA 6 , 0 3 6 2 DEG CD 5 , 0084 6 COC O R 5 ,008 4 9 UPPER S U R F ACE . -- L OW E R S U R F ACE S P ANWIS E X / C CP P _ L / PT M L OC X I C CP P pL I PT ML OC X / C Y I C CP P tL I P T ML OC 0 . 0000 ,0 4 0 5 . 7 88 9 .5 9 2 5 0 . 000 0 , 0 405 . 7 889 . 5 9 25 . 1508 , 17 02 -1. 1 5 4 8 .5 4g 7 , 966 5 ,0244 -1. 9 8 46 , 3837 1 . 2 5 60 .0 1 29 ,9 1 24 ,9 6 34 ,2 31 5 , 1508 , 503 3 -1 ,2 0 1 0 ,54 05 , 98 14 . 0 5 1 3 - 1 .3 04 g .519 7 1 ,015 1 . 0260 , 7 41 7 ,9 29 3 ,32 57 , 1 50 7 .8 357 -1 ,199 3 . 5 4 0 8 ,9 808 •07 6 5 -1, 2 6 3 8 , 527 q 1 ,00 1 7 , 0 50 2 .553 4 ,8 91 6 ,4 0 86 .1507 1 ,000 0 - 1,1 7 6 7 , 5 4 53 ,973 6 ,1005 -1.2565 , 5294 ,999 3 ,0 7 42 ,44 3 0 ,869 5 ,4 519 , 1 50 8 1,166 0 - 1.13 5 6 . 55 3 6 . 9604 •1506 - i . 1 9 68 .5 4 13 . 980 0 ,099 7 , 3 6 1 8 . 8 5 33 . 4 8 2 0 . 4984 ,1 70 8 - , 78 6 7 , 6 2 3 4 ,8 511 .2004 - 1,1488 , 5 5 0 9 .9 6 4 6 .149 6 ,243 5 ,829 6 . 52 41 ,4984 , 3 3 6 8 - , 86 13 ,6 0 8 5 ,8 7 4 2 ,2 5 0 0 - I,12 57 , 55 56 ,95 7 2 ,1996 ,1641 ,81 37 , 5 513 ,49 8 4 ,50 2 8 - , 87 9 3 , 6 0 4 9 , 87 9 8 .2988 - i,0 66 8 , 5 674 .938 5 ,249 0 .10 7 6 ,8 0 24 , 57 0 3 ,498 3 1,0 0 07 -, 8 561 ,6 09 5 ,8 7 26 ,3492 - 1,0443 , 5718 ,9315 ,2994 ,0549 ,7918 ,58 78 ,49 8 4 1 , 1 667 -,784 3 , 6 2 3 9 . 8 504 . 3 98 6 - i.02 9 6 .5 7 48 . 9 2 6 8 . 3 48 1 .0 07 4 , 7 82 3 . 6033 , 7 950 ,1 70 5 - ,2 0 14 , 7 4 0 5 , 670 1 ,44 7 9 - , 9 681 ,58 71 ,9 07 5 , 3 9 7 6 - , 03 99 , 77 29 , 6 1 8 6 , 7 95 0 , 33 7 5 - ,1 380 , 7 5 3 2 , b 500 ,49 83 -,8 77 2 .605 3 ,8 7 92 ,44 67 - ,0 6 5 6 , 7 6 77 ,62 6 q , 7 952 ,502 7 - ,i154 , 7 5 77 , b 429 .5466 - . 7 545 ,6298 , 8 41 2 .49 7 2 -. 08 44 .76 39 . 6 3 30 . 7 952 . 8 347 - , i i 03 . 7588 , 6 4 1 2 ,596 2 - , 6 021 , 6 6 03 , 7 942 ,5452 - , 06 72 , 7674 , 6 2 7 4 , 7 952 1 . 0008 - ,1297 , 7 549 , 647 4 ,6457 - ,4622 ,688 4 , 7 511 ,595 3 - .05 0 2 , 770 8 ,62 20 ,7952 1. 166 7 - ,2 0 86 , 73 91 ,6 7 23 .695 7 - , 3 35 3 . 7137 , 7 11g , 64 42 - ,022 0 , 776 4 ,6129 , 7 461 - ,2192 , 737 0 ,6 7 5 7 ,6944 ,0 0 64 , 7 821 ,60 37 , 7 952 - ,10 9 7 , 7 58 9 ,6410 ,7442 , 0 461 ,7 901 ,59 07 .845 7 - .0118 ,7 7 85 ,6096 , 7 8 7 9 ,0848 , 7 9 7 8 .5 77 9 .90 0 6 ,0642 .79 3 7 ,584 7 ,8444 , 1 26 5 ,8 0 61 , 5 64 0 Lrl ,.., 4

