Static and dynamic pressure measurements on a NACA 0012 airfoil in the Ames High Reynolds Number Facility

Technmal

Paper

NASA. I

June 1985

Static and Dynamic

Pressure Measurements

on a NACA 0012

Airfoil in the Ames High

Reynolds Number Facility

John B. M cDevkt

and Arthur F. Okuno

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Technical

Paper

198 5

; Static and Dynamic

Pressure Measurements

on a NACA 0012

Airfoil in the Ames High

Reynolds Number Facility

John B. McDevitt

and Arthur F. Okuno

, Ames Research Cente r Moffe tt Field, Califor nia i r , Nahonal Aeronautics and Space Adr'nlnl,slrai=on , Scientific and Technical '_ In f ormation Branch - - " _i_" _'_ ' _- -Y ":' ".. , t NO ME N C L AT UR E b span of airfoil, cm (in) Rec, oo Reynolds number based on airfoil chord and free-st r eam conditions c chord of airfoil, cm (in.)

u,v local velocities in x,z directions _ cn section normal f o rce coefficien t

% - c p

_1 u )d( x/c ) x , z ai r foil coordinates, see figure 1, cm ( in.)

. Xsh shock location - ;. . • Cp pr e ssure coefficient ( p - P oo) /q o o ._, Z test section coordinates, see fi gure 4, cm (in.)

C p '* pressure coefficient at sonic velocity y distance from wall, cm (in.)

f frequency, H z & P (instantaneou_ pressure) - (mean static pressure) T reduced frequency, 2 nfc divided b y free-stream A ( ) incremental quantity velocity (()) rms value m¢ l) ,m ¢2 ) mass flow rates through sidewall boundary-layer _ ,, removal panels (see fig. 4 ) a angle of a tt ack, deg _ ' _ rnT t unnel mass flow ra t e 6" sidewall boundary-layer displacemen t thicknes s M Mach numbe r 6_ s idewall boundar y - l a y e r displacemen t thickne s s fo r rn ( l ) = r _(2) = 0 : p sta t ic pressure, N / m 2 (lb / ft 2) Subscripts Pt pltot pressure , N / m 2 (lb / ft:) B condi t ions a t buffe t onse t • PT , PT t otal pressure, N / m 2 (lb / f t 2) •_ £ lower surface q dynamic pressure, N / m 2 (lb / ft _) N nominal or design value ; _ Re Reynolds number u upper surface oo free-stream value PRECEDIN(, I . \ ., , . . ,. T . , ,_,,, ,, N,_'[ ' F!.LT,_.r.;D SUM MA RY An experimental stud) ' h as been conducted of the supercritical flows at high subsonic speeds over a NACA 0012 airfoil in order to acquire aerod yn a m ic data suitable l ' or evaluating nu m erical - flow codes . The measure m ents consist e d primaril y of sta ti c and dynamic pressures on the airfoil and test - chan n el walls .

Shadowgra p hs were als o take n 'd " the flo w fi eld near the airf o il . The tests were performed at free - stream Ma e h n u mbers fr o m approximately O.7 to 0 . 8, at angles o f attack sufficient to include the o n set of buffet, and at Reynolds numbers (based on airfoil chord) fr om 1 million to 14 m illion . A u n ique test section was employed which was designed specificall y t o obtain t wo- dimensional airfoil data w ith a minimum of wall interference effects . Boundar )' -la y er suction panels were used to minimize sidewall interfere n ce effects . Flexible upper and lower w alls allowed test - cha n nel area - ruling to nullif y Mach number changes induced b y the mass removal, to correct fi _ r longitudinal boundary - layer growth, and to pro v ide contouri n g compatible with the strea m li n es of the m odel in free air .

INTRODU C TION of this approach was demonstrated in reference 2 . The first airfoil chosen for testing in the facility was the NACA 0012, ". which has long been a standard for evaluating wind tunnel The rapid advances in computer technology have test techniques and computational methods and for making prompted similar advancements in computational methods to comparisons between data obtained in different wind tunnels the extent that computers are now routinely used to comple- throughout the world.

ment the wind tunnel m the development of new aerospace The present tests were confined to high subsonic speeds at vehicles. However, the continued development of computa- which the airfoil creates locally supersonic flows terminated tional methods requires experimental studies to suggest by shock waves. The test program included both mean and better turbulence models and to prov,.de test cases for eval- dynamic pressure measurements so that the often overlooked uating new codes. In response to this need Ames Research unsteady flow aspects could be included. In particular, the Center has acquAred the High Reynolds Number Facihty , onset of buffet at high subsonic speeds was carefully . wtaich is being used to perform basic fluid dynamic studies in delineated.

'. support of numerical code developments. This facility con- sists of two major test channels, HRC-I and HRC-2 , which are described in detail in references 1 and 2. T he present APPARA T US AND T ECHNIQUES : " experimental study documents the high subsonic, locally supercritical, flows about a two-dimensional airfoil.

" Two-dimensional airfoil test data at moderate to large M o del Reynolds numbers (where natural transition is far forward on . , the airfoil) which are sufficiently accurate t o be useful in The symmetrical NA C A 0012 p_ofile is shown in figure 1 evaluating numerical codes are virtually nonexistent. The together with a tabulation of the streamwise locations where primary problem is wall interference. Usually, test results are measurements of static and dynamic pressures were made. A s assigned "colrccted" Mach numbers and angles of attack, noted in this figure , the model deviates from the theoretical This procedure is undesirable if the data are to be used in shape near the trailing edge for practical reasons. A sketch of critical assessments of numerical methods. To corr e ct this the model installed in the test section is shown in figure 2.

situation the first test section for use with the facility HRC-2 The angle-of-attack rotation is about the airfoil midchord.

channel was designed to minimize wall-interference effects. The model was machined from stainless steel. The devia- Sidewall boundary-layer removal is used to minimize the tion between measured (near the midspan where the pressure sidewall interference effects. The shapes of the upper and orifices were located) and design coordinates was small, never r : lower walls are adjustable so that Mach numbe - changes asso- exceeding ,S z/c = 0.0005 and usually less than 0.0002. These ciated with the sidewall mass removal and boundary-layer small deviations should not noticeably affect the results. The displacement effects can be nullified and to allow streamline static pressure orifices were 0.03 cm in diameter and con- , contouring compatible with the airfoil in free air. The success nected to individual differential pressure transducers located f J _ in ins _ t ed con t ainers vented to the atmosphere. These c ,m - The source of high-pressure dry air is t he 930-m 3 Ames tainers were located as near as possible to the test section. Underground Air Storage Facihty, pressurized to _i and the length of tubing from orifice to transducer was less 2× 107 N / m 2 (3,000 psi) and m a intained at ambient tempera- than 0.6 m. T he dynamic pressure transducers were buried in ture. With the present test section, the maximum mass flow -_ the model with the diaphragm about 0.13 cm from the sur- rate available is about 360 Kg / sec (800 lb / sec), for which the ; face, and the orifice diameter was about 0.18 cm. The refer- unit Reynolds number at subsomc speeds is about 108 / m and ence pressure sides for these t_ansducers were connected to airfoil test data can be acquired in the Reynolds nunlbei adjacent (same x/c ) static pressure orifices by employing range, based on chord length of 20.3 cm ( 8 in.), from about sufficient lengths of tubing to provide ad, quate damping so 1× 1 0 e to 20× 10 6. The corresponding available test run times that the transducers responded only to dc v mtions from the range from about 5 min to 1 ram. High-frequency pressure mean. transducers and hot wire anemometers were used to measure pressure and velocity fluctuations in the test section. Typical results are presented in table I.

Facility A single-pass shadowgraph system was installed as shown m figure 5. Because of the limited space available inside the The facility and techniques for obtaining two-dimensional test cabin, the light source (steady illumination for motion airfoil data with a minimum of wall interference effects is pictures, spark illumination for still photography ) was , described in reference 2. A brief review _s presented here. located , 'utside the cabin, the light entering through a small i The facility is of the blowdown type, discharging into a w i ndow. The light beam is colhmated by a spherical mirror, large vacuum sphere for low tot,,1 pressure runs ( PT below folded once, and then directed into the test section. For about 2 atm) and into the atmosphere for large total pressure sparkqllummated shadowgraphs a motor-driven fihn maga- uns ( PT ab°ve about 2 atm). A schematic of the new facility zine from an aerial-type camera ( 20-cm by 2 3-cm photu- is shown in figure 3, a,_ddetails of the airfoil test section are graphs) was mounted near the test section window as shown presented in figure 4. The test Math number is controlled by in figure 5. For motion pictures the light beam exits by tra- the adjustable throat at the downstream end of the test sec- versing a similar path on the far side of the test section with tion. Sidewall vent panels (perforated plates) located just the camera located outside the test cabin.

upstream of this throat maintain the "test cabin" pressure cssentially at free-stream static pressure T his alleviates the structural strength and rigidity requirements for the test- Tests and Procedures i section walls and facilitates the use o_large viewing ports for _ . _ making shadowgraphs and laser velo c imeter measurements. T he flow phenomenon chosen for study here is the super- -1 , Upper and lower wall interference effects on the airfml critical flow about the airfoil at high subsonic speeds. An flow field can be eliminated, at least in principle, by contour- important and necessary part of the investigation was the '; , mg the walls to follow t he streamlines in free air at a specific determination of the onse t of uns t eady flow (buffet) as tes * condition. For the present tests an airfoil code was used affected by test Mach number, Reynolds number, and model to compute the streamline shapes for walls initially located angle of attack. For each test condition the experimental 1.5 airfoil chords above and below the model. No attempt technique used required that the upper and lower walls be was made to further adjust the wall contours based on adjusted mechanically at the seven jacking stations shown in experimental measurements, as is done in the "adaptive wall" figure 4. Since the wall contoms could not be changed while approach. However, since solid walls are involved, the appro- the tun n el was running , the test program evolved around a priate boundary conditions can easily be incorporated in series of nominal test conditions, referred to as "data sets," - r: numerical methods when the test data are used to evaluate as shown in figme 6. T he data sets are numbered in the "t codes, chronological order that the test program progressed.

i Sidewall interference effects are reduced by thinning the Measurements were made at Reynolds numbers (based on sidewall boundary layer by suction at two sets of porous chord) ranging front 1 to at least 10 million. No attenipt was panels (one set near the entrance to the test section and the made to fix t ransition on the model. However, a few oil-film other as near as possible to the model; , each set operating tuns were made which provide qualitat i ve information separately from the other. The suction is provided by the low regarding transition Reynolds number. A thin oil film was pressure in the downstream diffuser; the mass-removal rate is applied to the model surface, and post-run inspection indi- controlled by throttling valves and monitored at venturi sec- cared turbulent transition wedges (easily recognized by their ! tJons (see lower right-hand portion of fig. 3). Mass removal l0 ° spreading angle) occurred in the vicinity of small rough- alters the longitudinal Mach number distribution in the test ness elements or surface irregularities near the model leading ": channel, but this can be nullified by appropriate adjustments edge for a certain range ol Reynolds number. Based on these in the upper and lower w a ll con t ours (refs. 2 and 3 ). observation_ the transition Reynolds number for the present tests was est;,nated to .. , :cur between Rey_:olds numbers of _ 2 o., 'r, 1 and 2 million. Since the condition of the model surface is The onset of buffet was determined by recording on tape critical in maintaining laminar fl o w , changes with time , and is the signal output from the dynamic pressure transducers difficult to monitor, parti c ularly in the absence of boundary- (fig. I) as the model angle of attack (" a sweep") or Mach layer surveys, the emphasis in this study will be on the data number ("Mach sweep") was changed. Post-run displays of acquired at high Reynolds numbers. Specifically, the test the signals using various combinations of tape- and chart- - data at Rec ,oo = 10 milhon will be considered to be the most recording speeds were made to view th e _-,nal envelopes and appropriate for use in evaluating codes, wave forms (see exam ? le presented in fig. 12L l ne onset of A detailed description and cahbration of the test so c tion is buffet is easily dlscernable by "his technique since the enve- given in reference 2. The recommended mass removal rates lope of the dynamic pressure measurements when the flow for the sidewall suction panels (see fig. 4) are 3% c f the becomes unsteady (as verified by high-speed shadowgraph tunnel mass-flow rate at the first station ( r _(l ) = 0.03 fiZ T ) movies) grows in essentially linear fashion with angle of _ and 0.8% at the second s,,.Zi_n ( m r2 ) = 0.008 rnT ). The attack. "Buffetting" ( structural response) was not involved in effectiveness of the mass removal in reducing the sidewall dis- the present tests.

placement thickness of the boundary layer is illustrated in figures 7 and 8.

The upper and lower wall contours used for the six data RESULTS AND DISCUSSION sets required inputs from three sources: First, a mean shape correction was required to offset the test sectmn boundary . layer growth in the model testing region. For Mach number The experimental results of this investigation consist of _. and Reynolds number ranges of the present t, s, ramp surface pressure measurements, surveys to define the onset of _. angles of 0.38 o were to be applied as shown in figure 9. buffet, and flow-field shadowgraphs. Separate presentations Second, wall changes were necessary to offset the effects of will be made beginning with the surface pressure measure- _. sidewall mass removal. These changes (see figs. 9 and I0) ments, which were all conducted in the steady flow domain.

" vary with the tes t Mach number, bu t were no t sensi t ive t o "_ Reynolds number , at least within the accuracy of the calibra- tions tests or reference 2 , provided that the mass removal Surface Pressure Measurements rates are large, as in the present case. Third, the walls were contoured to conform to the streamlines of the model in free Surface static-pressure measurements on the model and at air, at a height of approximately 1. 5 chords, as compute4 by the test-channel sidewall for the six data sets (fig. 6) are pre- _, Deiwert's me t hod (refs. 4 and 5) for a Reynolds numbe_ of sented in figures 1 3 -18 It is impor t an t t o note that for t he tO million (see fig. 11 and tabulated values in table 2). airfoil data presentations the origin of x is at the airfoil lead- •" The free-stream test Mach number (c o rr e spon,_ing to ing edg e whereas for the s idewall m e asurements th e origin for x/c = ..o_)was determined as follows: The local Mach number 3( is at the airfoil midchord (center of rotation) (see figs. 1 . near the side wall of the test channel directly ahead of the and 4) . The nominal Mach number, angle of attack , and wing and at station X/c = -3 (fig. 4) was evaluated from mea- Reynolds number (MN , a N , Rec ,o_, N ) in figures 13-18 refer • surements of total and static pressures. A Mach number more to the values used m defining the test channel upper and r e pr e sen t a t iv e of t ha t n e ar t he cen t er of the t est channel was low e r wall con t ours (see earlier discussion in Tes t s and Pre- then obtained by correcting for a slight variation in local cedures section). The effect of Reynolds number on airfoil Mach number across the channel (a residual effect from the pressure distributions is large a t low values of Reynolds num- uneven flow in the bellmouth entrance to the test section), ber but quite small above about 6 or 8 million. Since the _, This correction was _ = -0.003. Finally, the influenc e of streamline shapes used as a basis for wall contouring were the test model on the measurements at tunnel station estimated for a Reynolds number of 10 million, and since the X/c = -3 was estimated by D e iwert's numerical method and accuracy of the test program increases wi t h increasing total the appropriate corrections (see table 3) were applied, pressure, it is recommended lhat the Reynolds number test The measurement of airfoil static pressure employed data for 10 million be used in evaluating numerical codes.

tr ' _nsducers located outside the test section, but close to the The data at low Reynolds numbers have been included as a airf , il (see discussion in "Model" section), and the response matter of interest and to show primarily where Reynolds time (to reach 99.9% of the true value) was about 1 sec. Two number effects are large and where effects are small.

transducers of exceptional accuracy were used to measure A few test runs were made at conditions "off-design" with the test channel static and total pressures at station X/c = -3 regard to the upper and lower wall contouring to obtain a (fig. 4) and were also used to calibrate the remaining trans- feehng for the sensitivity of the present airfoil pressure mea- ducers i m mediately before each test run. Error analyses indi- surements to wall contouring. The effects of being off-design cated that the airfoil pressure measurements wele accurate to in the angle of attack or in the Mach number are shown in +0.002 PT and the free-stream Math number was accurate figures 19 ( a) and (b), respectively. For the test lesults pre- to ±0.002. sented in figure 19(a) the wall contouring used was based on _ . -- _" _._ ' k_ _ -:. - -..t ' the streamlines sh o wn in figure I l ( a). T he open data symbols with Karman-Tsien scaling (applic a ble only fol subcritical ' in figure 19 ( a) represent "on-design" test data in that the test flows) taken from reference 7. Tile corrected data from refer- values of Mach number, angle of attack, and Reynolds num- ence 6 provides a reasonable estimate for free-air values of ber agree with the nominal values (design values) used to Cn/a . The present tests give slightly lower values, but by obtain the streamlines employed in the wall contouring (the about the amount of a small sidewall interference effect data set I streamlines of fig. 1l(a)). The closed symbols in discussed above• figure 19(a) represent off-design test data since the test angle of attack ( a = 2°) differed from the nominal value ( aN = 0°) used in obtaining the streamlines (data set 2 of fig. 1l(a)) for Buffet : _ the wall contouring. The test data reflect the appreciable differences in wall contouring• For figure 19(b ) the stream- The present technique for determining the onset of . line input to the wall _ ; ontouring were those shown in unsteady fl o w was illustrated in figure 12. The envelope of figure 1l(c) and the a = 2° streamlines of figu r e ll(a). T he the d y namic pressure measurements g ro ws in essentially o pen symb o ls in figu r e 19(b) r epresent o n-design test data linear fashion with angle o f attack in the unsteady fl o w (the test Mach number, angle o f attack, an d Reyn o lds num- regime s o that the angle o f attack where buffet started is bet agree with the d esign values) while the cl o sed symb o ls easily discernible.

•: represent off-design test data _ince the test Mach number The buffet onset surveys were made at al! of the test ( M o o= 0.775) differ e d from the design value ( MN = 0.750)• setups (data sets) shown in figure 6 except for setJp no. 2.

In this case the differences in contouring were small and the The nominal or "design" angles of attack for data sets 4, 5, : experimental pressure measurements reflect this. T he test and 6 are very close to the buffet region, and the buffet results presented in figure 19 could be used as test cases in onset data should not be subject to appreciable off-design ._ numerical studies of wall interference effects• It should be effects• Typical post-run data displays are presented in fig- _. kept in mind that solid test channel walls can easily be ures 22-24 fbr data set 5 ( MN = 0 .775, aN = 2 ° ). Envelopes _" included in numerical methods and that i t is not necessary of th e pressure deviations from the mean and the model "_ for the test data to represent free-air conditions in order to angle of attack are presented in figure 22(0 for upper surface be useful in evaluating numerical m ethods. However, the measurements at x/c = 0.5 and 0.8. Wave forms at a = 4°, availability of "free-air" ( or n e arly so) data is to be preferred which is well into the unsteady domain, are presented in to avoid dealing with the uncertainties of wall-interference figure 23 and a comparison of upper and lower surface wave effects, forms is presented in figure 24. All of the buffet onset mea- The sidewall boundary-layer effect on the airfoil pressure sure m ents made at Reynolds numbers from 1 to 10 million .. measurements was evaluated by comparing test results with are summari z ed i n figure 25. These measurements were and without the use of the sidewall mass removal systems, obtained from "a sweeps" except for the two points at •; The normal force coefficient a = 0° included in figures 25(e) and 25(0, which were ' . o btained by "Mach number sweeps." Although the angle of Cn = ( Cp _ - Cp ber sweeps, the test Math number did vary slightly during the f ooI u )d( x/c ) attack remained fix e d (exac t ly at 0°) during the Mach num- a sweeps because of the change in stream momentum which affects the behavior of the speed control (see fig. 4). In is easily integrated with good accuracy and when it is normal- figure 25 the open symbols refer to data obtained with the • ized with respect to the angle of attack it may be used as midchord ( x/c = 0.5) sensor and the closed symbols refer to shown in figure 20 to demonstrate the loss in lift due to the the sensor near the trailing edge ( x/c = 0.8). During pitchup presence of the sidewall boundary layers. The displacement a sweeps at low Reynolds numbers, the midchord sensor sig- thickue_s values, _i*, were th_ average of the values (deduced rials buffet onset before the aft sensor responds, indicating fr o m pitot rake surveys) measured just ahead of, and behind, that the origin of the unsteady phenomenon is nearer to the the airfoil (see fig. 4). The basic data presented in this report midchord than to the trailing edge. However, at high (figs. 13-18) were obtained with rh tl _ = 0.03 rhT a,_d Reynolds numbers (greater than about 6 million)both sen- r _(2) = 0.008 rhT , and the normal force coefficient is about sors respond in similar fashion. High-speed shadowgraph 3% low, assuming that extrapolation to 8" = 0 is permissible, motion pict u res show that an intermittent shock-induced When no sidewall mass removal is made ( m (l) = _ h t2 ) = 0), separation of the boundary layer occurs near the midchord at the normal force is in error about 15%. angles of attack coi n cident with the buffet onset measure- i The normal-force coefficients, per degree of angle of ments. Thus it would be appropriate to label the buffet " attack, taken from data sets 1, 4, 5, and 6 for phenomena observed here as "shock-induced." In figure 25 Rec , oo _. 10X106, are presented in figure 21 alld are corn- the unflagged symbols refer to model pitchup, the flagged " pared with corr e cted data fr o m r eference 6. Also inclu d ed in symbols t o pitchdown. A hysteresis effec t is no t discermble thi s figure is a theoretical incompre s sible fl o w prediction from these te s t s .