TABLE 4 - C o nti n ued

TEST 148 D T 35.54 6 0 PSI CN .9156 CDI .01141 CDCDRI ,0114 3 PUN &3 TT 120.5794 K CM -.0 3 85 CD2 .OI0 3 g CDCOR2 .01049 POINT iI PC 15.0023 _ILLION CC -.0742 CD 3 .01076 CDCDR 3 .OlOgl _ACH .6014 C04 .01021 CDCOR4 .01032 ALPHA 7.0433 DEG CD5 .01004 CDCOR5 .01002 UPPFR SURFACE LDWER SUQFACE 5PANWISE X I C CP P , L I PT MLDC x I C CP P_L I PT MLOC X I C Y I C CP P,L I PT MLDC 0.0000 -.2104 .7416 .6684 0.0000 -.2104 .7416 .6 6 84 .1508 .1702 -1.2457 .53 6 5 .9878 . 0 244 - 2. 3 254 .3226 1.3827 .0129 .98 3 2 ,9781 .1784 .1508 .50 3 3 - 1.2657 .5 3 25 .9942 .0513 -2.2097 .3455 1.33 3 2 .0260 .8151 .9448 .2863 .1507 .8357 -1.2535 .5 3 5 0 .g903 .0 7 _5 - I.R05 5 .4256 1.1 7 59 . 0 502 .6251 .gO 7 1 .376 1 . 1 507 1.0 0 0 0 -1.2287 .5 3 9 9 .g824 •1005 -i.2705 .53I b . 9 q57 .0742 ,512 6 .8849 .4221 . 1 508 I.I 66 0 -1.2108 .54 3 4 . 9 767 •150 6 -1.25_2 .5 3 40 ._18 . 0 997 .427g ._ 6 Bl .4546 ,4984 . 1 709 - .7945 . 6 25g .847 3 . 2 004 -1.2 3 60 .5384 .9_47 .14Q6 . 3 025 .84 3 2 .5001 .4984 . 33 68 - .8822 ,60 8 5 ,8741 •2500 -1 . 2072 .544i .g755 .ig96 .21 73 .8264 .5297 .4984 .50 2 8 -.gO6g .6036 .881 7 ._9_ -1.1 3 85 .5577 ._538 .2490 .1553 .8141 .5507 .4983 1.0007 -.8825 .6085 .8 7 4 2 .3492 - 1.1050 .504_ .9433 .299 k .0981 .8 0 2 7 .569 7 .4984 1.1667 -.8143 .6220 . 8 5 33 • 3 986 -l. O _2& .5688 .9 3 62 , 3 481 .046 9 , 7 926 .586 5 . 7 g 5 0 . 1 7 0 5 - ,2 5 49 . 73 2 8 ,6822 .447g -1.0123 .5827 .9143 . 3 976 -. 0 0 0 7 .78 3 2 .b 0 2 0 .795 0 . 33 75 -.165 1 .7506 . 6 542 .4983 -.gO71 .60 3 6 .8818 .4 4 6 7 -.0 37 4 . 77 59 .6 13 8 .7952 .5027 -.1 3 62 .7563 .64 51 .5466 -.78 3 R .6280 .8440 .4972 -, 0 607 .7 7 13 ,5212 ,7952 .8 3 47 - ,1249 , 7586 ,64 16 • 5962 -.6225 .6600 ,7948 ,5452 -,0412 ,7751 ,61 50 .7952 1.0008 -,1465 ,754 3 ,6484 , b 457 -.4800 . 6 882 .7514 ,5953 -.0289 .7776 . 6 1Ii .7952 I.I b 67 -,2269 .7383 ,6735 .6 9 57 -.3515 .7137 .7120 .6442 -.0051 .7823 .6034 .7461 -.2352 .7367 .6761 .6944 .0188 .7870 .5957 .7952 -.I275 .7580 . 6 424 .7442 .0545 .7941 .5840 ,8457 -,0344 .7765 .6128 .7879 .0897 .80ii .5725 •gO06 .0356 .7g0 3 .5_02 . 8444 .1281 .8087 .55 9 8 k J '3 O0 • a _ l, TAB LE4 .- C o n tinued.