?

._. 4 The pressure wave forms in the buffet region were invari- shown in figure 34. The shock location was deduced from " ably e rratic at low Reynolds numbers (less than about 6 nail- flow-field shadowgraphs and from pressure measurements.

lion) , but at large Reynolds numbers the cyclic nature and When the angle of attack is increased from zero, the shock frequency were well defined. The reduced frequency param- first moves downstream, then upstream, and eventually eter 27r fe/U _ measured during buffet at a Reynolds number buffet begins.

of 10 million are tabulated in table 4.

C O NCL U DING REMA RKS S h ado w g r ap h s Spa r k - illumina t ed s h ado w g r a phs of t he up per, aft fl o w T il e tes ts d es c r i b ed w e re p erfo r m e d t o o b tain da t a suita- ; fields at Reyn o lds numbers ranging fr o m 1 t o 10 million are ble f o r evaluating numerical flow-simulation c o des. Emphasis presented in figures 26-30. The clarity of the photographs was placed on measurements at high subsonic speeds near the , diminish markedly with increasing Reynolds number because buffet region. The onset of the buffet, as affected by free- of the increased turbulent activity, particularly at the edges stream Mach number, angle of attack, and Reynolds number, of the sidewall boundary layers. Shadowgraphs illustrating was included in the study, and this information also can be the effect of angle of attack on the flow fields are presented used as a test case for evaluating codes. Test data were in figures 31-33. The nominel (or "design") test Mach num- obtained over a wide range of Reynolds numbers, but the bet and angle of attack ( MN , aN ) for which the upper and measurements at Reynolds numbers of 10 million are consid- lower walls were contoured are included in the figure titles ered to be the most appropriate for evaluating codes.

_5 together with the angle of attack for buffet onset (from The tests were performed in a new test leg for the Ames fig. 25). High Reynolds Number Facility, and a unique test section ; Although the clarit y with which these photogr a phs dis- was used which has provisions for minimizing wall interfer- ",- play the flow phenomenon diminishes with departure from ence effects. By using sid e wall suction the boundary-layer ",. the nominal angle of attack, aN , some observations can rea- displacement in the vicinity of the test model was reduced by __ sonably be made. First of all, these photographs, as well as about 75% and the reduction in airfoil normal force due t_ high-speed motion pictures, show that the onset of buffet sidewall boundary layers was determined to be less than coincides with the change from normal shock to an intermit- about 3%. Interference by the upper and lower walls was tent shock-induced separation of the boundary layer. When minimized by contouring to conform with streamlines of the the airfoil is in the steady flow regime, but near buffet onset, model in free air as estimated by an airfoil code that includes an increase in either the free-stream Mach number or angle of viscous effects. Since solid walls were used, the representa- attack will increase the local Mach number ahead of the tion boundary condition of tangential flow can easily be normal shock until, ultimately, the boundary layer can no included in the numerical methods. Comparisons of solutions longer tolerate the shock-induced pressure recovery, and with and without wall boundaries would be helpful in deter- separation occurs. With separation an oblique shock wave mining, qualitat w ely at least, if appreciable interference forms and, in effect, the airfoil _,hapcis altered (akin to the effects are present. It is not necessary, of course, to use free- upward deflection of a trailing-edge flap), which tends to air data to evaluate codes, but this is to be preferred to avmd slow down the upper flow field. This causes the flow field to dealing with the uncertainties of wall-interference effects. It return to its original configuration - hence the intermittent should be understood that the wall shapes to be used as invis- phenomena. At moderate to large angles of attack, the inter- cid boundaries in numerical simulations are the streamlines mittent, shock-induced separation phenomena may only presented in figure 11 and are not the actual _all shapes occur on the leeward surface, as the windward flow field is used, which included inputs from the test.secti o n caiibration too far removed from buffet onset to separate (in fact, in (internal area ruling to offset longitudinal Mach number some cases the lowm flow field may be everywhere subcriti- changes due to mass removal and boundary layer displace- cal), althougll the consequences of the upper flow field oscil- ment growth) performed to obtain a aniform test medium.

lations are felt globally. When buffet occurs at, or near, a = 0 ° , the unsteady phenomena are similar in the upper arid lower flow fields, but 180° out of phase. Ames Research Center The effect of angle of attack on the chordwise location of National Aeronautics and SFace Administration the base of the shock wave in the steady flow regime is Moffett Field, California 94035, February 1985 • 5 t' ?

RE F EREN C ES 1. McDev_tt. J. B.; Levy, L. L, Jr.; and Deiwert, G.S.: 5. Deiwert, G S.: "Computation of Separated Transonic "Transoni c Flow , about a Thick Circulai-Arc Ailfoil," Turbule n t Flo w s," AIAA 1., v o l. 14, J u,ae 1976, AIAA J., vol. 14, no. 5, May 1976, pp. 6 06 - 613. pp. 735-740.

2. McDevitt, J. B.; Polek, T . E., and Hand, L. A.: ' a , New 6. Harris, C. D , : "'Two-Dimensional Aerodynamic Character- , Facil i ty and T echnique for Two-Di'neusi o nal Aerody- ist i cs of the NA C A COl2 A i rfoil in the Langley 8-Foot namic Testing," A!AA J. Aircraft, vol. 20. nc;. 6, June Transonic Pressure Tunnel," NASA T M 81927, 1981.

o 1983, pp. 543-551. 7. V idal, R. J.; Catlin, P. A.; and Chudyk, D . W.: " T wo- 3. Bemard-Gu e ll e , R.: "Influence of Wind Tunnel Wall Dimensional Subsonic Experim e nts with an N A CA Boundary Layers on Two-Dimen_ional T ransonic 0012 Airfoil," Calspan Report No. RK-5070-A-3, T ests." NASA TT F17,253, 1975. C alspan, 19 ? 3.

4 Deiwert, G. S.: "'Nu m er i cal Simulation of Reynolds Number T ransonic Flows," AIAA J., vol. 13.. Oct.

1975, pp. 1354-!359.

L TAB LE 1. - T ES T -S E CTION PRESSU RE AND V EL OCI T Y LEVELS, a M oo = 0.8 PT " N / m2 .

1.4Xl0S [ 0.02 I0.0046[

i o . o __1 o . oo o I

a Measurements by F . K.

Ow e n of Complere, Inc.; NASA Contract NAS 2 -10859.

; 6 i TABLE 2. - FREE-AIR STREAMLINES ( see fig. ll) Upper wall Lower waU Upper w:_" I Lower wall I Data set 1; M N = 0.75, aN = 2° Data set 4; M N = 0.80, a N = 1° . -4.25 0 0 -4.25 C 0 -2.50 .0063 0050 -2.50 .0050 .0013 -1.25 .0200 .0110 -1.25 .0154 .0018 -.50 .0308 .0070 -.50 .0250 -.0041 0 0308 .0025 0 .0269 -.0085 .50 .0210 0 .50 .0194 -.0079 .25 .0045 -.0030 1.25 .0066 -.0056 .50 -.0138 -.0150 2.50 - 0075 -.0081 i .55 -.0230 [ -.0235 3.55 -.0133 -.0115 . .79 -.0320 I -.0300 4.79 -.0183 -.0159 Data set 2 ; M N = 0.75, a N = 0° Data set 5 ; MN = 0.775, _ N = 2° -4.25 0 0 -4.25 0 0 -2.50 .0031 -.0031 -2.50 .0063 .0056 -1.25 .0080 -.0080 -1.25 .0209 .Ol15 -.50 .0145 -.0145 -.50 .0321 .0074 0 .0180 -.0180 0 .0321 .0026 .50 .0145 -.0145 .50 .0220 0 1.25 .0080 -.0080 1.25 .0048 -.0031 2.50 .0038 -.0038 2.50 .0138 -.0150 3.55 .0012 -.0012 3.55 -.0240 -.0246 4.79 .0010 -.0010 4.79 -.0322 -.0328 Da t as et3 ; MN = 0. 8 0,_ N = 0° D at a set 6; MN = 0 . 7 25,_ N = 4 ° -4.25 0 0 -4.25 0 0 - 2 . 50 . 0 0 3 4 -.0 03 4 - 2.50 . 0 094 .0 08 8 -1.25 .0088 -.0088 -1.25 .0308 .0288 -.50 .0160 -.0i60 .50 .0451 .0274 0 .0199 -.0199 0 .0418 .O216 .50 .0160 -.0160 .50 .0264 .0138 1.25 .00 88 - .0 088 1 . 25 .00 38 0 01 3 2.50 .0040 -.0040 2.50 -.0 2 38 -.0250 3.55 .0014 -.0014 3.55 -.0438 -.0451 4.79 .0012 - . 0 012 4.79 - .0594 - .0600 i T ABI , E 3 .- C ORR E CTIONS TO M EASURED MA C H N U M B E R A T TUNN E L STATION X /c = - 3 ( see fi g . 4) DUE TO PRESEN C E O F MODEL M o o a , d e g A M M oo 0_,deg A M 0.725 0 0.00 4 6 0.775 0 0.0050 2 .0048 2 . 0 0 5 3 4 .0051 4 .0057 0.75 0 0.0048 0.80 O 0.0053 2 .0050 2 .0056 4 .0053 4 .0061 TAB L E 4 . - SH O C K- OS CI LL AT I O N FRE Q UE N C Y P A R AME T E R fi = 2 nfc /U oo IN B U F FET REGI ON , Rec , _ = IOT MN aN , deg M oo or ,deg fi 0 .725 4 0 .72 6 0 .55 .750 2 .75 4 .47 .775 2 .77 4 .44 • 800 1 .80 4 .38 x 3

o oo o . j

LEADING-EDGE RADIUS = 0.0158 c Z _ 0. 0 02 c c = 20.32 cm _ 8 i n.) r > STATIC DYNAMIC PRESSURE P RESSURE ORIFICES ; TRANSDUCERS ' : " x / c UPPER LOWER UPPER LOWER 0.025 . _ j ! 0.05 • • 0. 07 5 0 . 10 0.15 0.20 ....

t " 025 • f 0 . 30 • • 0 . 35 0.40 0 45 0 50 0 .55 0.60 0.65 0 .7 0 • 0 75 0 . 80 ....

0.85 • • 0.925 • • 0 . 95 . _ • 0.975 • • 1.00 F i g ure l . - N A C A 0 0 1 2 p r o fi l e a n d l o ca tion o f pres s ur e orific e s.

• t "- . a , ,_ " _ - , j .... '; , TUBING AND WIRING FROM MODEL _ 4 _ - d "" / _ U U b 2 c DYNAMIC PRESSURE • • • / TgAN S DUCER S

,- I} ................. <_ O RIFIcEsSTA T'C PRE S S UR E

20.32 cm (8 m.)

r" t r _ a I I I !

_" F ig ur e 2. Sketch of mod e l i nstalled m tu n nel.

RUP1 URE DISC B EL LMOUTH ENTRANCE CONE TEST SECTION ACCESS __ PERFORATED PLATES DOOR AND SCREENS jf / 1_-_-];¢ / TEST SECTION

, i i '.SETTL,NG _

" _I-l!l/ - i a l l I ! _ O ' AM: :_ I / LI . ,' ! I! t l-, , 'll /" _ , _' _______ . _ x I N L ET / r _ " ' : i ' -- _ " " / 1 " _" S P AC E R E SERV E D FOR B OU N DARY LAY E R V E N T UR I ACOUSTIC NOISE ,_ U P PRESSION REMOVAL S Y S TEMS THROTTLING PANELS AND HONE ' _ C OMB VALVE F i g u re 3. - Schematic of HRC - 2 and ai r fo i l test _ction.

" I O im

_ ........ [_,_II

. = BOUNDARY LAYER PITOT SURVEY STATIONS / BOUNDARY- L AYER F L EXIBLE WALL / ADJUSTAB L E THROAT REM Q VAL P A T : E L S JACKING STATIO N S / FOR SPEED C O NTRO L / / ; 1 2 3 4 5 6 7 • t = I I I / ' ,_ I I I f f \ I " " I I \ SIDEWALL

;(D " f_ / I

INL E T _ k - - ' CO / ' I _ I_: ' : /' l -- i !i t 1 HATCH • - STATION - _ = -3 . TTACK / ; _ ; _ _ _ _ L ! '_ '_' _ " :.. .... DIFFUSER __ _.J T URNT A BLE I I ,.., I I I I I f t BASIC DIMENSIONS I I I I I i / , , , , t , / ' 1 / " WIDTH _ 40.6 cm (16 i n.) t . l A + J / /¢ HEIGHT = 61 . 0 cm (24 m . ) 2.50 - 1 .2 5 0 1 .25 2.50 / LENGTH = 279.4 cm (11 0 m .) _ VENT TO TEST CABIN + F i g ure 4.- Test section schematic.

A ERIAL CAMERA MA G AZINE Figure 5 ,- Schematic of s hadowgraph s_stem (cro ss-s ecti o nal view fr o m above).

i ; '= l I B UFFE T O NS ET , Re c , _ = 10 7 r ( FR O M F IG 25 f ) / -' 6 r Z _ " " _' " ,_ .. _ _ t UNSTEADY F L OW " c , , deg _ _ , _ D AT A SE T = 1 "_,_ : 2 O 5 0 ,, % 2 3 '_ 0.7 .72 . 74 . 1 6 78 8-0. 8 2 M _ H Figure6. T est ll:atr]x.

" n_ i / r_ T n_2 / m T ' f _0 0 0 " - ' ---- -n 0.03 0.008 _] r_ I TES T S TAT IO N

,--_I-- _-i-i-_- + _ --

LJ / _ I _ \ :'

L _ • l J / , L I '

-s 00 / : 3 7s-z_o / -,.25 o 12_

- / _- . L B .k, R A KE / / NO. 1 / NO. 2 NO . 3 1.5 t i y , cm _, * /h o = 0 . 48 0.20 0. 36 ¢ I] I

, ¢_

1.0 [ _ I r 0 _ . 6 . 8 1 . 0 . 6 . 8 1 . 0 , 6 .8 1 . 0 PITOT PRE SS UR E / T OT A L H E AD = Pt / PT Figure 7 . - Typicals i dewallbou n dary-laye r pi t ot surveys, M, ,_ = 0 . 775, Rec , , , , , = 107.

_ P 12 l, M N = 0 . 7 ! " " " " 0 00 3 0 / ... , C Y _ 0 0.00 8

, _. / _; _ c_ , -/

1 I [] r _l / r _ T _ 2 / r _ T S I D EWALL P ' " _ , __ tt _ P A N E L S " o 1 ',' 1, [] MN = 0. 8 , _ ., - .., 0 0.0 3 0 " - . . . . X_ r '_ t . ___ 0 0 .008 . _ 0 .03 0, 00 8 :\ 0 ,i i _,, i - 7.5 - 5 .0 - 2.5 0 2.5 Figure8.- Typicallongi t udinalvariationsin s i dewallboundary-layerd i splacementthick,less ,Rec , oo = 107 .

BO UN D ARY - LA Y ER GROWT H CORRE C TION , 0 .7 _- M _ .-: 0 .8 , 0 50 \ 0.39 .. . . . .,.. . .. _ i UPPER W A LL . ... _ . _ .. - .. _ ,0 25 .. , . .

L " _" 0 F IXE D POINT . . .,.... - - - "' " " " r" _ __ - 0 25 , _ ARE A R U L E C O RRECTI O N FO R ! SIDE - WALL M A SS REMO V AL - .0 5 0 (SE E FIGURE 10) .IkJ i q . _ __L_._ _ l -- - -- __ __ J. _ _ _i_J ur ] -3 . 75 - 2.50 - 1 . 25 O 1.25 ' 2 . 50 3 . 75 5 .0 0 .0 5 0 )( / T / / . 025 / 1.5 - . 025 "" - ,.- LOWER WA L L "" " " " " " " "' .

- . 05 0 " " " " - ,, . .

Figu r e9.-- Uppe r and lower wallcontouring t o off s et channelboundary-layergrow t h and sidewallmass r emoval.

t "" 13 p, i I

J

t

.i

t -.026 ' , _ 2 ; '<106 < R ec, _ < 1 4 X 1 0 6 L 4 - . 0 2 2 'I _ Z -.0 18 -. 0 1 4

.4

.5 , .

Mo _ F i gur e 10.- T e s t ch a nnel cross . sec t ion a l area ch a nge requi r ed t o offse t effec t s of sidewall mass rem o val; rh (1 ) = 0. 03 rh T , &(2) = 0.008 & T " 'I r

t

I

FLEXIB L E-WALLJACKING S TATIONS UPPERWA L L , 0 25 _ t ' ' _ " o _ = 0 _ - . 0 2 5 _ _ ? ._ , -.050 (DAIA SE r 1) I_ _ --ct---_-_--._m_-----_-------_---_--_, - 3 . 75 -2 . 50 -1 . 25 0 1.25 2.50 3 . 7 5 5 . 00 .0 5 0 R .025 1.5c 0 _. .... --- -.025 "- . -. - ... ,. ..

LOWERWALL -. 0 5 0 (a) M = o = 0. 75; Rec , oo = 1 07;_ = 00 ,2 ° (Data Sets 2 and 1).

FLEXIBLE-WALLJACKINGSTATIONS 11 .5 -.o25i _ = 1'_ (DATA S ET4) _ 0 50 I i _ =-_--__-_'_'-_--'_---_--- - 3 . 75 - 2 . 5 0 - 1.25 0 1 . 2, _ 2 .50 3 . 75 5.00 . 0 50 "< '6 . 025 1 . 5 c 0 -.0 25 LO WERWAL L -. 0 50 (b) M oo= 0.80; Rec, _ = 107;_ = 0 ° , 1 ° ( D ata Sets 3 and 4).

Figure 11.- Streamlin e sof the airfoil in free ai r .

I ° FLEXIBLE-WALL JACKING STATIONS UPPER WALL .025 FIXED POI N T _ Z _ T q 1.5c o, ; -. 0 25 < _ J -3. 7 5 -2.50 - 1 .25 0 1 .25 2.5 0 3. 7 5 5.00 • __ X _ c

o . I

.02 5 1.5c

. _ zo - .. _

,1 -.025 _" LOWER WALL f -. o5o -- (c) M oo= 0.775 ; Re c, oo = 107; _ = 2 ° (Da t a Se t 5) .

FL EXIB L E-WALL JA C KING STATIONS .050 UPPE R WA L L I ; J .025 FIXED P O INT _ " E 0 1t , 1.5 " - .025 : -

_ z .. _ __.._

(

-. 0 5 o _j

- 3.75 - 2 . 50 -1 . 25 0 1 . 25 2.50 3. 7 5 5 .00 • 050 R Y . 025 r " - , 025

_ ° _ _

_ , LOWER WALL - .050 (d) M oo= 0 . 725; Rec ,o _ = 107 ; o _= 4 o ( Da ta Se t 6).

Figu r e I 1.. Concluded.

O F . pOOR Qw.--:_• Figur e 1 2.- Typical post run displays of dynamic pressure measurements showing onse t ot buffe t (sensor at midchord).

o- RIRFOIL UPP E R SURFACE

NRCR 0012 RIRFOIL x / c Cp P / P? M i

9,000 1,136 0.996 0.0 7 9 0.025 -0.35 7 0.585 0.909 H.s 0.050 -0.455 0.558 0.952 0.100 -0,804 0.462 1,1 1 0 0.150 -0.909 0.434 1.161 -1.0 o _ o o o , 0.200 -0.984 0.413 1.199 0.0 7 5 -0. 7 32 0.482 1.0 7 6 0.250 -i 0]9 0.403 1.21 7 4 °°_ r, _.... _, _ n _ !.19 7 o _ B o 0.450 -0 424 0 56 7 0.938 o Do o • 0.500 -0 238 0.6]8 0.859 o 0.550 -0.209 0 626 0 846 Op o.o _ @@@@, . .

0.600 -0.152 0.642 0.822 0.650 -0.15G 0.641 0.824 o.5 0. 7 00 0.750 -0.071 0 664 0. 7 88 0.800 -0.0!7 0 679 0 . 7 65 _.o 0.850 0.043 0 695 0.740 !

0.900 0.093 0 709 0.718 t 0,930 0,12i 0 7 1 7 0,707 1.s ..... 0.950 0.161 0 728 0.689 !

0.o 0.2 0.4 0.6 o.a 1.0 0.980 0.205 0 7 40 0.670 i X / C 1.000 0.189 0 735 0 . 677 5[DENALL , Z / C = 1.3 7 5 o - RIRFOIL LONER SURFRCE X / C Op P / PT M i X / C Cp P / PT M -3.75 0 . 054 0.70 1 0. 7 31 t -2.50 0.023 0.693 0.743 _ 0.025 0.]25 0.720 0.701 -2.00 0.027 0.694 0.742 " 0.050 -0.]23 0,650 0.810 -1 . 50 0 . 024 0.693 0.743 t 0.100 -0.3 7 0 0.582 0.9[5 - ].00 -0.009 0.684 0. 7 5 7 1 0,200 -0.509 0,54 7 0.969 -0,50 -0,058 0.6 7 1 0, 7 7 7 0,300 -0.4 7 8 0,552 0,962 0.00 -0.017 0.682 0. 7 60 _ i 0,400 -0,39 7 0,5 7 8 0,921 0.50 -0.030 0,6 7 8 0. 7 66 i 0,500 -0,292 0,603 0.882 1.00 -0 , 012 0,683 0.758 1 0.600 -0.187 0,635 0.832 1.50 -0.071 0.66 7 0.783 _ ," 0, 7 00 -0,110 0,653 0,804 2.00 0.012 0.690 0. 7 48 | 0,800 -0,036 0,6 7 6 0, 7 69 2.50 0,00 7 0,688 0, 7 50 0.850 0,014 0.58 7 0. 7 52 3, 7 5 0,039 0.69 7 0, 7 3 7 0,900 0,06 7 0, 7 05 0,725 0,930 0.105 0.712 0. 7 13 " 0.950 0.132 0. 7 22 0.698 SIBENRLL, Z / C = - 1 . 375 0.980 0,174 0, 7 31 0,684 X / O Op P / PT M SIOEWRLL, Z = 0 -3. 7 5 0.058 0. 7 02 0.729 -1.00 -0.005 0.685 0.755 X / O Cp P / PT M -0.50 -0.256 0.617 0.862 0.0 0 -0.015 0.682 0.760 -3.75 0,061 0.702 0. 7 29 0.50 0.022 0.692 0.74{ -3.00 0.02! 0.689 0. 7 49 1.00 0.003 0.68 ? 0.752 -1.25 0.06 7 0. 7 03 0. 7 2 ? 1.50 0.010 0.689 0. 7 49 [.25 0.036 0.695 0.740 2.00 0.007 0,688 0. 7 50 3 . 75 -0.004 0.684 0. 7 57 2.50 0.032 0.695 0. 7 40 3. 7 5 0.032 0.695 0. 7 40 ( a ) , i _ l I 0.7 53 , a = 2.0 2° , Rec _ = 1.2X 1 0 _.

Fi g u re 13 . - Alr _ iI an d test _ ctio n s ldewa H pr e_ ure mea s ure me n t s , Data S e t l ( MN = 0.75 , a N = 2° ).

+ o - RIRFOIL UPPERSURFRCE NRCR O0 ] 2 N I RrO I L x / c Cp P / P T M - - 0.000 1.08t 0.982 0.161 0.025 -0.507 0.552 0.962 -t. s 0 . 050 -0 . 72t 0 . 494 1 . 056 , o o o , o 0.100 -0.956 0.43i 1.166 o 0.150 -1.064 0.402 1.220 -i.0 o - 0 . 200 -1 135 0.382 1 . 25 7 O 0.250 -1.175 0.371 1.2 7 9 t 0.075 -0.881 0.451 1.130 --i n _ o 0 . 300 -1 . 211 0 . 362 1.298 _,, _ _,.o < _ _ .... _--- - -Jr .......... _ 0.350 -' . 23_ n.35q !.312 0._50 -1.187 0.368 1.285 : i_ o @ 0 + Op 0.0 o 0 . 500 -0.683 0.505 1 . 039 [] - _a 0 . 550 -0 . 340 0.597 0 . 891 ' 0.600 -0.219 0.630 0.840 : 0.650 -0.165 0.645 0.817 a . s 0 . 700 -0.1 2 6 0 . 655 0.801 0 . 7 50 -0.093 0.664 0 . 7 8 7 0 . 800 -0 . 049 0.6 7 6 0 . 7 69 _ 1.0 0 . 850 -0 . 006 0.688 0 . 751 it_ 0.900 0.049 0.703 0.728 0 . 925 0 . 082 0. 7 11 0. 7 15 + . l. s ..... 0.950 0.115 0.720 0. 7 01 -i o.o 0.2 0.4 0.6 o.8 1 . o 0.975 0 . 169 0 . 735 0 . 6 7 8 i X / C 1.000 0.222 0 . 749 0 . 656 , 5IDEN_LL , 2 / C = 1.3 7 5 ! [] - RIRFOIL LONER SURFRCE X / O Op P / PT M + X / C Cp P / PT M -3.75 0.013 0 694 0. 7 42 i -2 50 -0.036 0 681 0 7 62 0.025 0 1 7 2 0. 7 36 0.676 -2 O0 -0.028 0 683 0 7 59

!

' 0.050 -0 087 0.666 0. 7 85 -1 50 -0.031 0 682 0 760 0.100 -0 335 0.599 0.888 -1 O0 -0.0 7 1 0 671 0 777 0.200 -0 4 7 6 0.562 0.947 -0 50 -0.137 0 653 0 804 0.300 -0 468 0.563 0.945 0 O0 -0.130 0 655 0 802 0.400 -0 380 0.5W 0.905 0 50 -O.ItO 0.660 0 7 93 i -, 0 . 500 -0 305 0 . 60 7 0.876 1 O0 -0.058 0.6 7 5 0 7 71 ; 0. 7 00 -0 149 0,649 0.811 2 O0 -0.045 0.6 7 8 0 7 66 0.600 -0 220 0 . 631 0.839 1 50 -0,045 0 . 6 7 8 0 7 66 1 " 0.800 -0 0 7 2 0 . 6 7 0 0 . 77 8 2 50 -0 , 047 0 . 678 0 767 0 . 850 - 0 020 0.684 0. 7 5 7 3 75 -0 , 014 0.686 0 7 54 0.900 0 036 0. 7 00 0 . 7 33 0 . 925 0 066 0. 7 0 7 0 . 7 21 0 . 950 0 I01 0. 7 1 7 0. 7 06 SIOENRLL , Z / 0 " -1.3 7 5 i 0.9 7 5 0 149 0. 7 30 0 . 686 X / C 8p P / PT M 51O E NRLL , Z = 0 -3, 7 5 0.01 9 0.695 0 . 7 40 -1.00 -0.035 0.681 0. 7 62 X / C Cp P / PT M -0.50 -0.022 0.684 0. 7 56 -3. 7 5 0.027 0.69 7 0. 7 3 7 0.00 -0.03 7 0.680 0. 7 63 -3.00 -0.012 0.686 0. 7 54 0 50 -0.035 0.681 0. 7 62 1 O0 -0 . 031 0.682 0 . 7 6 1 -1.25 0.030 0 . 698 0.735 1 50 -0.018 0.685 0.755 1 . 25 -0 . 007 0 . 688 0 . 7 51 2 O0 -0 . 019 0.685 0 . 7 55 3 . 7 5 -0 . 015 0.686 0 . 7 54 2 50 -0.010 0.68 7 0. 7 52 3 75 -0.005 0.689 0. 7 50 _ ) M = = 0 .7 49 ,_ = 1 .99 °, Rec , =" 2 . 0 X 1 06 .

F l su _ 13. - Cont _ u e d.

I

g%

o-AIRFOIL UPPER5URFRCC

, NRCR 0012 AIRFOIL x / o Op P / PT M

o.o0o 1.o75 0 ,qan 0

:. 0 . 025 -0 . 543 0 54{I 0 980 -1.5 , 0.050 -0. 7 49 0 484 1 0 7 2 0.0 7 5 -0.909 0 44[ I 148 o o o 0 . 100 -0 . 984 0 42i i 185 o 0 . 150 -1 . 083 0 .'3F_4 l 2 35 t I -1.O o _ 0 . 200 -1 . 145 0 3 /7 1.268 o _ 0 . 250 -1 . 168 0 3 7 1 1.280 I -d'-C ,, o 0 . 300 -1 . 208 0 360 1 . 302 -0.s r o 0 . 350 -I 235 0 352 ] 318 i Q • : o o o u , ' iO0 -_.. 2 3_ S 352 1.315 0 . 450 -0 . 602 0 524. : . OOb -! Op o.o o .'. 0 . 500 -0 . 449 0 566 0 . 940 ° @ o _ ; o - ooo_ 0 . 550 -0 . 334 0 . 59 7 0 . 8£I ._ 0 . 600 -0 . 253 0 . 619 9 . 85 7 o.s -4 0 . 850 -0 . 194 0 . _35 9 . 832 0.700 -0 . 144 0 . 649 0 . 811

I

0. 7 50 -0.101 0.660 0. 7 93 , 0 . 800 -0 . 051 0 . 674 0 . 7 72 .

1. o 0 . 850 -0 . 002 0.68 7 0 . 7 52 L : O . 900 O . 055 O . 7 03 F) . 72 8. !

0 . 925 0 . 088 0,F12 0 . 7 14 " 1. 5 ...... 0 . 950 O. 122 0 . 72 ' 0 . 7 00 i , o.o 0.2 0.4 0.6 o. e 1.0 0 . 9 7 5 0.1 7 2 0 . 7 35 0 . 6 7 9 X / O 1 . 000 0.219 0.747 0 . 659 i : SIOENALL , Z / C = 1 . 375 .

: o - AIRFOIL LONER SURFRC[ X / C Op P / PT M { -3 . 7 5 0 . 028 O.Gg6 0. 7 33 i X / C Cp P / PT M -2 . 50 -0.021 0.683 0. 7 53 0.025 0.200 0. 7 43 0.666 2.00 -0.015 0.684 0.755 0.050 -0.061 0.6 7 1 0. 77 6 -1.50 -0.016 0.684 0.757 !

0.100 -0.29 7 0.607 0.8 7 5 -1.00 -0.05 7 0.673 0. 77 4 0.200 -0.416 0.5 7 6 0.924 -0.50 -0.112 0.658 0. 7 98 • 0.300 -0.415 0.5 7 5 0.925 0.00 -0.084 0.666 0.785 0.400 -0.334 0.598 0.890 0.50 -0.082 0.605 0.784 0.500 -0.2 7 9 0.612 0.868 1.00 -0.035 0.679 0. 7 65 .

0.600 -0.195 0.636 0.831 1.50 -0.024 0.682 0.760 0. 7 00 -0.12 7 0.653 0.804 2.00 -0.028 0.682 0.761 0.800 -0.051 0.6 7 5 0. 7 71 2.50 -0.022 0.683 0. 7 59 0.850 -0.005 0.68 7 0.753 3.75 0.008 0.691 0. ? 47 0.900 0.052 0. 7 03 0.728 0.925 0.082 0. 7 10 0. 7 1 7 0.950 O. 116 0. 7 20 0. 7 01 SIOEWRLL, f / O =-[ . 3 7 5 0.9 7 5 0. 159 0. 7 31 0.684 . X / O Op P / PT 1"1 SIDEWALL , Z=O -3 . 75 0.033 0.69 7 0.736 -1.DO -0.016 0.634 0. 7 57 _ / O Op P / PT N -0 . 50 0 . 005 0 . 690 0. 7 48 0.00 -0.013 0.685 0. 7 56 -3.75 0.04'I 0.700 0.732 0.50 -0.017 0.684 0. 7 5 7 -3.00 0 . 003 0. 6 89 0.750 1 . 00 -0.015 0 . 685 0 . 756 -1,25 0.04'I 0.700 0.732 I.50 0.002 0.68q 0.749 1.25 0.017 0.693 0. 7 43 2.00 0.003 0.689 0. 2 49 3. 7 5 0.008 0.690 0.74 7 2.50 0.014 0.692 0.744 3. 7 5 0.017 0.693 0.743 | (c) M _" 0 . 751, a = 1 . 99° , Rec ,_ " 3 . 9 X 10 6 .

F ig u re 13.- Con t i nu e d .

• 20 I V i i o - RIRFOIL UPPER SURFRCE X / O Op P / PT M .., NRC£ 0012 £[RFOIL 0.000 1.110 0,988 0.133 , 0.025 -0,422 0.562 0,945 , , - x .s 0,050 -0,498 0.541 0.979 0 075 -0.781 0.4B3 1.110 0 100 -0.865 0.439 1.151 o o o 0 150 -0.944 0,417 1.191 ." -I.o o 0 200 -1.023 0,396 1,232 o o 0 250 -1,067 0,383 i,255 M 0 300 -1.108 0 . 372 1.2 7 8 ---C 0 - , v r o o I 0 350 -1.133 0.365 1 292 0 400 -I.142 0.362 i 297 o 0 450 -0.582 0.518 1 017 _e - 0 . 5 o o o o I 0 @ o - Cp o.o ....... _ 500 -0.406 0.567 0 939 a " Oa Oo, 0 550 -0 . 288 0.599 0 887 0 600 -0.203 0.623 0 850 0 650 - 0.168 0.633 0 835 , o .s 0 7 00 -0.098 0.652 q 800 0 750 -0,094 0,654 0 804 0,800 -0,041 0,668 0 " 1 s.o 0,850 0 029 0,6e8 0 7 52 L ; 0 900 0 064 0 69 7 O 7 36 t ' • • , i _ 0,930 0 099 0,70 7 0 7 22 I _._ ..... 0.950 0 t34 0.717 O 707 { o.o 0 . 2 0.4 0 . 6 o.8 I .o 0,980 0 1 7 6 0 , 7 2d 0 688 X / O 1.000 0 209 0. 7 3 7 0 6 7 4 'i SIDENRLL , Z / C = 1.3 7 5 I !

o- RIRFOIL LON ER SURFRC E X / C Cp P / PT M p , -2 50 -0.013 0.679 0.763 X / C Cp P / PT M -3 7 5 0.028 0.690 0. 7 47 1 0,025 0,;35 0, 7 19 0, 7 03 -2 O0 -O.OtO 0.680 0. 7 63 _ 0,050 -0.1t5 0,64 7 0,813 -! 50 0.001 0.633 0. 7 59 _ , 0.100 -0,343 0,584 0,911 -1 O0 -0.043 0.671 0.7_7 i ; 0,200 -0,4 7 8 0,550 0,965 -0 50 -0,095 0.656 0.799 0.300 -0,459 0,552 0,962 0 O0 -'0.029 0.675 0. 7 72 0,400 -0.365 0.581 0,915 0 50 -0.064 0.655 0.786 t 0,500 -0.296 0.597 0,890 ! O0 -0.030 0.674 0. 7 72 0,600 -0,205 0.625 0.847 1 50 0.010 0.635 0.755 0. 7 00 -0,125 0,645 0,817 2 O0 -0.002 0.682 0.760 0,800 -0,047 0,669 0.780 2 50 -0,002 0.682 0,760 I 0.850 0 . 009 0.682 0.750 3 75 0.023 0.699 0,74 9 ' 0,900 0.060 0,699 0. 7 35 0,930 0,098 0, 7 0 7 0, 7 22 0.950 0,128 0, 7 17 0.706 SID E WRLL, Z / O =-1.3 7 5 0.980 0,180 0.730 0.6 8 7 X / C Op P / PT M : -3. 7 5 0.03 7 0.693 0. 7 44 S ID E NRLL , Z - 0 -1.00 -0.016 0.6 7 8 0 . 76_ _ 1 0 Op P I PT M -0.50 0.135 0.720 0. 7 02 i 0.00 - 0,016 0.6 7 8 0.76_ -3.75 0.047 0.694 0.741 0.50 0.014 0.686 0 . 753 ' -3.00 0.006 0.681 0. 7 62 1 . 00 -0 . 020 0 . 677 0 .7 58 -1 . 25 0 . 05 7 0.697 0. 7 37 !.50 0.005 0.684 0. 7 57 1.25 0.033 0.690 0, 7 47 2.00 -0.011 0.679 0. 7 64 3. 7 5 0.051 0.695 0.740 2.50 0.013 0.686 0. 7 54 3.75 0,031 0.691 0.746 e (d) M = = 0 2 59, a • 2. 0 5" , R ec, . • 6 . 3 X 1 0 6 .

Figure 13.- C ont _ ued.

__ I i I,, ' _ . =_ ......--_,,.,_ ,, % --"'_'- ..... - - . _ , _ " I J, ,!

o - RIRFOILUPPER SURFACE

NRCRO012 RI RFO I L x / c Op P / PT M

0 000 1 068 0 978 0.i 7 9

0 025 -0 557 0 537 0.986 - 1.s , 0 050 -0 7 59 0 482 1 . 0 7 6 0 075 -0 896 0 445 1.141 o o o 0 100 -0 961 0 427 1.173 o (' 0 150 -I 047 0 404 1,216 -1.0 o o 0 200 -1.123 0 383 1.256 o 0.250 -I 153 0 375 1,2 7 1 w 0.300 -I 195 0 364 1.294 -0.s_-Cp e 0.350 -I 222 0 356 1.309 o o o o 0.400 -I 0 7 8 0 396 1.232 ' o a o 0.450 -0 547 0 540 0.982 Op 0.0 _ - 0.500 -0 388 0 583 0.913 ' Io " _°oo 0.550 -0 283 0,611 0.869 0 600 -0 229 0 626 0.846 o.s" _............... O 650 -0 185 0 638 0.828 0 700 -0 140 0 65n n o-_ 0 750 -0 097 0 F( , 2 _.79[ 0 800 -9 045 U 676 0. 7 69 1.0_ 0 850 0 005 0 689 0.749 0.900 0 056 0.703 0.727 I 0 . 925 0 09 7 0.7 1 4 0. 7 10 i 1.s ...... 0,950 0 130 0. 7 23 0.696 i o.o o.2 0.4 o._ o.a i.o 0.975 0 185 0.738 0.673 X / C 1.000 0 244 0.754 0.648 5[O£NALL , Z / C" 1.375 o - RIRFOIL LONERSURFRCE X / C Op P / PT M i X / C Cp P / PT M -3. 7 5 0.031 0.69 7 0.7 c7 , -2.50 -0.008 0.686 0. 7 53 ; 0,025 0,209 0. 7 45 0.662 -2.00 -0.013 0.685 0. 7 55 t i 0.050 -0,032 0,679 0,764 -1.50 -0.012 0.685 0.755 0.100 -0.267 0.616 0.862 -1.00 -0.023 0.682 0.760 1 0.200 -0.394 0.582 0.9t5 -0.50 -0.041 0,677 0,767 _ 0,300 -0.393 0.581 0.916 0.00 -0.021 0.683 0.759 ; 0.400 -0.316 0 . 603 0,881 0.50 -0.037 0.679 0.765 i 0.500 -0.256 0.618 0.858 1.00 -0.003 0.688 0.75] 0.600 -0.181 0.640 0.825 1.50 0.02] 0.694 0.741 i 0.700 -0.112 0,658 0. 7 9 7 2.00 0,119 0. 7 21 0.700 _ ' " 0.800 -0.041 0.678 0.767 2.50 -0.008 0.687 0.752 9.850 0.007 0.690 0.746 3.75 0.025 0.695 0.739 i 0.900 0.068 0. 7 0 7 0.721 0.£25 0.096 0.714 0.710 0.950 0.131 0.724 0.695 SIDEWRLL , Z / C"-1.375 : 0,975 0.177 0.736 0.676 X / O Cp P / PT M 51OEWALL , Z-0 -3.75 0.040 0,700 0.733 -1.00 0.010 0.69] 0. 7 46 X I O Cp P I PT M -0.50 0.014 0.692 0.744 0.00 0.002 0,689 0.749 -3.75 0.051 0.702 0.729 0.50 0.00 7 0.69] 0. 7 47 -3.00 0,007 0,690 0. 7 48 1.00 0.008 0.69] 0.746 -1.25 0.054 0.703 0,728 1.50 0.015 0.693 0,744 1.25 0.030 0.697 0. 7 38 2.00 0.011 0.692 0.745 3. 7 5 0.02! 0.694 0.741 2.50 0.027 0.696 0. 7 38 3 . 75 0.031 0.69 7 0.737 ( e) iW'_ • 0 . 7 5 I , a • I .gg', Re¢,_ - 7 .gXI 0 6 .

F l l l U _ 1 3.- C ont _m d .

t o - AIRFOIL UPP E R SURFACE

NRCRO012AI RFO I L x / c Cp P / P T M

0.000 1.060 0.976 O . ]87 0 . 025 -0 . 532 0 . 543 0 . 976 -l . s 0 . 050 - 0.739 0.487 1.068 0.075 -0.904 0 . 442 1.146 !

, o o o 0.i00 -0.970 0 . 424 1 178 -1 . o ou 9 ' 0.150 -1.057 0.400 1.222 0 . 200 -1.133 0.380 1.263 o w 0.250 -1.158 0.3 7 3 1.2 7 6 0.300 -1.200 0.362 1.299 1 -o .s -n-- C_ 9 r 0.350 -1.224 0.355 1.312 [] o 0 . 400 -1.086 0.393 1.237 0 0 0 o 6 o 0.450 -0.553 0.53 7 0.985 Ca c.o o ...... 0.500 -0.388 0 . S P _ 3.5. ' i °•o a 0 . _50 -0.2 7 3 0.612 0.868 " _ O.600 -0.225 0.626 0.846 0.650 -0.184 0.638 0.826 0.5 0.700 -0.139 0.650 0.809 0.750 -0.094 0.662 0.791 0.800 -0.042 0.676 0.769 ; 1 . o 0.850 0.009 0.690 0. 7 48 j 0.900 0.063 0. 7 05 0. 7 25 0.925 0.099 0. 7 15 0. 7 10 j • l . s , , - ' , .... , - , 0.950 0.133 0. 7 24 0.696 o.o 0.2 0 . 4 o . s o. e .o 0.975 0.189 0. 7 39 0.6 7 2 X / O 1.000 0.249 0. 7 55 0.646 SIDEWALL , Z / C" 1 . 3 7 5 o- AIRFOIL LOWER SURFRC£ X / C Op P / P T M X / C Cp P / PT M -3.75 0.035 0.697 0.736 - 2.5O -0.014 0 . 684 0 . 7 57 0.025 0.228 0. 7 49 0.655 -2.00 -0.012 0.685 0. 7 56 0.050 -0.009 0.685 0.755 -1.50 -0.008 0.685 0.755 0.100 -0.253 0.619 0.857 -1.00 -0.048 0.675 0.771 0.200 -0.384 0.583 0.912 -0.50 -0.096 0.662 0.791 0.300 -0.380 0.584 0.9ti 0.00 -0.058 0.672 0.776 0.400 -0.306 0.604 0.880 0.50 -0.071 0.669 0.78!