TES T 148 P T 35 , 5 4 5 6 P SI C N 1. 0 1 62 C D1 , 0 1 548 C D C OR1 , 01557 R U N 4 3 TT 1 20 , 53 9 3 K C M -, 030 1 CD 2 ° 0 141 3 C D C O R 2 . 01 4 33 POINT 12 RC 15.0294 MILLION CC -. 0 951 CD 3 , 0 1444 COCOR 3 , 01 4 7 1 MACH . 6 024 C _4 .01 3 82 C D C OR4 .0140 6 A LPH A 8,034 3 DEG CD 5 ,0 1377 CDCOR 5 . 013 8 1 UPPER S U R F AC E L OW E R S U R F A CE S P ANWIS E XI C CP P , L I PT MLO C X I C C P PpL I PT MLO C X I C Y I C C P PpL I PT MLO C 0. 000 0 -° 40 30 .7 02 7 .7 2 8 9 0. 0 00 0 - .40 3 0 . 70 2 7 . 728 9 . 1508 . 170 2 -1 .1 89 6 . 5 4 6 6 .97 16 , 0 244 - 2.52 5 6 ,2 813 1.4 7 9 1 .0129 1. 03 00 ,9 873 , 1355 , 150 8 . 5033 -1 . 4 10 4 , 50 2 7 1, 0 4 3 1 . 05 1 3 -2 .4 57 9 . 294 7 1,4466 .02 60 . 880 1 . 9 575 ,2 50 0 .1 507 , 8357 - 1 .49 53 ,4 85 9 1. 071 4 , 07 6 5 - 2. 3 4 0 9 . 3 1 80 1 . 3 9 30 . 05 02 . 6 q 38 .92 05 , 3 46 3 .1 507 1 . 0 000 -1.4 0 2 0 . 50 44 1 . 0 4 03 .10 05 - 2.259 3 o 33 41 1. 3 5 7 4 .0 7 42 . 5817 .89 83 , 3 949 , 1508 1 . 1 66 0 - 1. 2 12 7 , 5 420 .9 7 9 0 .1 5 06 - 1. 5 121 .4 8 25 1.0 77 0 .099 7 .49 5 0 .8 8 11 .4296 .4 q 84 .1 708 -. 77 6 2 . b 286 . 8 4 30 .2 00 4 -1.11 35 . 5 61 7 .94 7 6 .1406 . 3 644 . 8551 .4 78 6 .49 8 4 .3 3 68 - . 875 4 . 6 08 9 ° 87 3 5 ,2 500 - 1, 1577 , 55 2 9 , Q 6 15 , 1 99 b ,27 55 , 8375 , 51 0 3 ,49 8 4 , 5 028 - .9 03 8 , 6 033 , 88 22 •2 q 88 -I .1 3 4 7 . 5575 .9 5 42 .249 0 .2 0 9 9 .8244 . 5330 .4 983 1 . 0 0 07 - . 88 2 1 .6 07 6 . 875 5 . 3 492 - 1.1 13 0 . 5 61 8 .94 7 4 .2994 . 1 46 3 .81 1 8 ° 55 4 5 .4984 1 .1 6 6 7 -. 80 9 5 .622 0 . 853 2 •3986 -i, 0 88 7 , 5 666 , 9 3 98 , 3 48 1 , 0 948 ,8 01 6 , 571 6 , 7 9 5 0 ,1 70 5 -, 2 6 4 1 , 7303 , 68 6 1 ,44 7 9 - i , 0 1 3 6 . 5 81 5 . 9 163 . 3 9 7 b .04 0 4 ,79 08 , 58 9 5 , 7 9 50 . 33 7 5 -, 1 6 5 9 ,7498 , 65 54 ,49 8 3 -, 9 0 93 .6022 ,88 39 ,4467 , 0 07 1 ,7842 ,6 003 , 7 9 5 2 ,5 0 2 7 - ,132 5 , 75 64 ,6449 , 5 466 -, 7 794 ,6 2 8 0 ,844 0 .49 72 -, 0 2 00 . 7 788 ,6091 ,795 2 ,8 3 4 7 -.1224 , 75 84 ,6417 • 5 962 -,618 3 ,6600 .7948 , 5 4 5 2 - , 0 12 1 ,780 3 , 60 6 5 ,79 52 1 , 00 08 -,14 8 1 . 7 534 , 6 498 ,645 7 -,4750 ,6884 .751 0 .595 3 -, 0 0 35 , 78 2 1 ,6 03 7 , 7 952 1,1667 -,2485 , 7 3 3 4 ,68 12 ,6957 -, 3 4 6 2 ,714 0 , 71 1 5 , 6 442 , 0 1 6 4 , 7 8 b 0 ,5973 • 7 4 6 1 - ,2 30 1 , 737 1 ,6 755 , 6 944 . 036 6 , 7 90 0 ,59 0 8 , 7 9 5 2 -, 1 229 ,7 5 84 ,64 1 9 , 7 442 ,0691 ,7965 ,58 0 1 , 8 4 57 -. 0306 , 7767 . b 12 5 . 7 8 7 9 . i00 8 ,8028 , 56 9 7 ,9 0 06 .0346 , 7 896 ,5914 ,8444 .13 5 9 ,8097 ,5 5 80 tO TABLE 4.- Concluded.