0.500 -0.251 0.619 0.856 1.00 -0.019 0.683 0.759 0.600 -0.175 0.640 0.82 1 1.50 -0.001 0.686 0.752 ,_ 0.700 -0.106 0.659 0.796 2.00 -0.009 0.685 0.755 0.800 -0.035 0.678 0.766 2.50 -0.003 0.687 0.752 0.850 0.012 0.691 0.747 3.75 0.027 0.695 0.740 ; 0. 9 00 0.070 0. 7 0 7 0.722 0.9 2 5 0.09 8 0. 7 14 0 . 710 I 0.95 0 0,133 0,721 0. 69 5 SI D E W A LL , Z / O" -1, 3 75 0 . 9 7 5 0.1 7 9 0. 7 36 0. 6 7 6 R I O Cp P I PT M 5 1DEWALL, 2 m 0 -3.75 0.045 0. 7 00 0.733 t -1 . 00 -0.004 0. 6 8 7 0. 7 53 _ / C C p P I P T M -0.50 0 . 0 19 0 .69 3 0 . 74 3 I -3.75 0 . 05 7 0 . 70 3 0 .728 0 . 00 0 .0 04 0 .689 0 . 7 5 0 ; -3 . 00 0.01 0 0. 690 0.747 0 .5 0 -0.00 5 0 .6 8 6 0. 7 5 3 1 . 00 -0.004 0. 68 7 0. 7 5 3 I - 1 .2 5 0.05 9 0.704 0.727 1 .25 0 . 0 3 4 0 .69 7 0 . 7 3 7 1 . 50 0. 0 2 0 0 .693 0.7t 3 i 3. 75 0 . 027 0. 6 05 0 . 74 0 2. 00 0 . 0 1 4 0.692 0 . 745 • 2 . 50 0 . 0 3! 0 .696 0 . 7 39 3. 7 5 0. 0 36 0 .69 7 0. 7 36 I (OM .- o _ s i , = - 1. 99 " , a _ . - _S , , I( P.

Fl l l U m 1 3 .- Cem e imu_ l.

2 3 " ' ,L ............ III IIIIII ii i ......................... _ b _ o - RI R FOI L U PPE R SU R FAC E

NRORO012 8 1RFO I L x / c Cp P / P T M

0.000 1.061 0 976 0.185

0 02_ -0.539 0 5_4 0.975

t ., -2,s .... 0 050 -0. 7 48 0 48 7 1.068 0 075 -0.916 0 442 1.147 , 0 150 -1,0 7 2 0 400 1.224 -l.o o ° o _ o o o 0 100 -0,983 0 424 1.1 7 9 0 200 1.148 0 3 7 9 1.264 i o . 0 250 -1.1 7 6 0 3 7 I 1.2 7 9 -0.s!_--C_ . o 0 300 -1.219 0 360 i.302 ' o ] o . 0350 -1.243 0353 l.J,6 o 1 o o I 0 400 -1.215 0 361 1.300 o @ o _ 0 450 -0.585 0 53! 0.995 ;' Op 0 . 0 ..... 0 5nO -0.408 0 5 7 9 0.919 _ _ '_ _:_ a.289 0.611 0.869 o oa,,=l o 5 _, ';" 0,232 0.62 7 0.845 O . _J .... = .............

-_ ; 3. / UO - -0 . 1 44 0 . 650 5.80u

i '.°, l 0.800 -o.o 8o.szz

: 0.925 0 . 094 0. 7 15 _. 7 10 s.s • , 0.950 0.128 0. 7 24 0.595 o.o 0.2 o.4 o. s o.e s . o 0 . 9 7 5 0 . 185 0 . 7 39 0.6 7 1 X l O 1.000 0.24 7 0 . 7 56 0.645 SIDEWRLL , Z'C = 1.375 o - RIRFOIL LO_ER SURFRC£ X / C Op P / P? M -2 . 50 -0.022 0.684 0.75 7 1 X / C Cp P / PT M -3. 7 5 0.029 0 . 698 P. 7 36 0,025 0.231 0, 7 53 0.650 -2.00 -0.021 0.684 0.756 0,050 -0.01 7 0.685 0,756 -1.50 -0.019 0 685 0. 7 56 0.100 - 0.263 0.618 0.858 -1.00 - 0.059 0 6 7 4 0. 77 2 ; 0,200 -0.392 0,58{ 0.911 -0.50 -0.104 0 662 0. 7 91 : . 0.300 - 0.3 9 0 0.584 0 . 911 0.00 - 0.054 0 6 7 6 0. 77 0 : 0.400 -0.314 0.605 0.878 0.50 -0.080 0 668 0.781 0.500 0.619 0.85 7 1.00 - 0.027 0 683 0.759 { 0.600 - 0, 18 _ 0.641 0.824 1.50 -0.012 0 68 7 0.753 0.700 -0. 1 15 0.658 0. 7 96 2 . 00 - 0.018 0 685 0 755 , 0 . 800 -0 . 043 0.6 7 9 0. 7 65 2.50 -0 . 009 0 688 0. 7 5] , i 0 . 850 0.005 0 . 691 0. 7 47 3. 7 5 0.020 0 696 C. 7 39 ' 0,900 0.062 0, 7 0 7 0, 7 22 0 . 925 0.092 0, 7 14 0, 7 10 0. 9 5 0 0.126 0. 7 24 0.6 9 5 5 [ O E NRLL. , Z / C- -1.3 7 5 : 0. 9 75 0.1 7 4 0. 7 37 0. 6 76 X / C C p P / P T H SID E WALL , Z-0 -3.75 0.03 8 0.700 0. 7 3 2 - I.O0 -0.013 0.68 7 0 . 7 53 X / O O R P / PT M - 0.50 0.012 0.693 0 . 742 - 3. 7 5 0.051 0.703 0 . 7 2 7 0 . 0 0 - 0 . 0 03 0 . 6 8 9 0. 7 49 - 3.00 0.003 0. 6 90 0. 7 47 0.50 -0.012 0. 68 7 0. 7 53 - 1 25 0.053 0.704 0.726 1 ,00 -0 . 01 2 0, 68 7 0. 7 52 " 1.50 0.013 0.694 0.742 1.25 0.028 0. 69 7 0. 7 3 6 3 75 0.0 22 0. 69 6 0.739 2.60 0.00 8 0. 6 92 0. 7 44 " 2 .5 0 0 . 02 3 0 .696 0 . 73# 3. 75 0 . 0 28 0 . 69 8 0 . 7 36 = M.. 0 .7 4 9 , = - 2. oo ', Rec , - - sI._ x so'.

Filu m 13. - Co r . _ nu _ I.

% o - RIRFOIL UPPER SURFRCE

" • NRCRO012 RI RFO I L x / c gp P / PT N

. 0.000 1.053 0.9 7 5 0.192 0.025 -0,554 0.54! 0.980 -1.5 0 . 050 -0 . 750 0.488 1 . 067 0.075 -0.9]7 0.443 1.144 o o o 0 . 100 -0 . 985 O,d2d 1 . 1 7 8 o 0 . 150 -1.0 7 0 0 . 402 1.220 - -I.0 o_ 0.200 -I.149 0.380 1.261 o M 0.250 -1 . 174 0 . 37d 1 . 27d 0.300 -I,234 0.357 1.307 _ e -o . s-c-Cp o 0.350 -1.239 0.356 1.310 Q 0 o o o 0.d00 -I.]42 0 . 382 1 . 25 7 o B o 0.450 -0.546 0.543 0.976 : Op 0.0 [] = 0.500 -0.373 0.590 0.902 aoo_ 0.550 -0.2 7 6 0.616 0.862 o 0.600 -0.231 0.628 0,843 o.s 0.650 -0.195 0.638 0.828 0.700 -0.148 0.650 0.809 0.750 -0.103 0.663 0.790 0.800 -0.049 0.677 0.768 - 1 . o 0.850 0.003 0.691 0.7_" '_,i 0.900 0.057 0.706 0.72. : 0.925 0.094 0.716 0.70E i_ 1.s .... U,950 O.128 0.725 0.69d o.o 0.2 0 . 4 o._ O.B .O 0.975 0.186 0.741 0.669 = X / O 1.000 0.251 0.758 0,641 • SIDENRLL, Z / C = 1.3 7 5 :! []- RIRFOIL LONER SURFRCE X / O Op P / P T M i X / C Op P / PT M -3.75 0.033 0.698 0.736 -2.50 -0.022 0.683 0. 7 58 0,025 0,232 0, 7 52 0,651 -2.00 -0.021 0.683 0. 7 58 !

0,050 -0,019 0,685 0, 7 55 -].50 -0.021 0.683 0.758 ' O,lO0 -0.23_ 0,619 0.857 -1.00 -0.024 0.682 0.759 ; 0,200 -0,394 0.583 0,913 -0,50 -0,040 0,678 0, 7 66 0,300 -0,390 0,585 0.910 0.00 -0.007 0.687 0.753 0,400 -0,314 0.604 0,880 0.50 -0,041 0.678 0, 7 66 : 0,500 -0,259 0,620 0,855 1.00 -0.004 0.688 0. 7 51 ' 0,600 -0,183 0,640 0,825 1,50 0,025 0,696 0. 7 39 0, 7 00 -0,]14 0,659 0, 7 95 2.00 0.035 0.698 0.735 0.800 -0,041 0,678 0, 7 66 2,50 -0,005 0,688 0,75] 0,850 0,005 0,692 0, 7 45 3.75 0 027 0 696 0 738 0,900 0,066 0, 7 0 7 0. 7 21 ' ' ' 0,925 0,094 0. 7 16 0, 7 08 0.950 0.130 0. 7 24 0.695 SIO E NRLL , Z / C = -1 . 3 7 5 .. 0,9 7 5 0,1 7 9 0, 7 39 0.6 7 2 X / O Cp P / PT N SIDEWRLL, Z = O -3,75 0,0d2 0 7 00 0.732 : X / O Op P / PT N -0.50 0 014 0 693 0. 7 44 -3,75 0.054 0.704 0,726 0.00 -0 002 0 688 0.750 -3.00 0.005 0.692 0.745 0.50 0 007 0 69] 0.746 i -1.00 0 007 0 69] 0. 7 46 j -1,25 0.055 0.704 0.726 ].00 0 004 0 690 0. 7 48 1.25 0.031 0.698 0. 7 36 1.50 0 01 7 0 693 0.742 i 3,75 0,024 0 696 0.739 2.00 00tO 0,692 0. 7 45 "-_ " 2.50 0 026 0.696 0. 7 39 ¢ ! 3.75 0 . 032 0.698 0. 7 36 , ( h ) M _" 0 . 7 4 7 ,a ffi 2.010 , Rec , . = 1 3 , 9X l0 e.

Fig u re 1 3.- Con c l u ded.

2 5

•

" . o - RIRFOIL UPPgR SURFflCg

NRCR O012 RI RFO I L x / c cp P / PT M

0 . 000 1.1{6 0 . 999 0,032 _ " 0,025 -0.130 0.654 0.803 -i.s _ 0.050 -0.392 0.583 0.914 0.075 -0.535 0.544 0.9 7 5 0.100 -0.579 0.532 0.994 -l.o .... 0.150 -0.711 0.496 1 . 053 0.200 -0.664 0.509 1.031 __o 0.250 -0.613 0.523 1.009 _osl---_ _ o _ _ _ 0.300 -0 , 556 0.538 0.984 ' _ " e _ _ o 0.350 -0.489 0.556 0.955 o o 0.400 -0.424 0.574 0.927 • B c _ o 0.450 -0.382 0.585 0,909 , Op o . o" _ 0.500 -0,328 0.600 0 . 687 _°oo 0.550 -0.274 0.615 0.864 0.600 -0.232 0.626 0.846 - o.s 0,650 -0.185 0,639 0.826 1 0.700 -0.138 0.652 0.80 7 } - 0 . 7 50 -0.092 0.664 0.788 !

1.o I 0,800 -0.0{2 0.677 0.76 7 , 0.850 O,OU7 0,691 0.746 i :: (' 0.900 0,063 0. 7 06 0. 7 23 =_ 0.925 0.097 0.715 0 .7 09 _. 1.s. , J , .... _ - , t , - 0 . _50 0.I33 0. 7 25 0.694 o,o 0. 2 o_ .s o.A .o 0 . 975 0.182 0 .7 38 0 . 673 : X / D 1.000 0.231 0. 7 52 0 . 652 : [ S[OEXRLL, Z / C = 1 . 3 7 5 o- RIRFgIL :ONER SURFRCE X / C gp P / PT M X / C Cp P / PT M -3.75 0.037 0.700 0 7 33 i -2.50 - 0.001 0,690 0 7 48 0.025 -0,!83 0 _40 0.825 - 2.00 0.008 0,692 0 7 45 -- 0.050 - 0,422 0 575 0.926 -1.50 0.014 0.694 0 7 42 i 0 . 100 - 0.632 0 518 1 017 -1.00 -0.017 0.685 0 755 0.200 - 0,688 0 503 1 041 - 0.50 - 0.033 0.681 0 762 i 0.300 -0,565 0 536 0 988 0.00 - 0.065 0.685 0 750 0.400 -0,428 0 574 0 9 2 7 0,50 -0,018 0.685 0 755 0,500 -0.329 0 600 0 88 7 1 , 00 0.028 0.698 0 736 0.600 -0.208 0 633 0 835 1,50 0,001 0.690 0 748 0.700 -0,138 0 651 0.807 2,00 -0 , 036 0.680 0 763 0,800 -0.05I 0 6 7 6 C. 77 0 2,50 -0,020 0.68{ 0 7 56 0,850 0 , 005 0 690 0,7_8 3. 7 5 0.032 0.698 0 7 35 0,900 0.06 7 0 7 0 7 0. 7 21 0,925 0,!00 0 713 0.708 0.950 0 . 134 0 7 26 0.693 SIDENRLL , Z / g = - 1 . 375 ' 0.975 0.1 7 7 0, 7 37 0.675 X / O Op P / PT M SIOE_ALL, Z = 0 -3,75 0.034 0.699 0. 7 34 - 1.00 -0.024 0,683 0, 7 58 X / O gp P / PT M -0.50 - 0.005 0.688 0 ,7 50 -3. 7 5 0.04q 0 703 0 728 0.00 -0.030 0.682 0.760 " " 0.50 -0.031 0.682 0,761 -3.00 0.004 0.690 0. 7 48 1.00 -0.012 0.68 7 0. 7 53 -1 . 25 0.051 0 . 7 03 0 . 7 27 1.50 0 . 002 0 . 690 0 . 7 4 7 1.25 0 . 028 0.607 0.73 7 3.75 0.015 0.694 0.742 2.00 -0.003 0.689 0. 7 49 .

2.50 0.012 0.693 0. 7 43 3. 7 5 0.019 0.695 0. 7 40 ( a ) M _ = 0 , 7 _ 2 , e = -0.02 °, Rec , _ = 4.0 X l Os .

| Figure 1 4 . - Ai r_ and test _h anne l s idewall pressuremea s urement s, Data S et 2 ( MN = 0.75, _ N = 0°)" - . o - RIRFO[L UPPgR 5URFROE

, NRCRO012 RI RFO I L x / o Cp P / PT M

0 . 000 1,141 0 . 998 0 . 056 0 . 025 -0.124 0 . 655 0.802 . -1.5 _ 0.050 -0,3 7 6 0 . 586 0.908 0.075 -0.513 0.549 0.966 0.100 -0.555 0.538 0.985 0.150 -0. 7 03 ?,497 1.051 -1.o 1 -- 0.200 -0.664 b._38 1.033 ' 0.250 -0.611 0.523 1.0 0 9 -o.s ---§_ o = o 0.350 -0.484 0.557 0.954 i _o 0.300 -0.551 0.539 0.983 ,_ o o o 0.400 -0.41G 0.575 0.925 / _ 0 0 0 o i 0.450 -0.3 7 5 0.586 0.908 Op o.o - 0.500 -0.322 0.601 0.885 _ amo o 0.550 -0.266 0.6;6 0.862 0.600 -0.224 0.628 0.844 0.650 -0.179 0.640 0.825 o.s 0.700 -0.130 0.653 0.805 0 . 750 -0 . 084 0 . 665 0.786 : i 0.800 -0.033 0.6 7 9 0. 7 64 0.900 0.0 7 0 0. 7 07 0. 7 21 1.o I 0.850 0.015 0.692 0.744 i_ l t I I 0.925 0.106 0. 7 :7 0. 7 06 1,5 . , , , , 0.950 0.140 0.725 0.692 ; _ o.o 0.2 0.4 o.s 0 . 8 1.o 0.975 0.192 0.740 0.6 7 0 X / C 1.000 0.245 0. 7 55 0.647 - c S[DCNRLL, Z / 0= t.375 ' "! o- RIffFOIL LONER $LIRFRCE X / O Op P / PT M -_ X / C Cp P / PT M -3. 7 5 0.03 7 0.700 0. 7 33 ] -2.50 0.000 0.690 0.748 0.025 -0.]66 0.645 0.81 / -2.00 0.011 0.693 0. 7 44 : 0.050 -0.387 0.583 0.913 -1.50 0.022 0.695 0.739 --I 0.]00 -0.599 0.526 1.004 -I.00 -0.009 0.887 0, 7 52 0.200 -0.665 0.510 1.030 -0.50 -0.026 0.683 0. ? 59 0.3 0 0 -0.556 0.53 7 0.985 0.00 0.007 0.692 0.745 i 0.400 -0.411 0.578 0.920 0.50 -0.01! 0.687 0. 7 53 0 .600 -0.!94 0.63 7 0.829 1.50 0.009 0.692 0. 7 45 • 0 . 7 00 -0,128 0 . 653 0 . 804 2.00 -0.027 0.682 0. 7 60 i 0.500 -0.318 0.602 0.883 ].00 0.036 0.699 0.733 0,800 -0,043 0.6 7 8 0,766 2.50 -0,012 0.686 0. 7 53 t 0,850 0.013 0,692 0.745 3.75 0 040 0.700 0. 7 32 | 0,900 0,0 7 6 0, 7 10 0.71 7 0 . 925 0,109 0 , 718 0.705 0,950 0.143 0, 7 28 0,689 SIOENRLL , 2 / C=-1.375 0.9 7 5 0.189 0, 7 39 0.6 7 1 X / O Cp P / PT M SIOENAL!,,Z=O -3.75 0 039 0. 7 00 0. 7 32 -].00 -0 015 0.685 0. 7 55 X / O Cp P / PT M -0.50 0 004 0.69] 0. 7 47 -3. 7 5 0.052 0.703 0.728 0.00 -0 01 7 0,685 0. 7 55 -3.00 0.009 0.691 0.74 7 0.50 -0 024 0.683 0.758 1.00 -0 005 0.688 0. 7 50 t -1.25 0.059 0.705 0. 7 25 1,EO 0,011 0.693 0. 7 44 1.25 0.037 0.555 0.734 2.00 0,005 0.691 0, 7 46 3.75 0.024 0.696 0. 2 39 2,50 0.020 0.695 0, 7 40 ; _. 7 5 0.028 0,69 7 0. 7 3 7 ' i (b) M . = 0.75 0 , a = -0. 02 ° , Rec , . = 6. 0 X 10 e.

Figur e 14. - Continu e d.

_ - . ., r] r o - RIRFOILUPPER SURFRCE

,, NRCR 0012 RIRFOIL x / o Cp P / P T M

o ooo i.i 5 o ].oo; o.oo0

, , 0 025 -0.115 0.659 0.796 , -1.5 0 050 -0.3 7 3 0 . 589 0.903 0 075 -0.520 0 . 549 0.966 0 100 -0 . 56d 0.538 0 , 985 0 150 -0.7]7 0.d96 1.053 -i.0 0 200 -0.680 0.506 1.036 0 250 -0.626 0.521 1.012 : ____ ,o o 0 300 -0.563 0.538 0.985 -o.s , o o I 0 350 -0 . d97 0.556 0 . 956 I 0 dO0 -O.d2d 0.575 0.925 @ 0 d50 -0.383 0.586 0.907 _ @ ° Q o _ o o o _ Op o.o" , s 0.500 -0.329 0.601 0.885 0.550 -0.272 0.616 0.861 m_=°' 0.600 -0,230 0.628 0.843 o.s 0 . 650 -0.185 0.640 0.82d 0. 7 00 -0.133 0.65d 0.803 ,: 0.750 -0.088 0.666 0.78d ; 0,800 -O.03d 0.681 0.762 1.0 0,850 0.015 0.694 0.742 I 0.900 0 . 0 7 0 0. 7 09 0.718 0.925 0.107 0. 7 19 0. 7 03 ].s ..... 0.950 0.141 0.728 0.689 o.o 0.2 o._ 0.6 o.8 .o 0.9 7 5 0.198 0.743 0.665 X / C l.O00 0.25d 0,759 0.641 SIDEWRLL , Z / C= 1.375 o- RIRFOILLOWERSURFflCE X / C CR P / PT M -2.50 -0,005 0 689 O, 7 d9 i X / C Cp P / PT I"1 -3. 7 5 0.032 0 699 0. 7 34 0 025 -0 53 0 648 0,812 -2,00 0 008 O 693 0. 7 43 0 050 -0 384 0 586 0,908 -i,50 0 021 0 696 0. 7 38 ; 0 100 -0 609 0 526 t.on4 -1.00 -0 010 0 688 0. 7 51 0 200 -0 695 0 50;' 1.0t3 -0.50 -0 02 7 0 684 0. 7 58 : 0 300 -0 566 0 53 7 0,986 0,00 00tO 0 693 0.743 -, 0 400 -0 419 0 5 77 0.923 0.50 -0 012 0 688 0. 7 52 _, 0 500 -0 324 0.602 0.883 1.00 0 03 7 0 701 0. 7 31 0 600 -0 i95 0.637 0.829 1.50 0 015 0 695 0. 7 40 I 0 700 -0 132 0.654 0.803 2.00 -0 028 0 683 0.758 0 800 -0 042 0.679 0.765 2.50 -0 010 0 688 0, 7 5] ' 0 850 0 013 0.694 0.742 3.75 0 Od] 0 702 0,730 0 900 0 0 7 9 0 , 7 11 0 , 715 0 925 0 109 0, 7 t9 0, 7 02 0 950 0 14 7 0. 7 29 0.687 SIOEWRLL , Z / C=-1.3 7 5 0 9 7 5 0 193 0, 7' t2 0,667 X / C Op P / PT N SIOEWRLL , Z = O -3. 7 5 0 038 0. 7 01 0. 7 31 -1.00 -0 018 0.686 0.754 X / O Op P / PT N -0.50 0 00'1 0,692 0. 7 '15 ' -3.75 0.049 0. 7 04 0. 7 26 0.00 -0 020 0.685 0, 7 55 0.50 -0 018 0.686 0.754 -3.00 0.00`1 0.691 0. 7 46 ].00 -0 006 0.689 0. 7 '19 -t.25 O.06t 0.707 0.721 1.50 0 012 0.694 0,742 t.25 0.038 O. 7 0t 0.731 2.00 0 005 0.692 0, 7 45 3.25 0.025 0.697 0. 7 36 2.50 0 92] 0.696 0.738 ; 3. 7 5 0. 0 29 0.699 0,734 ( c) M . =0. 7 48, a = -0.02 ° , R ec ,, = 7 .8X I 0 6 . i F i gur e 14 .- Con ti nu e d .

2 @ • l 'i . o- RIRFOILUPPER5URFRCg

NRC£ O012 RI RFOI L x / o Cp P / P3 M i

0.000 1 .145 0.999 0.042 0 025 -0.101 0 660 0. 7 94 0 050 -0,365 0 588 0.905 _': -t.5j r 0 075 -0,509 0 549 0.962 ' I 0 100 -0.551 0 537 0.986 -1.o I 0 150 -0.699 0 497 1.052 0 200 -0,655 0 509 1 , 032 0.250 -0,605 0,522 1.010 i -0 . s ___Q _o o o 0 , 300 -0,544 0.539 0,983 -' _ 0 . 350 -0.4 7 8 0 . 557 0.954 ! o o a o 0.400 -0.407 0 . 576 0.924 0,450 -0 367 0,587 0,906 _ O0 0 • .i Op o.o _ 0.500 -0.315 0.601 0.884 :! °oao 0 . 550 -0,258 0,6]7 0,860 , 0.600 -0.21 7 0.628 0.843 0.5 0.650 -0.172 0.640 0.824 0.700 -0.121 0.654 0.803 0.750 -0.075 0.667 0.784 0 . 800 - 0 . 023 0 . 681 0 . 7 62 ' 1.o 0.850 0.026 0.694 0. 7 4[ 0.900 0.080 0.709 0.719 0.925 0.116 0,719 0,704 1 .5] , , I . 0.950 0.150 0.728 0 . 689 _.o o.2 o.4 o.6 o.e _.o 0.9 7 5 0.206 0. 7 43 0.665 X / C 1.000 0.265 0.759 0.640 SIDENRLL, Z / C= 1.3 7 5 o - AIRFOIL LONER SURFACE X / O Op P / PT M X / C Cp P / PT M -3. 7 5 0.045 0.699 0. 7 33 .

-2.50 0.006 0.689 0. 7 50 0.025 -0.133 0.651 0.808 -2.00 0.019 0.692 0. 7 44 0.050 -0.364 0.588 0 . 905 -].50 0.032 0 . 696 0.739 i 0.100 -0.586 0 . 528 1.001 - 1 .00 0.002 0.688 0. 7 52 0.200 -0.655 0.509 t 031 -0.50 -0.016 0.683 0. 7 59 0.300 -0.544 0.539 0 £83 0.00 0.024 0.694 0. 7 42 ; 0.400 -0.399 0.579 0 920 0.50 0.000 0.68 7 0.752 0,500 -0.30 7 0.603 0 881 1 . 00 0 . 050 0. 7 0_ 0.731 0.600 -0.180 0.639 0 82 7 1.50 0.029 0.695 0.740 I . : 0. 7 00 -0.1t8 0.655 0 802 2.00 -0.016 0.683 0.759 i - 0.800 -0.031 0.6 7 9 0 7 65 2.50 0.001 0.688 0. 7 52 0.850 0.023 0.693 0 7 43 3. 7 5 0.053 0 7 02 0. 7 30 0.900 0.088 0.711 0.715 ' 0.925 0.119 0.719 0.702 0 . 950 0.156 0. 7 30 0.686 SIDENALL, Z / C_ -1.3 7 5 0.975 0.203 0. 7 42 0.66 7 X .' O Op P I PY M SIDEWALL , Z _ O -3. 7 5 0 . 049 0. 7 01 0 . 7 32 -1.00 -0.004 0.686 0. 7 54 X / O Cp P / P T M -0.50 O.Ot6 0 . 692 0. 7 45 -3. 7 5 0.061 0.704 0.727 0.00 -0.00 7 0.685 0. 7 55 -3,00 0.014 0.69] 0. 7 46 0 50 -0.008 0 . 685 0. 7 56 -1.25 0.0 7 2 0. 7 07 0. 7 22 1 O0 0.006 0.689 0. 7 50 t.25 0.050 0.701 0.73 1 I 50 0.024 0.694 0.742 3. 7 5 0.037 0.69 ? 0. 7 37 2 O0 0.016 0.692 0.745 2 50 0,032 0.696 0.739 3 7 5 0.041 0.698 0. 7 35 (d) M _ ffi 0 . 7 5 2 , _ ffi - 0 .0 2°, Rec , _ = 9 . 4X lO 6.

Figur e 14. - Continu e d.

( 29 _ _- o - AIRFOILUPPER SURFPR5

NRCR O012 R IRFO IL x / c Cp P / PT M

0.000 1 .146 0.999 3.037 0.025 -0.I00 0.6613 '9.79b -1.5 , 0.050 -0,365 0.5_ / 0.906 " " 0.075 -0.5i0 0.548 0.969 0.!00 -0.554 0.53C 9.988 0.150 -0.707 0.494 !.056 i -i.0 0.200 -0.668 0.505 1.038 I _o 0.250 -0.6!2 0.520 !.0]3 o 0.300 -0.549 0.537 _].986 i N_ -0.s---_p o _ 0.350 -0.480 0.556 0.955 I o o o o 0.400 -0,410 0.5 7 _ 9.925 0.450 -0.371 0.586 C;.909 o o o Op 0.0 - _ 0.500 -0.318 0.600 0.886 I %o 0.550 -0.26i 0.6I_ 0.862 0 . 600 - 0.21 7 0.62b 0 . 844 0.550 -0.174 0.639 3.825 0.5 0.700 -0.122 0.65_ 0.804 0.750 -0.n 77 0.66,-S 0.785 ! 0.800 - 0.023 6.68_ 0.762 1.0 0.850 0.02 7 0.694 0.742 0.900 0.082 0.70 c ?.718 I 0.925 0 . 116 0.; .... i 3. 7 04 0.950 0.151 0. 7 2_ 0.689 1.5 , _ , oL8 ' o.o o . 2 0.4 0.6 1.o 0.975 0.2]0 0.744 ,].664 , X / C l,OOC 0.2 7 2 0. 7 6L 0.63 7 tt SIOENRLL, Z / C= ! . 375 ;| m- AIRFOIL _ONER SURFACE X / C Cp P , mT M X / C Cp P / PT M -3.75 0.04] 0 699 0 734 i -2 50 0.000 0 688 0 7 5i ' 0,025 -0,134 0.651 C,OO8 -2 O0 0.011 0 6q! 0 747 t , 0,050 -0.360 0.589 0.90_ -1 50 0.025 0 694 0 7 4: I O.lO0 -0.584 0,528 t.OOi -i oo -0.004 0 _97 0 75_ 0.200 -0.663 0.50 7 t.035 -0 50 -0.020 0 632 0 7 6J 0.300 -0.546 0.538 0,98{ 0 oo 0.022 0 694 0 742 0,400 -0.403 0,5 7 8 0,92I 0 50 -0.005 O 696 O ? 54 0,500 -0,308 0,603 0,882 I O0 0.044 0 7 00 0 733 0,600 -0.183 0,638 0,828 ] 50 0,023 0 694 0 7 4_ !

O. 7 0C -0,120 0,654 0,803 2 O0 -0.022 0 682 0 7 bl - _ 0,800 -0,035 0,6 7 8 0,766 2 50 -0,002 0 687 0 7 52 0,850 0,022 0,693 0,743 3 7 5 0,048 0 7 0] 0 7;i < 0,900 0 . 085 O , 7 tO 0 . 7 t6 0,925 0.;20 0, 7 t9 0. 7 02 0.950 0.154 0,729 0,687 SIDEWRLL , Z / C=-1.375 0.9 7 5 0.203 0, 7 42 0.66 7 X / C Cp P / PT M SIDCWRLL,Z = O -3 7 5 0.04 7 0, 7 01 0 7 3_ -1 O0 -0,009 0.685 0 755 X / C Cp P / P? M -0 50 0.013 0.691 0 74S -3. ? 5 0.060 0.704 0.727 0 O0 -O.Ot] 0.685 0 7 5_ -3.00 0.0]3 0.690 0. 7 4 7 0 50 -O.Ot4 0.684 0 7 57 ] O0 0.000 0.688 0 751 -1 . 25 O . 07t 0 . 707 0.722 ! 50 0 , 021 0 . 693 0 743 t.25 0.048 0. 7 0I 0.732 2 00 0.009 0.6gO 0. 7 48 3 . 7 5 0 . 036 0.69 7 0.73 7 2 50 0.026 0.6_5 0. 7 43 i 3 2 5 0.03 7 0,698 0. 7 36 " : ( e) M f O.75 3 , a=. O.O2O , Rec, = 12.2 X i0 6 . 1 ,

, 1

_ Figure14.- Con _ ud _ d.

I

3O ' ' 1 o - AIRFOILUPPERSURFACE

x NRCR OO 12 R IRFO IL x / c Cp P / P? M i

" 0.000 1.203 1.01i 0.000

0.025 -0.044 0.652 0.806 . -1.s| I ' 0.050 -0.3 1 1 0.5 7 5 0.92 5 . 0.0 7 5 -0.475 0.528 1 . 001 , 0.100 - 0.534 0.511 1.029 -l . o - - 0 .1 50 - 0. 7 01 0 . 465 i , 1 ] 0 o B o 0.200 - 0. 7 9 7 0.435 1 . 158 o o 0.250 - 0.840 0.423 1 . 181 _ _, 0.300 - 0.883 0.410 1.204 -o.s ........ 0.350 - 0.929 0.39 7 1.229 BuP 0.400 -0.926 0.398 1.22 7 0 . 450 - 0.876 0.412 1 . 200 D 0 _ o , ° Cp o.o _ .... _ 0.500 -0.85 7 0.418 1.190 .

" : " °_o= 0.550 -0. 7 45 0.450 1.132 0.600 -0.28 7 0.582 0.9 1 4 o.sl 0.650 - 0.172 0.615 0 863 t 0 .7 00 -0.115 0.631 0,838 ; 0 , 750 - 0.0 7 2 0.644 0 819 ' 0.800 - 0.031 0.656 0 80!

_-°I 0 . 850 -0.015 0.660 0794 ; 0.£00 0.061 0.682 0 7 60 !

; 0.925 0.076 0.686 0 7 53 1 . s . , 0 . 959 O. 125 0 . 7 0t 0 731 , _ o.o 0.2 0.4 o.6 e.a 1 . o 0.9 7 5 0.159 0. 7 10 0 7 ] 7 _ { _ X / O l . OOO 0.191 0. 7 20 0 7 02 ' SIDEWALL,Z / C = ! . 3 7 5 : "I D - AIRFOIL LOWER SU R FACE X / O Cp P / P T M i X / C Op P / PT M -3 7 5 0.032 0.6 7 5 0. 77 0 ; - 2 5U -0.00 7 0.664 0. 7 8 7 " '_ 0.025 -0.129 0.629 0 8_1 -2 00 0.003 0.66 7 0. 7 83 l ' 0.050 -0.356 0.562 0 946 -1 50 0.00] 0.66 7 0. 7 84 i :t 0.100 -0.609 0.489 1 064 -1 O0 -0.041 0 . 655 0 . 802 1 , 0.200 -0.833 0 . 427 I 1 7 3 -0 50 -0.104 0.63 7 0.830 _ 0 . 300 -0.924 0.399 1 226 0 00 -0.100 0 . 638 0.828 I 0.400 -0.879 0.414 i 19 7 0 50 -0 . 0 7 8 0.644 0.819 ; !

0.500 -0 . 867 0.415 1 195 1 O0 -0.053 0.651 0.807 ; 0.600 -0.229 0.600 0 886 1 50 -0.042 0 . 654 0.803 !

0, 7 00 -0.095 0.63 7 0 829 2 O0 -0.038 0.655 0.801 ;_ .< 0.800 -0.044 0.654 0 804 2 50 -0.043 0.654 0.803 0.850 0.013 0.668 0 7 81 3 75 -0.026 0.659 0.795 0,900 0 . 056 0.682 0.760 0.925 0.092 0.691 0. 7 46 0.950 0.118 0. 7 00 0. 7 33 SIDEWRLL , Z / C = - 1.3 7 5 I 0.975 0.156 0.710 0.71 7 X / C Cp P / PT M i SIDEWALL , Z=0 -3. 7 5 0,018 0,6 7 2 0, 7 76 -1.00 -0.041 0.655 0 . 802 X / C Op P / P? M -0.50 -0.061 0.649 0 . 811 J - 3 . 75 0.038 0.677 0.768 O.O0 -0.132 0 . 628 0.842 -3.00 -0 009 0 662 0. 7 91 0.50 -0.054 0.651 0.808 " " 1.00 -0.052 0.651 0.80 7 -1.25 0.035 0.6 7 6 0. 77 0 1,50 -0,040 0,655 0.802 1.25 -0.011 0 . 662 0. 7 90 2.00 -0.050 0.652 0.806 3,75 -0.031 0.657 0.799 2.50 0.038 0.656 0.801 3. 7 5 0.329 0.658 0. 7 97 i (a ) M . =0,787 , a = -0 ,I0 ° , Re c , . = 1 .0X I 0 6 .

F ig u r e 1 5 ,- Alr fo fl a nd t e st channel s i d e wall p _u ur e meuu r emen t $ , Da ta S e t 3( MN = 0.80, a N = 0 ° ) .

" I 2w_'' : h { , , , o- RIRFOIL UPPERSURFACE

':" NRCR0012 RIRFOIL x / c Op P / PT M

o.ooo 1.18o 1.oo o.ooo

0.025 -0.036 0.645 0.817 > .-1.5 0.050 -0.293 0.569 0.934 t 0 . 0 7 5 -0.455 0.522 1. 0 11 _ 0.I00 -0,515 0.504 1.040 -I,o _ 0.150 -0.6 7 8 0.456 1.121 o 8 o o @ 0.200 -0. 7 65 0.430 1.167 ' 0.250 -0.811 0.41 7 1 191 7 0 _o.s / R, 0.300 -0.849 0.406 1.212 - : " 0.350 -0.898 0.392 1.239 -- BSp o 0.400 -0.911 0.388 1.24 7 , i, 0.450 -0 . 892 0.393 1.236 " Op o.o: _ o o o _ - 0.500 -0.839 0.409 1,206 0.550 -0.350 0.553 0.961 oo%i 0,600 -0.179 0 , 603 0,882 o.s 0.650 -0.130 0 . 618 0.659 ; 0.700 -0.095 0.628 0.844 : 0.750 -0 . 065 0.637 0.830 0.800 -0.026 0.648 0.812 1.0 ' 0.850 0.009 0.658 0.797 i 0.900 0.975 0.678 0.767 0.925 0,106 0.68 7 0.753 1.5 . . _ • . . 0.950 0.144 0.698 0.735 i "_' o.o 0.2 0.4 o.6 0.a 1.o 0.975 0.188 0. 7 1l 0. 7 15 X / O 1 . 000 0.240 0.726 0.692 SIDENRLL, Z / C = 1.3 7 5 o - RIRFOIL LONER SUR P RC£ X / O Cp P / PT M X / O Cp P / PT M -3. 7 5 0.043 0.669 0. 7 80 -2.50 -0.001 0.656 0. 7 99 0.025 -0.107 0.625 0 847 -2.00 0.020 0.663 0. 7 90 0.050 -0.349 0.553 0 960 -1.50 0.026 0.664 0. 7 8 7 0.100 -0.592 0.481 1 0 7 8 -1.00 -0.015 0.652 0.805 t _- 0.200 -0.799 0.422 1 182 -0.50 -0.080 0.633 0.835 0.300 -0.891 0.393 1 236 0.00 -0.066 0.638 0.82B 0.400 -0.941 0.381 1 260 0.50 -0.053 0.641 0.823 0.500 -0.863 0.402 1 220 1.00 -0.024 0.650 0.810 I 0.600 -0.185 0.602 0 883 1.50 -0.012 0.65? 0.804 0. 7 00 -0.088 0.630 0 840 2.00 -0.006 0.655 0.802 0.800 -0.015 0.652 0 806 2.50 -0.013 0.653 0.805 0.850 0.017 0.661 0 7 93 3.75 0.007 0.659 0. 7 96 0.900 0.081 0.681 0 762 0.925 0.106 0.68 7 0 7 53 0.950 0 . 148 0 . 700 0 732 SIOENRLL, Z l C = -1.375 : 0 . 975 0.183 0.709 0 718 X / C Op P / PT M SIDEWALL , Z= 0 -3.75 0.036 0.667 0. 7 83 -1.00 -0.01 7 0.652 0.806 R / O Op P / PT M -0.50 -0.034 0.64 7 0.814 -3. 7 5 0.04 7 0.6 7 0 0. 77 8 0.00 -0 . I01 0.627 0.844 -3.00 -0.001 0.655 0.801 0.50 -0 . 023 0.650 0.809 l.O0 -0.032 0.648 0.813 -1.25 0.05 7 0 . 6 7 3 0. 7 74 1.25 0.016 0.661 0 .7 92 1 . 50 -0.013 0.653 0.805 3 7 5 0.000 0 656 0.800 2.00 -0.015 0 . 653 0.805 " ' 2.50 -0.012 0 . 653 0.804 3.75 0.004 0 . 658 0 .7 9 7 I _) M _ = 0 _ 0 1, a = ..O . l O° , R ec ,_ " 2. 0 Xl O 6 .

, Figur e15 . - C o nt _ u e d .

-' 32 ...... _ ,_ _ "m_"_"_ " _. ....

, . w ,.. ¢ < - i " J o - RIRFOIL UPPER SURFRCE i

:l NRCR 0012 RIRFOIL x / c Cp P / PT M

j 0.000 1.180 1.003 0.000 _ ' i 0.025 -0.034 0.645 0.81 7 -1.s 0.050 -0.296 0.568 0.937 ] I 0.075 -0.456 0.521 1 . 012 I 0.100 -0.512 0.504 1.039 0.150 -0.6%8 0.155 1,122 -I.0 " o 8 o o 0.200 -0.760 0.431 1.165 0.250 -0.809 0.417 1 192 o 0.300 -0.837 0.409 1 207 ! -o . s R_ o . . i --_'p o 0.350 -0.886 0.394 1 234

o oo

Cp 0.0 _ o o o 0.500 -0.543 0.495 1 064 :I _ o0% 0 . 550 - 0.250 0 . 581 0 915 , 0.600 -0.169 0.605 0 878 ; o.s 0.650 -0.135 0.6t6 0.862 0. 7 00 -0.100 0.626 0.84 7 0.750 -0.067 0.635 0,832 , 0.800 -0.025 0.648 0,813 _ l.o 0.850 0.024 0.662 0,791 _j 0.900 0.079 0.679 0.765 !