TEST 14a PT 35.21 5 9 PSI CN .13 5 7 C91 .00 7 21 CDCDRI .00 730 RUN 43 TT 119 .7 319 K C_ -.0284 CD2 .00704 COCOR2 .0071 5 POINT 13 RC 15.0132 _ILLION CC .0061 CD3 .00 7 02 CDCOR3 .00 7 18 MACH .6011 C04 • 00 698 CDCOR4 . 00 7 1 2 ALPHA .0 00 0 DEG C D 5 .00698 CDCDR 5 , 0 070 5 LIPP r P SURF_C[ LDWE_ SURFACE SPANWISE X / 3 CP P , L / PT _LOC X / C C P P , L / PT MLOC X I C Y / C C P P , L / PT ML O C 0 .0030 1.097 7 1 .0009 0.0000 0.0000 1.0977 1.0009 0.0 0 00 .1508 . 1 702 - • 391 2 .7 0 7 0 .7224 ,0244 .0 7 g2 , 7 998 .5 7 46 ,0129 - .2 03 4 . 7 440 , 5 646 .15 0 8 •50 33 - .4 1 50 .7 0 2 3 •7297 .0513 -,125_ .75 9 3 .6403 .0260 - .1664 . 7 513 .05 3 0 .1507 •8 3 57 - .4119 .7029 ,7287 , 0705 -,2227 .74C2 ,6706 .9592 - .2052 ,7437 .6652 .15 0 7 1.0000 - .4 0 60 .7040 .726 9 ,i005 - . 3 041 , 7 242 .6_5 7 .0 7 42 - .22 3 8 . 7 400 .6 7 09 .1 5 08 1 . 1 66 0 - . 3 864 . 7 0 7 9 . 7 2 10 .1506 - .4123 .7028 .7289 .0 9 97 - .2 3 74 ,7 3 7 3 ,6 7 51 ,4 9 84 ,170B - ,59 1 7 ,667 4 ,7 83 4 .2004 - ,4840 .68@6 , 7 507 .1496 - .268 7 . 7 3 1 2 .684B ,4984 • 33 68 - . 6 222 , 66 1 4 ,7 9 27 ,25 0 0 - , 5 47B .6762 ,7609 .1996 - .2B53 ,7279 •68gQ ,4984 •5 0 28 - .6272 ,6604 ,7942 •2Q88 -.5_0_ ,6 6 95 ,780I .2490 -,2916 .7255 ,ogi9 .49Q3 1.0007 -.6200 .6618 ,7 9 20 , 3 492 -.617 4 ,5 6 2 3 ,7 q 12 .2g94 - . 3 080 ,72 3 4 .6969 .4984 1. 1 667 - .6 0 26 ,66 5 2 .7 8 67 • 3 986 -,6552 ,6548 .8027 . 3 481 - , 3 199 .7210 . 7 006 . 7 950 ,1705 - .0682 .7707 •6221 .44 7 9 - .656 3 .6546 .80 3 0 . 3 9 7 6 - • 33 8 1 . 7 175 ,7062 • 7 95 0 • 337 5 -. 0 57 0 ,7729 ,61 8 6 .498 3 - ,6281 ,6602 . 7 945 .4467 - . 333 1 ,7184 . 7 046 .7952 .502 7 -,0491 , 77 45 ,6160 ,5465 1 ,5601 ,67 3 6 ,77 38 ,6 q 72 -. 3 18 q .7212 .700 3 ,7952 .8 3 67 - .067 0 ,7749 ,6 1 5 6 ,5967 -.450 1 ,6953 , 7 404 .5452 - .2693 , 73 10 .6_50 , 7 952 1.0008 - .05 3 9 • 773 6 •6 17 6 .645 7 -, 3 441 .716 3 .7080 .595 3 - .2223 ,740 3 ,6 7 05 . 7 952 1.1667 -.0589 . 7 726 •6 19 2 •6957 -._4 3 4 ,736 1 ,6 7 70 .6442 -•1658 , 7 515 .6529 .7461 -,1463 ,755 3 .6 4 68 ,6944 -.ii06 . 7 624 ,6 3 55 .7952 -.0485 . 7 746 ,6158 ,7442 -.0481 .774 7 ,6157 •8457 .04 3 9 , 7 _26 ,5061 , 7 _ 7 9 •01 3 1 . 7 _68 ,5961 ,900 6 ,1309 ,_i00 , 5 576 ,8444 . 07 45 . 7 989 .5 7 6 2 O_ C D ' (a) Photograph.

9 . I 4 4 m & LN s e cti o n 0 . 7 62m-!

1 . 70 2m Tunnel onchor " (b) Schematic drawing.

Figure 1.- Elevation view of 0.3-m TCT with two-dimensional

testsectioninstalled.

i ._ :.'::_:.,.:::;': c~,:.:_:_ ;, ,_.

t~stseCtion of the Langley O.3-m TeT,

_ i _ f 1

20.17

+Y

_'_ L e ading Edg e

I J ! J

15.25

l ; _.

Figure 3.- Schemotic dro w ing of NACA 65 1 -213 model.

(All dimensions ere in centimeters.)

Tube Passage

Trailing Edge Section

Leading Edge Section

Figure 4.- Centerline section drawing showing model construction.

G Upper Surface

0.010

8 Lower Surface

o 8

o Elm~

___ -E-0._- @.- ~ --g~_....0_ --.,.--

ElEl ET Q . ElEJ El 0

Q 0 <:) Tolerance

Z meas. - Z design

o

() 20 40 60 80 0 1 00 Band

(em.)

~ Percent Chord

------------------------~-

-0.00

-0.010

Figure 5.- Difference between measured and design thickness

coordinates. Centerspan station.

0'1 U'1 0 • • •

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Figure 6 . - Range of Re y nolds number and Mach number u s ed in

test program .

o_ P 1.6 1.4 1.0 / Tr a nsition V J 0 Fixed d_ ( I" 3 Free Cn . 8 / . 6 / I --.2 - 4 0 4 8 1 2 1 6 20 .0 04 . 008 .0 12 . 0 1 6 . 02 0 . 024 - . 028 . 0 3 2 -.1 0 - . 05 0 _, deg ca C r .

• Figure 7.- Effect of fixing tr a nsition on aerodyn a mic characteristics of a irfoil at M = 0.22 a nd R c = , 3 x 10 6 1.6 1.4

" i

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-- .2 -4 0 4 8 12 16 20 .004 .008 .012 .016 . .020 .024 .028 .032 -.I0 -.05 0 a , deg cd cm Figure 8.- Effect of fixing transition on aerodynamic characteristics of oirfoil at M = 0.22 and R c = 6 x 10 6 1 . 6 r 1 . 0 .. Transi t ion

12 J i i 0 Fixed

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Figure 10.- Effect of fixing transition on aerodyn a mic characteristics of airfoil at M = 0.22 and R c = 12 x 10 6 1.6 1.4 ...- /

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Figure 11.- Effect of fixing transition an aerodynamic characteristics of airfoil at M = 0.22 and R c = 15 x 10 .

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Cd lX, deg Figure 12.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.60 and R c = 3 x 10 6 .

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1.6 1.4 Transition 1.2

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Figure 14.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.60 and R c = 9 x 10 6.

1.6 1.4 Transition 1.2

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Figure 15.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.60 and R c = 12 x 10 6.

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Figure 16.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.70 and R c = 3 x 10 1.6 1.4 Transition 1.2

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figure 17.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.70 and R c = 6 x 10 6.

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Figure 18.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.70 and R c = 9 x 10 6.

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Cd 0:. deg Figure 19.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.70 and R c = 12 x 10 6.