0.925 0.1!6 0.689 0,749 L _ 1.s . . . . . 0.950 0.152 0.700 0.732 j o.o 0.2 0.4 o.s o.a 1.o 0.975 0.199 0.714 0. 7 11 X / C 1.000 0.260 0.732 0,683

I

n - RIRFOIL LONER5URFRCE X / C Cp P / PT M X / C Cp P / PT M -3 7 5 0.042 0 66 7 0. 7 83 -2 50 5.000 0 655 0.802 I SIDENRLL, Z / C = 1.3 7 5 0.025 -C.110 0.622 0.852 -2 O0 0.018 0 660 0. 7 93 _ 0.050 -0.349 0.552 0.961 -I 50 0.032 0 664 0.%8 7 0.100 - 0.591 0.481 1.078 -1 O0 - 0 . 012 0 651 0.807 1 0.200 -0. 7 89 0.422 1.182 -0 50 -0.070 0 634 0 833 i 0.300 -0.8 7 9 0.396 t.230 0 O0 -0.043 0 642 0 821 1 0.400 -0.922 0.383 1.256 0 50 -0.039 0 643 0 820 • 0.500 -0.434 0.52 7 1.001 1 O0 -0.012 0.651 0 807 Lt 0.600 -0.166 0.606 0.877 1 50 -0.001 0.655 0 802 0.700 -0.099 0.626 0.846 2 O0 0.005 0.656 0 799 0.800 -0.023 0.648 0.812 2 50 0.000 0.655 0 801 0.850 0.022 0.662 0. 7 91 3 75 0.022 0.662 0 792 r 0.900 0.089 0.681 0.762 J 0.925 0.121 0.691 0. 7 47 :1_ 0.950 0.159 0.702 0. 7 30 SIDENRLL, Z / C = -1.3 7 5 i 0.975 0.205 0. 7 15 0.709 X / C Cp P / PT M • I SIDEWALL, Z-O -3 7 5 0.036 0,666 0 7 85 -1 O0 -0.01 7 0 . 650 0 809 I X / C Op P / P? M -0 50 -0.019 0.649 0 810 0 O0 -0.082 0.631 0 839 "] -3 . 7 5 0 . 050 0.6 7 0 0 . 77 9 0 50 -0.004 0.654 0 803 -3.00 0.004 0.656 0. 7 99 1 O0 -0.019 0.649 0 810 I -1.25 0 . 063 0 . 6 7 4 0. 77 3 1 50 -0.002 0 . 654 0 803 1.25 0.028 0.663 0. ? 89 2 O0 0.000 0.655 0 802 t 3.75 0.013 0.659 0. 7 95 2 50 0.001 0.655 0 801 , 3. 7 5 0.016 0.660 0 7 94 (c) M _" O .801 , a = -O .I O ° , Rec ,_ = 4. 0X lO 6 .

Figur e 1 5.-C on tl nued.

I o - RIRFOILUPPER SURFRCE

NRCR 00i2 RIRFOIL x / o Op P / P7 M

i 0.000 1,165 0.998 0.055 0.025 -0.041 0.642 0.822 -1.s 0 . 050 -0,292 0 . 56 7 0 . 937 0.0 7 5 -0.444 0.523 1.009 0.100 -0.480 0.512 1.02 7 0,150 -0,551 0.452 1 112 -1oO.

o B o 6 0 . 200 -0 . 749 0.433 I 163 0.250 -0 . 788 0.421 1 184 o_° 0.300 -0,819 0.412 1 201 -o.5-___ o 8 0.350 -0 . 814 0.396 1 231 , ,_ 88P 0.400 -0.886 0.392 1 238 o 0.450 -0.901 0.388 1.247 C _ 0 : Op o.o _ o 0.500 -0.4]9 0.530 0,99 7 _o_ 0.550 -0.260 0.57 7 0.922 0.600 -0,194 0 . 597 0.892 o.5 0.650 -0.15 7 0.607 0.8 7 5 0.700 -0,119 0.6]9 0.858 0.750 -0.080 0.630 0.839 0.800 -0.035 0.644 0.819 1.o .. 0.850 0.023 0.661 0.793 0 . 900 0.0 7 1 0.675 0. 77 1 : 0.925 0.104 0.685 0. 7 56 _,! 1.s . . , . - , 0.950 0.142 0,696 0.739 ;'i o .o o.2 0.4 0.6 o.B .o 0.9 1 5 0.185 0. 7 09 0. 7 19 i X / O 1.000 0 . 247 0 .7 27 0 . 691 I 5IDENRLL , Z / C= 1.375 }, I X / C Op P / PT N ;_ _- RIRFOIL LONER SURFRCE , : X / C Cp P / PT M -3.75 0.037 0.665 0.786 -2.50 -0.005 0.652 0.806 i 0 025 -0.125 0 61 7 0.860 -2.00 0.010 0.657 0.799 0 050 -0 339 0 554 0.959 -!.50 0.023 0.661 0.793 -- 0 100 -0 5 7 4 0 484 1.0 7 3 -1 . 00 -O.OtB 0.648 0,812 0 200 -0 7 84 0 422 1.182 -0.50 -0.075 0.632 0.83 7 0 300 -0 883 0 393 1.236 0.00 -0.030 0.645 0.81 7 • 0 400 -0 926 0 380 1,261 0.50 -0.043 0.64! 0.823 : 0 500 -0 380 0 542 0,978 1.00 -0.016 0.649 0.810 0 600 -0 186 0 599 0,888 1,50 -0.00 7 0.652 0,806 0 700 -0 109 0 622 0.853 2.00 0.000 0.654 0.804 0 800 -0 034 0.644 0.819 2.50 -0.005 0,652 0,808 0 850 0 014 0.658 0.797 3. 7 5 0.018 0.659 0. 7 95 0 900 0,078 0,677 0.768 0 925 0,110 0,686 0, 7 54 0.950 0.1t 7 0.69 7 0. 7 3 7 SIDENRLL , Z / 0=-1.375 0.975 0.191 0.710 0. 7 16 X / C Cp P / PT N SIOENRLL,Z = 0 -3. 7 5 0.033 0.664 0. 7 88 ' -I.00 -0.019 0.648 0.812 X / O Cp P / PT N -0.50 -0.021 0.648 0.813 -3. 7 5 0.047 0 668 0 782 0.00 -0.0 7 8 0.63 1 0,839 " " 0.50 -0.008 0.652 0.80 7 -3.00 0.007 0.656 0.800 1.00 -0.025 0.646 0.815 -1.25 0 . 055 0.6 7 0 0.778 1.50 -0.008 0.651 0.807 1.25 0.025 0.661 0.792 2.00 -0.00 7 0.652 0.806 3. 7 5 0.009 0.656 0.799 2.50 -0.003 0.653 0.805 3. 7 5 0.011 0.65 7 0. 7 98 (d) M , = 0 . 803, a = - 0 . 10 °, R e c ,. = 6 . 5X I0 6 .

,!

Figur e 1 5 . - Continu e d. ;

N

p !

.1 r 'i ' _ q

o! ' i

'!" o - RIRFOIL UPPCR 5URFRCC r " NRCR 0012 RIRFOIL x / c Cp P / PT M ; ,'! 0.000 1.166 0.998 0.048 ' 0.025 -0.034 0.6_4 0.81@ I 0.050 -0.276 -_.s I 0.075 - 0.434 0.5730.526 0.9281.003 i 0.100 -0.475 0.514 1.023 '

I

0.I50 -0.654 0.461 1.112 -l.o 0,200 -0,750 0.433 1.162 o 8 o o 0.250 -0.784 0.423 1.180 o o 0.300 -0._16 0.414 1.19 7 v -o.s - _ ..... 0.350 -0.870 0.398 1.227 "'8 r e 0.400 -0.880 0.395 1.233 o 0.450 -0.846 0.405 1.214 -:_ 0 O_ o Cp 0.o _ 0 0.500 -0.338 C . 555 0.957 °ao o 0.550 -0.239 0.364 0.912 -, 0.600 -0 . 191 0.593 0 . 889 o._ ...... 0.650 -0.156 0 . 508 0 . 874 0.700 -0.119 0.619 0.856 0.750 -0.076 0.832 0.837 0,800 -0.029 0.646 0.816 i.o .... 0 . 850 0.031 0 . 664 0.788 ,_{ 0.900 0.078 0.67£ 0 . 767 0.925 0.113 0.688 0.751 , : z.s .... . 0 . 950 0.149 0 . 696 0 . 735 _i o.o a.2 0.4 o.B o.B 1.o 0 . 975 0 . 193 0.71t ,J.715 _' X / C 1.000 0.258 0 . 73_ 0 . 685 : !

' SIOEWRLL, Z / C = i,375 ; ,'- o - RIRFOIL LOWER SURFflOE X / O Op P / PT M i X / C Cp P / PT M -3 75 0.040 0.666 0.783 -250 -0.004 0.653 0.80 5 0.025 -0.]23 0.6t8 0.858 -2 O0 O.OtO 0.557 0.79q _ 0.050 -0.338 0.555 0.957 -I 50 0.025 0.661 0,792 0.100 -0,579 0.484 1.074 -1 O0 -0.016 0.649 0.810 | 0.200 -0. 7 86 0.423 1.181 -050 -0.065 0.635 0.833 | 0.300 -0.884 0.394 t.235 0 O0 -0.014 0.650 0.809 , 0.400 -0.923 0.382 ].258 050 -0.034 0.644 0.8]8 : • 0.500 -0.358 0.549 0.967 I 00 -0.006 0.652 0 . 80_ " O.GO0 -0.186 0.600 0.887 I 50 0,003 0.E,35 0.80_ .

0.700 -0.111 0.622 0.853 2 O0 0.003 0.655 0.602 I , ' 0.800 -0.033 0.645 0.8t7 2 50 -0.001 0,654 0,804 i 0,850 0.018 0,660 0. 7 94 3 75 0.024 0.661 0.792 ' 0.900 0,081 0,679 0.765 : 0.925 0.116 0.689 0.750 0.950 0.151 0.699 0.734 SIDEWALL , Z / C " -I,315 0.975 0.198 0.713 0.7 L 3 X / C Bp P / PT M 51DCWALL , Z =0 -3.75 0.038 0.665 0.786 -I.00 -0.017 0.649 0.81!

X / O Cp P / P? M -0.50 -0.015 0.650 0.813 -3.75 0.050 0.669 0 . 781 0.00 - 0.072 0.633 0.83 3 -3.00 0.007 0.657 0.799 0.50 -0.00] 0.63i 0.803 -t 25 0.060 0.672 0 776 1.00 -0.020 0.6a8 O._l!a _ • " 1.50 -0.004 0 . 653 0..0_ 1.25 0.G32 0.663 0. 2 89 2.00 -0.004 0.653 0.8n5 • 3 . 75 0.016 0.659 0. 7 96 2.50 0.000 0.654 0.803 ' 3.75 0.018 0.660 0.795 t : ( e ) M . = O _ 02,a = -O . lO °, Rec , . = 8 .3X lO t. , " • Fi @ u _ IS. - Con t_ u e d , !

• 35 ' % N, 0 - RIRFOIL UPPERSURFRCE

_ - NRCR 0012 RIRFOIL x / c Cp P / PT m '

0.000 1.165 0.998 0.060 0.025 -0.026 0.64 7 0.814 -1.5, 7 I 0.050 -0.2 7 7 0.5 7 2 0 . 929 , • 0.075 -P.435 0.526 1.004 0.100 -0.479 0.513 1,025 _ 0.150 -0.655 0.461 1 . 113 -1.0 ' 0.250 -0 . 783 0.423 1 . 180 _ o 8 o o 0.200 -0.752 0.432 1.163 " o o 0.300 -0.814 0.414 1.197 -o.s ---9£ o 0.350 -0 . 8 7 3 0. 3 97 1 . 229 , 0 . 400 -0.886 0.393 1.23 7

BP

o 0.450 -0.900 0 . 389 1 . 244 , _' Cp o . 0 _ _ 0.500 -0.401 0 , 536 0. 9 8 7 • , °Oo o 0.559 -0.251 0,580 0.91 7 0.600 -u .i 91 0.598 0.889 o . s .... 0. 6 50 -0.156 0.608 0.8 7 3 ; 0. 7 00 -0.118 0 . 620 0.856 : 0. 7 50 -0 . 0 7 6 0 . 632 0.83 7 0.800 -0.030 0.645 0 . 81 6 l . o 0.850 0.028 0 . 663 0 . 7 9 0 L ' _ 0 . 900 0.0 7 5 0.6 77 0. 7 68 !

; _ 0.925 O. 109 0.68 7 0. 7 53 : : 1 . 5 . . ...... . 0.950 0. 14 7 0.698 0 .7 36 :_ o.o 0 . 2 0.4 o.s o e l.o 0. 9 7 5 O. 190 0. 7 10 0. 7 16 t X / O 1.000 0.25 7 0. 7 30 0.685 SIOEWRLL, Z / C= 1.3 7 5 o - RIRFOIL LOW E R fiURFRC£ X / C Cp P / PT H , X / C C p P / PT M -3.75 0 03 7 0 665 0. 7 86 ; " -2.50 -0 00 7 0 652 0 . 806 0.025 -0 112 0.621 0.864 -2 . 00 0 006 0 656 0 . 800 0.050 -0 336 0 . 555 0.95 7 -].50 0 022 0 661 0 .7 93 ' 0.100 -0 578 0.484 1.0 7 4 -1 . 00 -0 022 0 649 0 . 813 !

0,200 -0 783 0.423 1.181 "0.50 -0 0 7 3 0 633 0 . 83 6 0 . 300 -0 885 0.393 1.235 0.00 -0 021 0 648 0.812 i 0.400 -0 925 0.381 1 . 260 0.50 -0 041 0 642 0.821 0.500 -0 413 0.533 0.993 1.00 -0 011 0 651 0.808 0 . 600 -0 18_ 0.600 0.887 1.50 -0 003 0 653 0.804 _ "° 0 .7 00 -0 111 0 . 622 0.853 2 . 00 -0 003 0 653 0 . 804 # 0.800 -0.035 0.64{ 0.819 2.50 -0 006 0 652 0.806 l 0.850 0 . 014 0.658 0. 7 9 6 3. 7 5 0 020 0 660 0. 7 9 4 0.900 0.0 7 9 0. 6 77 0. 7 6 7 0.925 0.110 0.68 7 0.753 0.950 0.148 0.696 0.736 SID£WRLL,Z / C"-_.375 , 0.975 0.19 6 0. 7 1 2 0.714 _ / C Cp P / P? M ' ' 5 10£WRLL, Z" 0 -3. 7 5 0.033 0. 66 4 0. 7 88 -1.00 - 0.020 0. 6 48 0.812 , X / C Cp P / PT M -0.50 -0 . 019 0.64 9 0 . 811 -3 .7 5 0.048 0. 6 68 0. 7 81 0.00 -0 . 080 0. 6 31 0.839 -3.00 0.004 0.656 0.B01 0.50 -0.006 0.652 0.805 1 . 00 -0.02 7 0. 6 4 6 0.815 -1.25 0.057 0 . 6 71 0.77 7 1.50 -0.010 0 . 651 0 . 80 7 1 .2 5 0 . 0 2 7 0 .662 0 . 7 90 2 . 00 -0 . 00 9 0 .65 2 0 . 80 7 3 . 75 0 . 011 0 .6 5 6 0 . 7 9 8 2. 50 - 0 . 00 4 0 .6 5 3 0 . 805 3 . 7 5 0 . 014 0 .6 58 0 . 7 9 7 I ( 0 m . = o _ o 3, a• . . o .l o °, a, ¢,. • l o.o xm' .

F@ u m 1 5 .- C o _l i n u ec l .

" t . 36 _ 2 ......

_ ..'- 81_, ' _III t _.r _ : -. , _-_

!

i !

f o - RIRFOIL UPPER SURFACE

t NRCR 0012 RIRFOIL x / c Cp P / PT M

f o.ooo 1.i71 1.ooo .oo4

0.025 -0.020 u.649 0.811

ii -,.s 0.050 -0.278 0.573 0.928

0.075 -0.436 0.52 7 1.003 0.100 -0.481 0.514 1.024 -1 . o ' .. 0 . 150 -0.656 0.462 1.11t o 8 o o 0.200 -0. 7 54 0.433 1.162 0 . 250 -0 . 7 84 0.424 1.178 -0.s g o 0 . 300 -0 . 816 0 . 415 1 . 195 --- _ .... = 0.350 -0 . 8 7 7 0 . 397 1.229 88p o 0.400 -0.889 0.393 1.236 o Op o.o R o _ o 0.450 -0.897 0.391 !.240 0.500 -0.391 0.540 0.981 mooo 0.550 -0.242 0.584 0.912 0.600 -0.186 0.600 0.886 0.650 -0.155 0.609 0.8 7 2 0.5-- 0.700 -0.117 0.621 0 . 854 0. 7 50 -0.075 0.633 0.835 0 . 800 -0 . 028 0 . 647 0.814 l.o 0.850 0.031 0.664 0.78 7 0.900 0.078 0.678 0.766 0.925 0.112 0.688 0.751 1.5 . ...... . ..... 0.950 0.150 0.699 0.733 o . o 02 0.4 0.6 o.s .o 0 . 975 0 . 194 0 . 712 0 . 713 X / C 1.000 0.265 0.733 0.681 SIDEWRLL , 2 / C = 1.375 [] - AIRFOIL LOWER SURFACE X / C Cp P / PT M X / C Cp P / PT M -3. T 5 O _ .... ,_ u .SOG u .,' 84 -2.50 -0 007 n _c_ _ . _ 0.804 0.025 -0.103 0.625 0.849 -2.00 0 006 0.657 0.799 0 , 050 -0 . 334 0 . 55 7 0 . 954 -I.50 0 022 0.662 0 .7 91 0 . 100 -0.578 0.485 1.072 -l . O0 -0 021 0.649 0.811 0.200 -0.786 0.424 [ 179 -0.50 -0 073 0.634 0.834 0.300 -0.891 0.393 i 237 0.00 -0 014 0.651 0.808 O.40n -0.933 0.380 t 261 0.50 -0 038 0.644 0.819 0.500 -0.494 0.510 1 031 1.00 -0 009 0.652 0.805 0.600 -0.184 0.601 0 885 1.50 -0 001 0.655 0.802 0.700 -0.105 0.624 0 849 2.00 -0 002 0.654 0.802 . 0.800 -0.034 0.645 0 81 7 2.50 -0 006 0.653 0.804 0.850 0.01 7 0.660 0 7 94 3 . 75 0 022 0.661 0 . 792 0. 9 00 0.080 0 . 6 7 9 0 7 65 0,925 0.115 C .q89 0 750 0.950 0 . 150 b.699 0 733 SIDEWRLL., Z / C =-t.3 7 5 0.975 0,200 0.714 0 711 X l C Cp P I PT M SIDEWALL,Z-O -3.75 O 035 0 . 665 0. 7 86 - -1.00 -0 021 0.649 0.811 X / O Op P / PT M -0.50 -0 020 0.649 0.810 0.00 -0 083 0 . 631 0 . 839 -3.75 0.05,0 0.6 7 0 0,779 0.50 -0 005 0.654 0 . 804 -3 . 00 0.004 0.656 0.800 1.00 -0 02 7 0.647 0,814 -1.25 0.062 0.6 7 3 0.774 1.50 -0 008 0.653 0.805 1 . 25 0 . 031 0.664 0. 7 88 2.00 -0 011 0 . 652 0.806 3. 7 5 0.013 0.659 0.795 2 . 50 -0 004 0.654 0.803 3.75 0 01 7 0.660 0. 7 94 ( | ) M _ " 0 _ 01, ¢ .-O , 08 " , Rec, . . 12 . 1 X lO 6 .

Ft _ 1 5.- Con d ud e d .