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-4 Cd lX, deg Figure 20.- Effect of fixing transition on aerodynamic characteristics of airfoil at M = 0.76 and R c = 6 x 10 6.

o 1.6 1.4 Transition .-

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Figure 21.- Effect of fixing transition on aerodynamic characte~i~tics of airfoil at M = 0.76 and R c = 9 x 10 1.6 1.4 a

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C Cd a. deg m Figure 24.- Effect of Mach number on aerodynamic characteristics of airfoil with free transition at R c == 15 x 10 6.

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Cd a, deg Figure 25.- Effect of Mach number on aerodynamic characteristics of airfoil with fixed transition at R c = 6 x 10 6.

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Cd C m lX, deg Figure 26.- Effect of Mach number on aerodynamic characteristics of airfoil with fixed transition at R c = 9 x 10 6.

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Figure 27.- Effect of Reynolds number on aerodynamic characteristics of airfoil with free transition at M = 0.22.

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Cd lX, deg Figure 28.- Effect of Reynolds number on aerodynamic characteristics of airfoil with free transition at M = 0.60.

• ..

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Figure 29.- Effect of Reynolds number on aerodynamic characteristics of airfoil with free transition at M = 0.70.

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Cd ex, deg Figure 30.- Effect of Reynolds number on aerodynamic characteristics of airfoil with fixed transition at M = 0.22.

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Figure 31.- Effect of Reynolds number on aerodynamic characteristics of airfoil with fixed transition at M = 0.60.

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Figure 34.- Effect of angle of attack on pressure distribution of airfoil with free transition at M = 0.60 and R c = 6 x 10 6 .

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.5

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'?"

:t.

~

1.0 ~ c) 1.5

.4

1.0 .9 .8 .7 .6 .3 .2 .5 . 1 o

x/c

Figure 35.- Effect of angle of attack on pressure distribution of airfoil with free transition at M = 0.60 and R c = 9 x 10 6 .

-3.0

I I

a, deg f- -2.5 A 0 0 I f\. 0 3

I~ 0 6 ~

I~ 6 8

-2.0

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) ....

1.5_

o .1 .2 .3 .4 .5 .6 .7 .8 .9 1.0

x/c

lD Figure 36.- Effect of angle of attack on pressure distribution

O"l of airfoil with free transition at M = 0.60 and R c = 15 x 10 6 .

•

•

• ..

• •

-3.0 a. deg A f....- -2.5 0 a

f

~~

f....- 0 6

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K

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,~

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.. Figure .37.- .Effect of angLe._ of_ attack_on pressure distribuJio.n_

of airfoil with free transitioh at M = 0.60 and R c = 40 x 10 6 .

1. ".;< .. " NASA TM- 85732

.- -_.

s. r.t·~"".Jll eLite

February 1984

Tests of a NACA 65 -213 Airfoil in the NASA Langley

---------_._- ---- ... - - -- 6. Performing O:!rin~"'i:1i(lr) Cride

505-31-53-10

0.3-Meter Transonic Cryogenic Tunnel

E. B. Plentovich, Charles L. Ladson, and Acquilla S. Hill

10. ·:.'8rk C"it No .

•

•

Langley Research Center

Hampton, VA 23665

- - 13. T: .':: c1 r~'~~~)f~ C!,:d r-.~riu1 C .. :: ..... j

Technical Memorandum

National Aeronautics and Space Administration

Washington, DC 20546

A wind-tunnel investigation has been conducted to study the two-dimensional

aerodynamic characteristics of the NACA 65 -213 airfoil over a wide range of

Reynolds numbers. Test temperature ranged from ambient to about lOOK at pressures

ranging from about 1.2 to 6.0 atm. Mach number was varied from 0.22 to 0.80 and

Reynol ds number (based on ai rfoil chord) from 3 x 10 to 40 x 10 . Data are

included which demonstrate the effects of fixed transition, Mach number, and

Reynolds number on the aerodynamic characteristics of the airfoil. A sample of data

showing the effects of angle of attack on the pressure distribution is also given.

The data are presented in an uncorrected form with no analysis in order to expedite

the release of the data.

"

•

Unclassified - Unlimited

Laminar flow airfoils

High Reynolds number

Two dimensional flow Subject Category 02

1 /~.~~_s~~~ ~~_,-t::J~~';~" ~-:'J-;:-t) - - ---. ''70. s:;~;i;~,-c~;,.~;i. (~;--:his. ~:;)------- -J21~ ~~~8-o; p~~~--1- 22~ :;~~----

j

Unclassf-ied - - -.-- - - - ·Unclassified _. -- -- - - - - -

•