3 . _" o - AI R FOIL UPP ER SURFAC E

NRCR 0012 AIRFOIL × / c o R P / PT M

0.000 1.155 0.995 0.083 0.025 -0.162 0.608 0.875 -1 . s 0 . 050 -0 . 40 7 0 . 535 0.9 8 9 0.0 7 5 -0.565 0.489 1.065 0.I00 -0 . 642 0 . 466 I . I04 0,150 -0.762 0,431 1,166 -].O" o o _ o o o 0,200 -0,841 0.408 1.209 o o m 0.250 -0.888 0.394 I . 35 o o 0.300 -0.93 7 0.3 7 9 i 263 - o . s --_Ro 0.350 -0.971 0.369 1 . 283 -p o 0 . 400 -0.950 0.3 7 6 1.271 : 0.450 -0.895 0.392 1.239 oO _ o 0.500 -0.8 8 6 0.394 1.234 Cp o.o _ ..... = @@@@ 0 . 550 -0 . 893 0.392 1.238 0.600 -0.585 0.489 1.065 o . s ..... 0 . 650 -0.316 0.562 0.946 0.700 -0.178 0.603 0.882 0. 7 50 -0 0 7 6 0.633 0.836 0 . 800 -0.020 0 . 649 0.810 l . o 0.850 0.003 0.656 0.800 0.900 0.0 7 6 0,6 7 8 0.76 7 0.930 0.100 0.685 0. 7 56 _ . s . .- , -_ . 0.950 0.132 0.694 0. 7 41 o . o o . 2 o.4 o . s o8 o 0.980 0.159 0. 7 02 0. / 29 X / C 1.000 0.1 7 9 0.708 0,720 5I DE NRLL , Z / C- 1.3 7 5 o- AI R FOIL L ONER SURFAC E X / C Op P / PT I'I X / C Cp P / P T II -3.75 0.06] 0.6 7 4 0. 77 2 -2.50 0.012 0.660 0. 7 94 0.025 0.054 0.6 7 2 0,7 7 6 -2.00 0.620 0.662 0. 7 90 0.050 -0. 195 0.596 0 . 890 -1.50 0 . 02 , _ 0.663 0. 7 89 0.I00 -0.443 0.525 1 . 006 -l . O0 -0 . 014 0 . 652 0 . 806 0.200 -0 . 675 0.458 1 . 118 -0.50 -0.092 0.629 0.841 0.300 -0. 7 70 0 . 428 1. I 7 0 0.00 -0.093 0 . 62Q 0.842 0.400 -0, 7 93 0,423 t.180 0.50 - 0,08 8 0.630 0,839 0.500 -0. 7 14 0.445 1.141 1.00 -O.OSO 0.642 0.822 0.600 - 0 . 325 0.561 0 . 948 1.50 -0.031 0.64 7 0.813 0 . 7 00 -0. 103 0.625 0.848 2 . 00 -0.019 0 . 651 0. 8 08 0.800 -0.053 0 . 641 0 . 924 2.50 -0.020 0.651 0.808 0.850 -0.010 0.652 0.806 3 . 75 -0.004 0.655 0.801 0.900 0.03 7 0.66 7 0. 7 83 0 .9 30 0.065 0.6 7 4 0 .77 2 0. 9 50 0.099 0.685 0. 7 55 S| O E I_ P , LL , Z / C ' -1.3 7 5 0.980 O. 128 0.693 0. 7 43 X / C Cp P / P T M S IO E _R LL , Z"O -3. 7 5 O.O ' tl 0.6 6 8 0 . 7 81 -1.00 T . 028 0.648 0.812 X / C Op P / PT M -0.50 -0.032 0.647 0.814 -3.75 0.054 0.672 0.776 0 . 00 -0.111 0.62 ' t 0.85,5 -3.00 -0.020 0.649 0.810 0.50 -0.026 0.6 4 9 0.811 1 . 00 -0 . 045 0.643 0.820 -t .25 0 . 053 0 . 6 7 2 0. 7 76 1 . 50 -0.021 0 . 650 0.@ 0 9 1.25 0.010 0. 6 59 0.796 2.00 -0.020 0. 6 50 0. 8 0 9 3 . 75 -0.001 0.655 0.801 2.50 - 0.011 0.653 0.804

3.75 -0 . 006 0 . 65s 0.802

(m ) M ..• o . s m , _ - 0 .96 ", R_ e , .- l .o xl o' .

F l llure16. - Airfoilandt e st channel sid e wallpressure measuremen t s, Dat a S e t 4 ( M N • 0.8 0 , a N • 10).

t

3 8

,mw i _l o - AIRFOIL UPPgR SURFRCg ' 'i X / O Cp P / PT M

f NRCR 0012 RIRF O IL

0.000 1.154 0.995 0.088 = ; 0 . 025 -0 . 1 77 0 . 600 0 . 886 _ -1 . 5 0.050 -0.423 0 . 52 7 1.002 , 0.075 -0.58 7 0.4 7 9 1.083 : t 0.100 -0.655 0 . 459 1.117 -_ -1 . o 1 - n _ 0.150 - 0 . 7 7 4 0.423 1.180 • o o _ v o " 0.200 -0 . 856 0.399 1.225 o o o 0 . 250 -0 . 904 0 . 385 1.253 _ o° 0.300 -0.951 0.371 1.280 0.350 -0.989 0.360 1.303 . 4 - - _Cp u o 0 . 400 -1.012 0.353 1.31 7 oU u o 0.500 -0.980 0.362 1.29 7 0.550 -0.961 0.368 1.286 iI ] 0.450-I.026 0.3,9 1.325 Op o o o o B=_o 0 . 600 - 0.788 0 . 419 1,18 7 _| o . s _ 0 . 650 -0 . 321 0 . 55 7 0 . 953 0. 7 00 -0.134 0.613 0.866 : 0.750 -0.053 0 . d3 7 0.830 t 0 . 800 -o.n06 0.651 0.808 1 . o.- l 0.850 0.002 0 . 653 0.804 ' O . 9OO 0.0 7 8 0 . 6 7 6 0.7 7 0 _ i 0.930 0.10, 0.683 0. 1 58 1 . s . . . , , 0.950 0 . 134 0 . 692 0 . 7 44 t o . o o.2 o.4 0 . 6 0.8 1.o 0 . 980 O. 168 0. 7 02 0. 7 29 X ,' C 1.000 0.21, 0.716 0.708 i S[OENRLL. , Z / C= 1 . 375 I u- RIRFOIL LOWCR SURFRCC X / O Cp P / PT N _ i X / C Cp P / PT M -3 . 75 0.048 0.66 7 0. 7 83 ! i -2.50 0.002 0.654 0.803 _ I 0.025 0.044 0 666 0. 7 84 -2.00 0.010 0.656 0.800 , 0.050 -0.205 0 592 0.899 -1.50 0.010 0.656 0 .7 99 0 . 100 -0 . 45 7 0 51 7 1 , 018 -1.00 -0.030 0.644 0 . 818 0.200 -0.683 0 451 1.130 -0 50 -0.I06 0.622 0.852 * 0.300 -0. 7 80 0 422 1.183 0.00 -0.105 0.622 0.852 _ 0.400 -0.830 0 408 t.209 0.50 -0.10 7 0.622 0.853 i 0.500 -0.778 0.422 1.182 1.00 -0.061 0.635 0.832 0.600 -0.192 0 596 0.892 1.50 -0.038 0.642 0.821 0. 7 00 -0.135 0 612 0.867 2.00 -0.025 0.646 0.816 i 0.800 -0.060 0 636 0.832 2.50 -0.028 0.645 0.81 7 0.850 -0,00 7 0 651 0.808 3.75 -0.005 0.652 0.806 0 . 900 0 . 050 0 668 0.782 0.930 0.086 0 678 0 . 766 0.950 0.120 0 689 0, 7 50 SIOEWRLL, Z / C =-1.3 7 5 0,980 O. 162 0 7 00 0. 7 32 X / O Op P / P3 M 5IO E WRLL, Z=O -3.75 0.034 0.663 0 . 7 89 -I . 00 -0 . 034 0 . 643 0 . 820 X / O Op P / PT M -0.50 -0 . 042 0 . 641 0 . 823 -3. 7 5 0,049 0.66 7 0, 7 82 0 . 00 -0 . i08 0 . 621 0 , 853 -3.00 -0.002 0 652 0.806 0.50 -0.031 0.644 0.818 " 1 . 00 -0 . 044 0 . 640 0.824 -1.25 0 . 045 0 . 666 0. 7 84 1.50 -0.02 7 0 . $45 0 . 8t6 1, 2 5 0.009 0.656 0.800 2.00 -0.023 0,64 7 0.815 3.75 -0.C09 0.850 0.809 2.50 -0,014 0.649 0.810 3. 7 5 -0,004 0.652 0.806 Co) M oo= 0 ,80 5 , e = 0. 97° , Rec ,_ = 2 .0X 1 0 6.

; , 3 9 Fig u re 1 6. - C ontinue d. . _ _ D_ o - RIRFOIL UPPER SURFACE

NRCR 0012 RIRFOIL x / c Cp P / PT n

OLD00 11156 Ol_g5 OlO_ , , 0.025 - 0 .!86 0.595 0.894 -_.s- - 0.050 -0.42 7 0.524 1.008 0.0 7 5 -0 . 592 0 . 474 ].089 0 . 100 -0 650 0 . 45 7 ! .1 19 li f o _ II 0"200 -- 0849 0 " 398 1 . 227 o d '-e----_ 0 0.150 -0 7 49 0 . 428 1.] 7 2 _ o ° 0.300 - 0 942 0 370 1.281 o i [] 0.250 -0 891 0.385 1.25!

-o . s_L_CO .. o 0 . 350 -0 983 0 . 358 1 . 306 _ P o 0.400 -0.999 0.353 1.316 "_ ou 1 u o 0.450 -!.024 0.346 1.331 O.O 0.500 -1.045 0.339 1.345 :. C u _._ 0 . 550 -0 . 549 0 . 48 7 1 . 068 0.600 -0 . 422 0 . 525 1.005 0 .s ..... 1 l 0 . 650 -0 . 3 7 2 0 . 540 0.981 0. 7 00 -0.29 7 0.562 0.946 0. 7 50 -0.20 7 0.589 0.903 : 0.800 -0.110 0 . 6!8 0 . 859 1.o 0.850 0.010 0.654 0.804 . 0.900 0.052 0.666 0. 7 85 , , - 0 . 930 0 . 084 0.6 7 5 0. 77 0 t " 1 . s -------r--------- - -,------------,--- , 0.950 0.114 0.684 0 . 756 o.o 0.2 o.: 0.6 O B .0 0.980 0.144 0.693 0 . 743 " X / 6 1 . 000 0.164 0.699 0. 7 34 SIDEWALL . Z / C= 1.3 7 5 o- AIRFOIL LONER SURFACE X / C Cp P / PT M X / C Cp P / PT M - 3 75 0 . 036 0 . 662 0 . 791 -2 50 -0 , 001 0 , 651 0.808 0,025 0,050 0,666 0 785 -2 O0 0.00 7 0.653 0.805 0.050 -0 . 195 0.592 0 698 -1 50 0 . 014 0 . 655 0 . 801 -- 0.100 -0.43 3 0.522 I 011 -1 O0 -0 . 029 0.643 0 . 821 0.200 -0.662 0.454 1 125 -0 50 -0.105 0.620 0.856 0.300 -0. 7 C 7 0.4 2 2 I 182 0 O0 -0.092 0.624 0.850 0.400 -0.8t2 0.409 I 206 0 50 -0.102 0.621 0.854 ' 0.500 -0.564 0.483 1 0 7 6 1 O0 -0 . 047 0.637 0.829 0.600 -0.226 0.584 0 912 1.50 -0.031 0.642 0.822 0. 7 00 -0.152 0.605 0.8 7 8 2.00 -O.Olfi 0.646 0.815 0.800 -0.0 7 1 0.630 0.840 2.50 -0.019 0.645 0.816 0.850 -0.023 0.644 0.8t9 3.75 O.OOS 0.653 0.805 0.900 0.029 0 660 0. 7 94 0.930 0.059 0.668 0 . 781 0.950 0.084 0 . 676 0 . 769 SIDENRLL , Z / 0 =-1.3 7 5 0.980 0.124 0.688 0. 7 51 X / O Op P / PT M SIOEWALL, Z =0 -3 . 7 5 0.033 0.661 0 . 7 93 -I.00 -0 . 028 0 . 643 0.820 X / C Op P / PT M -0 . 50 -0.030 0 . 642 0.821 -3.75 0.052 0 . 666 0.784 0 O0 -0.094 0.623 0.851 -3.00 0.010 0.654 0.804 0 50 -0.019 0.645 0.816 I O0 -0 . 035 0 . 641 0 . 823 -1 . 25 0.049 0 . 666 0. 7 85 1 50 -0 . 018 0.646 0 . 816 1.25 0.018 0.656 0.800 2 O0 -0.019 0.645 0.816 3. 7 5 O.OOl 0.651 0.80 7 2 50 -0.008 0.649 0.811 3 7 5 0 . 009 0.654 0.804 (c) M _ = 0.808, _ = 0. 9 7 °, Rec , _ = 4.1X 10 _ .

" Figure 16.- Cont _ ued.

o - RIRFOILUPPER SURFRCE

NRCR 0012 RIRFOIL x ,, c Cp P I PT M

0.000 t160 0.996 0.073

0_025 -0 189 0.598 0.890 0.050 -0 421 0.529 0.999 -t.s. I 0.075 -0 593 0.478 J.083 0.100 0 647 0.462 !.I]0 o o 0.150 -0 7 62 0.428 1.1/.

-1 . 0 o o o 0.200 -0 666 0.398 1.228 o u 0.258 -0 907 0 . 385 1 . 251 o° o o 0 . 300 -0.950 C.370 1 . 282 0.350 -0.996 0.359 1 . 304 -°.5 -.-eCp o o 0.400 -1 013 0 . 354 1 . 314 0 oo o o 0.450 -1.039 0.347 !.330 0.500 -1.063 0 . 339 ! . 345 " Cp o . o u _ _80 0.550 -0 . 590 0 . 479 1 . 081 0.600 -0.434 0.525 1.005 o.5- 0 . 650 -0 . 369 0 . 545 0.974 0.700 -0 . 2 77 0 . 572 0.931 • 0.750 -0.173 0.602 5.883 0.800 -0 , 074 0.632 0.837 1.o 0.850 0.008 0 . 656 0 . 800 i 0 . 900 0.069 0 . 674 0.772 " 0.930 0.099 0.683 0.759 -:; 1.s. ..... 0.950 0.129 0.692 0 . 745 &i o . o 0 . 2 °.4 0.6 o.8 l.o 0.980 0.160 0. 7 01 0 . 731 I _i X / C 1,000 0.191 0.710 0 . 717 T SIDEWALL,Z / C= ! . 375 o - flIRFOIL LONER SURFRCE X / O Op P / PT M X / C Cp P / PT M -3. 7 5 0 030 0.662 0.79[.

-2 50 -0 010 0.650 0.80£ 0.025 0 043 0.666 0.784 -2 O0 -0 003 0.653 0.805 0,050 -0 ]86 0.599 0.888 -1 50 0 010 0.65 7 0.799 0.100 -0 446 0.522 1 .0 1 1 -1 O0 -0 033 0 . 644 0.8 '_ 0,200 -0 676 0.454 t.125 -0 50 -0 110 0.621 0.854 0.300 -0 7 84 0.422 1.183 0 O0 -0 089 0.627 0.844 0,400 -0 82 7 0.409 t.206 0 50 -0 ]04 0.623 C.851 0 500 -0.591 0.4 7 9 1.082 1 O0 -0.052 0.638 0.82_ 0 600 -0 . 234 0.584 0 . 911 1 50 -0.031 0 . 644 0.818 , 0 7 00 -0.162 0.606 0.878 2 O0 -0.020 0.64 7 0.813 i_ 0 800 -0.075 0.631 0.838 2 50 -0.022 0.647 0.814 0 850 -0.025 0.646 0.815 3 75 0.004 0.655 0.802 0 900 0.033 0.663 0.789 0 930 0.063 0.6 7 2 0. 7 75 0 950 0 . 095 0.682 0 . 7 61 SIOENALL, Z / 0 = -1.375 0 980 0.138 0.695 0.741 X / O Cp P / PT M SIDENALL,Z = O -3 75 0.026 0.661 0.792 -I O0 -0.035 0.643 0.820 X / O Cp P / PT M -0 50 -0 . 036 0 . 643 0,820 -3.75 0.044 0._67 0.784 0 O0 -0.103 0.623 0.85] -3.00 0.004 0.655 0.802 0 50 -0.025 0.646 0.815 -t.25 0.046 0.667 0.783 1 00 -0.044 0.64] 0.824 i 50 -0 . 024 0 . 646 ., . 8i_ t.25 0.015 0.658 0.797 2 O0 -0.024 0.646 0.SIS 3 7 5 0 . 004 0 . 655 0 . 80:: • ( d ) M mffi 0 . 804, a = 0 . 96 °, Rec , m ffi 6. 1X1 0s .

i i 3.75 -0.002 0.653 0.805 2 50 -0.011 0.650 0,809 Figur_ 16 . - Cont _ ued.

. 4 1 , " '" - , J = ; o - RIRFOIL UPFER SURFRC E

• 0.000 i.i98 1.000 0.000

i NRCR 0012 RIRF@IL x / c Cp P / PT M

{_ 0.025 -0.154 0 . 607 0 . 875 -1.s 0 . 050 -0 , 403 0.534 0 991 0 . 075 -0 . 575 0.483 1 075

i

_ 0.I00 -0.631 0 , 466 1 103 ! -i.0 _ _ o 0.150 -0.747 0.432 i 164 " o o o 0.200 -0 . 849 0 . 402 1 220 G 0 0 0.250 -0.890 0.390 1 243 oO o 0.300 -0 . 949 0 . 372 1 277 " _ 0 . 350 -0 . 986 0 . 361 1.299

• I _o . 5 o

_, oo o o 0 . 450 -1 . 030 0 . 348 1 . 326 1 Cp o.0 l 0 . 500 -1 . 056 0 . 340 1 . 343 _ o 0 . 550 -0 . 675 0 . 453 1 . 126 .I 0 . 600 -0.437 0 . 524 1.008 i o _ 0.400 -i.004 0.356 1.310 i 0.s 0.650 -0.372 0.543 0 . 976 q i 0.700 - 0 . 262 0 . 569 0.934 0.750 -0.178 0.600 0.886 :I 0 . 800 -0 . 074 0 . 631 0.838 i 1.0 0.850 0 . 025 0.66! 0.793 " 0.900 0 . 086 0 . 679 0.765 'I 0 . 930 0.118 0.688 0.751 4 1.5 , 1 , , -----,-----_ 0 . 950 0 . 148 0.697 0 . 7 37 : o.o 0.2 0.4 o.6 o.8 J.o 0 . 980 0 . 178 0 . 7 06 0 . 724 X / O 1 . 000 0 . 204 0 . 713 0 . 712 S[DEHRLL , Z / C = 1 . 3 7 5 :, o-RI R FOIL LONER SURFACE X / O Cp P / PT M X / C Cp P / PT M -3. 7 5 0.082 0.6 7 8 0. 7 66 -2.50 0 042 0,666 0. 7 84 , 0 , 025 0 . 101 0 , 68{ 0.758 -2.00 0 050 0.669 0.78 1 0,050 -0,169 0,603 0,882 -1.50 0 060 0.6 7 2 0. 77 6 - 0 , 100 -0,432 0.525 t,O05 -1.00 0 016 0.659 0 .7 96 0,200 -0,657 0 , 460 1,i15 -0,50 -0 064 0,635 0 , 832 0,300 -0, 7 83 0,421 1.183 0.00 -0 043 0.64] 0.823 0,400 -0,819 0,412 1,201 0,50 -0 059 0,63 7 0,830 0,500 -0,869 0,396 1,231 !.00 -0 004 0.653 0,805 ,.

0,600 -0,2t6 0,590 0,902 1.50 0 020 0,660 0,794 _" 0,700 -0,14G 0,6[2 0,868 2.00 0 028 0,662 0. 7 90 0,800 -0,034 0,644 0,8[9 2,50 0 025 0,661 0,792 0,850 -0,00 7 0,651 0,808 3, 7 5 U 053 0,6 7 0 0, 77 9 0 . 900 0 . 0 7 2 0,675 0 . 771 0,930 0,0 77 0,676 0,7 7 0 _: 0 , 950 0 , 132 0 , 693 0 , 744 SIOENRLL , Z / 0=- 1, 375 i 0,980 0,152 0,698 0, 7 36 X / C Op F / PT M -1.00 0 01 7 0,659 0. 7 95 i! 5IOENALL, Z=O -3 . 7 5 0 076 0,6 7 6 0 , 7 69 X / O Op P / PT M -0.50 0 010 0,65 7 0,798 0.00 - 0 067 0.634 0.833 "} -3.75 0.08 7 0.6 7 9 0. 7 64 0.50 0 028 0 . 662 0.790 -3.00 0.025 0.661 0.793 -1 25 0,087 0 , 679 0 , 764 1,00 0 006 0,656 0,800 " 1.50 0 02 7 0,662 0, 7 91 t.25 0.054 0.670 0. 72 9 2,00 0 022 0,66] 0,793 - 3 . 75 0 . 037 0 . 664 0 , 78 7 2,50 0 041 0 , 666 0 . 784 3. 7 5 0 058 0 , 6 7 1 0 . 77 7 ( e) M _ = 0 .80 5, _ = l .O0 ° , Re c ,_ = 8 . 3XI06 .

\] Fig u re 1 6 .- Co n ti nu ed.

J !

1 o - AIRFOIL UPPER SURFACE

NRCR 0012 RIRFOIL x / c Cp P / Pr M

0.000 1.154 0.996 0.074

0.025 -0.203 0.601 0.884

0.050 -0.454 0.528 i.000 -1.sj_ 0.0 7 5 -0.626 0.4 ? 8 1.083 0 . I00 -0 . 681 0 . d62 1.110 o o 0.150 -0.802 0.d2 7 1.1 7 3 -l.o o - [] ° I 0,200 -0,904 0 , 398 1,228 ' o _ ] 0,250 -0.9_ 7 0,385 1,252 o° 0.30ri -1.009 0,36 7 1.288 -* 0.350 -1.046 ?.356 1.310 -0.s --eu_ o o O.dO0 -1.064 0.351 1.320 o oo o , 0.459 -1.091 0.343 1.33 7 , o 0,500 -I . i1 7 0.335 1 . 353 Op o.o 0 6_ 0,550 -0,988 0.3 7 3 1.2 7 5 0,600 -0.519 0.510 1,031 o.s- I 0.650 -0.450 0.529 0.998 0, 7 00 -0,3 7 0 0 , 553 0,_61 0, 7 50 -0,2 7 9 0,5 7 9 0,919 0.800 -0,1 77 0.609 0,8 7 2 1.o 0,850 -0.041 0.649 0,811 0,930 0,042 0,6 7 3 0, 77 5 -" 0.900 0.005 0,662 0, 7 91 1.s . i , . _ ' . 0 , 950 0,0 7 2 0 . 681 0, 7 6; o.o o._ 0.4 0.6 o.e .o 0 , 960 0.104 0,691 0 .7 42 X / O 1,000 0,125 0.697 0.737 5IOENRLL, Z / C = 1.3 7 5 o - RIRFOIL LONERSURFRCE X / O Op P / PT N X / C Rp P / PT N -3 7 5 0.045 0.6 7 3 0. 77 4 -2 50 0.005 0.6S] 0.792 0 025 0 066 0 680 0, 7 63 -2 O0 0.013 0.664 0. 7 88 0 050 -0 229 0 594 0,896 -1 50 0.025 0.667 0. 7 83 0 I00 "0 d93 0 51 7 1,018 -1 O0 -0.022 0 . 653 0.804 I 0 200 -0 7 0 7 0 454 1,125 -0 50 -0,103 0,630 0.840 0 300 -0 858 0 411 t,203 0 O0 -0 . 090 0 . 634 0.835 0 400 -0 8 7 6 0 405 1,214 0 50 -0.101 0.630 0,839 0 500 -0 957 0 382 1,258 1 O0 -0.045 0.64 ? 0.814 i 0 600 -0 367 0 553 0,960 1 50 -C , 023 0,653 0.805 1 0 7 00 -0 222 0 596 0,893 2 O0 -0.013 0.656 0.800 0 800 -0 063 0 642 0,822 2 50 -0,016 0,655 0.801 1 0 850 -0 063 0 642 0,821 3 75 0 , 013 0,663 0 , 7 89 1 0 900 0 038 0 6 7 1 0 . 777 0 930 00lO 0 663 0. 7 89 0 950 0 096 0 688 0, 7 51 SIDENRLL, Z / C = -1 . 3 7 5 0 980 0 0 7 5 0 682 0,759 X / O tp P / PT M , SIDENRLL , Z = 0 -3. 7 5 0,036 0,6 7 0 0, 77 8 -1.00 -0.022 0.653 0.804 X / O Cp P / PT N -0.50 -0.031 0.651 0.808 [) O0 -0.119 0 . 625 0,848 -3. 7 5 0.038 0,6 7 1 0. 777 0 . 50 -0.013 0,656 0,80U -3.00 -0,122 0,625 0,848 1.00 -0.032 0.650 0.809 -1.25 0.041 0,6 7 2 0, 7 76 1.50 -0.013 0.656 0.800 1,25 0.002 0,661 0, 7 93 2,00 -0,018 0.654 0.802 3. 7 5 -0.016 0,655 0.801 2,50 0.001 0.660 0. 7 94 3 . 7 5 0.019 0 . 665 0, 7 a6 (f) M o o = 0 .7 93, a = 1. 00 °, Rec , oo = lO. 3 XlO s , Fig u re 16 .- Co ncl u ded .

L t ' o - RIRF O IL UPP E R SURFACE } '

NRCR 0012 RIRFOIL x / c Cp P / PT M

: 0.000 1.i28 0.991 0.115

",, o.o2 -0.405 0.556 0 . 956

-1.s 0.050 -0.613 0.49 7 1.052 ' _i 0.0 7 5 -0. 7 63 0._54 1.124 [ 0.I00 -0.838 0 . 433 1.16 2 -1 . 0 o _ n _ , .... I 0.150 -0.947 0.402 1.219 o 0.200 -1.014 0.383 i.256 o o 0.250 -1.050 0.373 1.276 ,_ o , 0.300 -1.031 0.3 7 8 1.266 -0.5 o"._','_p [] o 0.350 -0.9 7 1 0.395 1.232 ' ' o n 0.400 -0.9 7 2 0 . 395 1.233 o 0.450 -0.938 0.404 1.215 ' Op o.o --e---- o _ _ 0.500 -0.443 0 . 545 0.973 0.550 -0.226 0,607 0,876 u @eBB, 0.600 -0.132 0.633 0.835 0.s ...... 0.650 -0.105 0.641 0.823 0.700 -0.058 0.654 0.603 0. 7 50 -0.02 7 0.663 0. 7 89 0.800 0.0!2 0.674 0.7 7 2 1.o J 0.850 0.054 0.686 0.754 ; L 0.900 0.113 0,703 0. 7 28 0.930 0,141 0. 7 11 0. 7 16 _.s ,.... I , , , 0.950 0.180 0. 7 22 0.699 o.o 0 . 2 o._ o.6 0.8 1.o 0.980 0.208 0. 7 30 0.686 t X / C 1,000 0.248 0.741 0.668 SIDENRLL, Z / C = 1.3 7 5 i [] - RIRFOIL LONER SLIRFRCC X / O Cp P / PT M { X / C Cp P / PT M -3 7 5 0.084 0.696 0.738 i" -2 50 0.046 0 . 685 0.755 0.025 0.230 0.737 0.675 -2 O0 0.049 0 . 686 0. 7 54 [ 0.050 -0.012 0.66 7 0.783 -1 50 0.043 0.684 0. 7 56 i 0,100 -0.259 0,59 7 0,891 -1 O0 0.008 0.675 0.772 0.200 -0.406 0.55 7 0.953 -0 50 -0,058 0,656 0,800 : 0,300 -0,40 7 0,555 0 95 7 0.00 -0.047 0.659 0.796 • 0,400 -0.330 0.579 0 920 0.50 - - 0.037 0.662 0. 7 91 0.500 -0.283 0,590 0 901 1.00 -0.020 0.666 0.784 0.600 -0.1 7 2 0,623 0 850 1,50 0,008 0,674 0,772 0. 7 00 -0 . 08 7 0 . 646 0 816 2 . 00 0 . 019 0.678 0.767 0,800 -0.030 0.664 0 7 88 2.50 0,017 0.677 0,768 0,850 0,025 0,6 7 8 0 7 6 7 3.75 0.036 0,683 0.739 0,90 0 0,0 7 6 0,694 0 7 42 0,930 0.115 0.703 0 727 0.950 0.132 0. 7 09 0 718 SIDE_RLL , Z / C = -I.g_5 0,980 0.1 77 0. 7 21 0 7 00 X / O Cp P / PT M 8IDE_ALL, Z =0 -3.75 0.081 0.695 0.740 -1,00 0.029 0 680 0. 7 63 X / C Op P / P$ M -0 . 50 0.032 0 681 0. 7 61 -3 . 75 0.08 7 0.696 0. 7 38 0 . 00 0.010 0 5 7 5 0 . 7 7 1 -3 . 00 0.031 0.680 0. 7 64 0.50 0.030 0 681 0 . 7 62 -1,25 0,086 0,696 0. 7 39 1.00 0.021 0 678 0.766 1.25 0.069 0.691 0. 7 46 1.50 0.025 0 6 7 9 0.764 3.75 0 043 0.684 0.75 7 2.00 0,028 0 680 0.763 " 2.50 0.044 0 685 0.756 3. 7 5 0 . 03 7 0 683 0.759 i ( a ) M _ = 0 . 77 5, a = 2 . 0 3 °, Rec , _ = 1.0 X 1 0 _ .

Figur e 17. - Airfoil and t es t ch ann e l _ d e wa ] l pr eu ur e m eu ur e m e nts , Data S e t 5 ( MN = 0 . 77 5, a N = 2°).

44 _i " ¢

,!

i o . -RIRFOIL UP'PER SURFACE

I NRCFI0012 RIRFOIL x / c Cp P / PT n

, ,. ' 0.000 1.127 0 991 0,114 i: _ 0 . 025 - 0 . 428 0 551 0 . 964 0.050 -0.634 0 492 1.059 -, -! .5 I ' i 0.0 7 5 -0. 7 95 0 44 7 1.13 7 '_ 0 . I00 -0.869 0 426 1.1 7 5 o o o o 0.150 -0,9 77 0 395 1 . 232 - -i,0 "_----o- 0.200 -1.04 7 0 3 7 6 1.2 7 1 o 0 . 250 - 1.085 0 365 1.292

i oO

oo_L_ 0,300 -1.118 0,356 1.311 ! -o.5 [] 0.350 -1.140 0,349 1.324 ' 0 . 450 - 1 . 086 0 3 7 0 1.281 o 8 0 • _ Op o.o__ 7 _._. # 0.500 -0. 7 34 0.464 1.10 7 il I o o 0 . 400 - 1 . 084 0 , 365 1 . 291 _oo o , 0 . 550 - 0.282 0 . 592 0 . 899 0.600 -0.149 0.630 0.840

1o

c _ o.5 - , 0"650 -0"118 0"6_38 0"827 0. 7 00-00850.6480.813 0. 7 50 -0 05 7 0.656 0.800 --- 0 . 800 - 0 015 0.668 0 . 7 82 4 1.o 1 I 0 . 850 0 030 0 . 680 0 . 7 63 " 0 . 900 0 082 0 . 695 0. 7 40 . _ 0.930 0 llO 0. 7 03 0. 7 28

I

_ i. s , , _ , 0 . 950 0 145 0.713 0. 7 12 _ o.o 0.2 0.4 0.6 0.8 .o 0 , 980 0 184 0 . 7 24 0.695 X / O 1.000 0 235 0. 7 38 0.6 7 .", $[DENRLL , Z / O= 1.375 c - R]RFOIL LONER SURFACE X / O Cp P / PT M X / C Cp P / PT M [_,75 0.070 0.692 0.744 { . 50 0 . 026 0 . 680 0 .7 63 i 0,025 0,22! 0,735 0.6 7 8 -2.00 0.025 0.680 0.764 0.050 -0.040 0.66] 0,793 -1.50 0.022 0.6 7 9 0.765 I "# 0,100 -0.296 0.588 0.905 -;.00 --0,018 0.66 ? 0.783 • } 0.200 -0,453 0.545 0.974 -0.50 -0.087 0.648 0 812 , O,3qO -0,449 0,545 0,973 0.00 -0.0 7 6 0.651 0 808 { 0,400 -0.3?5 0.567 0.939 0.50 -0.066 0.654 0 803 4 0,500 -0,278 0,593 0.89 t 1.00 - 0.034 0.663 0 789 t 0.600 -0,205 0,615 0,864 i,50 -0.012 0,669 0 780 { 0, 7 00 -0 . 126 0 636 0.830 2.00 0.006 0 6 7 4 0 7 7 2 0,800 -0.046 0,659 0,795 2,50 0.005 0.674 0. 77 3 , 0,850 0.00 7 0.6 7 4 0.7 7 3 3.75 0.028 0.68; 0,762 0,900 0,063 0.690 0, 7 48 0.930 0.100 0. 7 00 0. 7 32 0,950 0.131 0 . 710 0. 7 18 SIDENRLL, Z / C=-1.3 7 5 i 0,980 0.1 7 6 0, 7 22 0 , 699 X, / C Cp P / PT M I SIDENRLL , Z = 0 -3 . 75 0 . 0 7 1 0,693 0. 7 44 - 1.00 0.006 0.6 7 4 0 77 2 X / 5 Cp P / PT M -0.50 0.0!5 0.6 77 0 7 68 !

-3. 7 5 0.082 0 . 695 0 . 739 0.00 -0.00 7 0 . 6 7 1 0 77 8 i -3.00 0 017 0 6 7 7 0 . 7 68 0.50 0 . 0i1 0 , 676 0 77 0 " " 1.00 -0.005 0.6 7 1 0 777 -1.25 0 . 068 0.692 0.7_5 j i 25 0 046 0 685 0.755 1.50 0.017 0 . 6 7 7 0 7 6 7 " " " 2.00 0.018 0.6 7 8 0 7 67 3.75 0.025 0.67g 0.764 2,50 0,024 0,679 0 7 64 3 . 7 5 0 , 035 0,682 0 7 59 ( b ) M _ffi O' 77 4 'a = 2" O 3 °' R % , _ffi l ' 9X lOS " l Fig u rel 7 . - Contin u ed. i , _ .. ., :, ..

! o - AIRFOIL dPPER SURFRCE

, NRCR 0012 RIRFOIL x / c Cp P / PT M

0.000 1.110 0.985 0.145 0.025 -0.134 0.546 0.971 -I.5 0.050 -0.639 0.468 1.066 ' 0.075 -0,79 7 0.443 I.I ' H ' 0.100 -0.866 0,423 1.180 o o o o 0.150 -G.966 0.395 1.237 - , -1.0 u 0.200 -t.052 0.3 7 0 1.281 0 o 0.250 -I.081 0.362 1.297 o M o 0.300 -i.124 0.350 1.32.3 3e -0.so-_p_ o o 0.350 -i.158 0.340 1.347 o [] o 0.400 -i.167 O,3_e 1.34e B o 0.450 -1.131 0.348 1.327 Op o.o o = 0.500 -0.584 0.504 1.040 o ° 888e, 0.550 -0.508 0.525 1.005 , 0.600 -0.407 0,554 0,95_ o.s 0.650 -0,310 0.582 0.915 0.700 -0,204 0.612 0.86_ ", 0.750 -0.110 0,639 0.827 _'° . 0,800 -0.036 O,6b_ 0, 7 95 0 850 0.015 0,674 0 7 7 2 J 0 900 0.070 0.690 0 7_£ : ' 0 930 0.099 0.698 0 73_ i_. 1.5 , I .... 0 950 0 . 126 0.706 0 724 : 0.o 0.2 0.4 o.s o.a .o 0 980 0.160 0. 7 15 0 709 '3 X / g * 000 0.193 0.7 . 5 0 694 i SIOEWRLL , Z / C= 1.375 • _ o - R1RFOIL LOWER SURF£CE X / C Op P / PT M X / C Cp P / PT M -3. 7 5 0.046 0.683 0.%8 -2.50 0 003 0.671 0.7;'7 0,025 0.203 0.728 0,689 -2.00 0.004 0.6 7 1 0.776 : " 0.050 -0.046 0.656 0.800 -1.50 0.009 0.6 7 3 0.7;4 ' 0.100 -0.291 0.587 0.907 -1.00 -0.036 0.660 0. / _ 0.200 -0.466 0.538 0,985 -0.50 -0.109 0.639 0,826 0.300 -0,473 0.535 0,989 0.00 -0.]04 0.641 0.824 0.400 -0.386 0.561 0,948 0.50 -0.094 0.644 0.819 0,500 -0.314 0,580 0,917 1.00 -0.053 0.655 0.801 0,600 -0.231 0.605 0,879 1.50 -0.032 0.661 0.792 0.700 -0,151 0.627 0.845 2.00 -0.009 0 . b68 0.782 0,800 -0,06 7 0.651 0,807 2,50 -0,009 0.6_8 0.782 0,850 -0,016 0,665 0, 7 86 3, 7 5 0,012 0.6 7 4 0, 77 3 0,900 0,038 0,681 0,762 0 . 930 0 . 065 0 . 688 0.750 0.950 0.098 0.698 0.735 SIOENRLL, Z / C =-1.3 7 5 _- 0.980 0.136 0.709 0. 7 19 X / O Cp P / PT !1 SIDEWALL , Z =0 -3,75 0.042 0.682 0. 7 60 -1 . 00 -0.010 0.66 7 0 . 7 83 X / C Op P / PT M -0,50 O.OOO 0.670 0.778 -3.75 0.061 0.688 0. 7 '52 0.00 -0.023 0664 0.788 _ ' -3 O0 0.009 0 6 7 2 0. 77 5 0.50 -0.011 0.66 7 0.783 " " ].00 -0.023 0.664 0.788 ": -1.25 0.054 0.685 0.755 1.50 -0.005 0.669 0.7_0 _.25 0.025 0.6 7 7 0.768 2.00 -0.006 0.669 0.781 3. 7 5 0.010 0.673 0. 77 4 2.50 0.005 0.6 7 2 0. 7 76 " 3. 1 5 0,021 0.6 7 6 0. 7 69 ; , ( c ) M_ = 0 .777, a = 2. 03 ". Rec ,_= 3 .9XI 0 _.

" " Fi g ure 17.- C ontinued , / 4 6 ,

!1 '

,!

"Z , I u- AIRFOIL UPPER SURFRCE i

, i NFICFI 0012 RIRFOIL x / c Cp P / PT M

! 0.000 1.093 0.980 0.168 " _ 0.025 -0.429 0.547 0.970 , -1.s 0.050 -0.625 0.491 1.061 0.075 -0.794 0.443 1.145 o 0.I00 -0.869 0.422 1.183 o o o 0.150 -0.963 0.395 1.233 • "l -1.o o 0.200 -1.056 0.368 1.285 o 0.250 -i.082 0.361 1.300

t °

_ o w o 0.300 -i.125 0.349 1.325 -o.s o Cp _ o -- 0.350 -1.152 0.341 1.34l : ! o [] o 0.400 -i.162 0 . 338 1.34 8 a o 0.500 -0.586 0.502 1 043 i " Op o.o n I 8 0.450 -1.103 0.355 1.312 _@e o, i 0.550 -0.498 0.527 1 002 o l 0.600 -0.384 0 . 560 0 949 0.700 -0,1 7 0 0,62t 0 854 0. 7 50 -0.089 0.644 0 819 0.800 -0,033 0,660 0 794 ii o.s 0.350 -0.276 0.591 0 901 t . o 0 . 850 0 . 014 0.673 0 774 1 0.900 0.064 0.688 0 752 : n_ _ i . s I I 0.930 0.094 0.696 0 739 , - , - . ' . , , 0.950 O.123 0. 7 04 0 726 o.o o2 .4 0.6 O.e l . O 0 . 980 0.157 0 . 714 0.71l X ,' O 1.000 0,202 0.72 7 0,691 SIDCNRLL , 2 / C= 1.375 o- RIRFOIL LOWER SURFRCE X / O Cp P / PT M X / C Cp P, ' PT M -3 . 7 5 0.030 0.6 ? 8 0 . 766 i -2.50 -0.011 0.666 0.784 [ 0.025 0,201 0.72 7 0.690 -2.00 -0 00 7 0.668 0.782 i_ 0,050 -0,033 0.660 0,794 -1.50 0.003 0.671 0.7 7 8 f 0.100 -0,293 0.586 0,909 -1.00 -0.042 0.658 0. 7 97 :} 0,200 -0,460 0.539 0,983 -0,50 -0,112 0.638 0 828 0.300 -0,474 0,534 0,991 _.00 -0.095 0.b43 0 821 ' 0,400 -0,384 0,561 0,948 0,50 -0,0£5 0.643 0 821 4 0,500 -0.318 0,5 7 9 0,920 1.00 -0.054 0.654 0 802 0,600 -0,235 0,603 0,882 1.50 -0.035 0,6_0 0 ?9{ ! 0,700 -0.158 0,624 0,_49 2.00 -0.014 0.666 0 785 :! 0,800 -0,0 7 0 0,650 0,809 2,50 -0,011 0,66 7 0 7 84 0 . 860 -0.020 0 . 663 0.789 3.75 P . Oil 0 . 673 0 774 0.900 0.035 0.680 0, 7 64 0,950 0,099 0.598 0,736 SIDEWALL,Z / C = -1.375 0.930 0.056 0.688 0.751 • SIDEWALL,2=0 -3.75 0.03_ 0.678 0 766 i 0.980 0,144 0,710 0, 7 17 X / C Cp P / PT M -1.00 -0.015 0.665 0 7 86 -3.75 0.049 0.683 0. 7 58 0.00 -0.028 0.662 0 790 -3.00 0 . 009 0,672 0.7 7 6 0.50 -0.006 0.668 0 781 -1.25 0.050 0.684 0.757 1.00 -0.028 0.062 0 791 1.25 0.024 0.676 0.769 1.50 -0.007 0.088 0 7 82 3.75 0 008 0 672 0.776 2.00 -0.009 0.667 0 783 i X / O Cp P / P T h -0.50 -0.002 0.669 0 780 " " 2.50 0.003 0 . 671 0 777 3.75 0.019 0.675 0 7 7 1 (d) M . -0 2 78, a -2.03 °, Re c , . =6.JX I 0 6.

FI _ I? .- Continued.

4 7 o - RIRFO[L UPPER SURFACE

NRCR 0012 RIRFOIL x / c Cp P / PT M

0.000 i.097 0.982 0.163

0.025 -0.418 0.550 0.965 -1.s- , 0.050 -0.620 0.492 ;.060 " / 0.075 -0.791 0.444 1.]43 o o o _ o 0.i00 -0.863 0.423 1.181 0.150 -0.961 0.395 ],233 -z.0_ o 0.200 -i.052 0.369 1.283 °° 0.250 -i .077 0.362 1.298 -o.s- o o o 0.350 -1.151 0.341 1.342 i °C_ W o 0.300 -1.122 0.349 1.324 ! [] o 0.400 -1.163 0.337 1.349 i 0.430 -l,lfiO 0.336 1.351 Cp o.o-'o _ m , _ 4--8 0.500 -0.612 0.495 1.056 @co 0.550 -0.521 0.520 1.013 o 0.600 -0.411 0.552 0.962 0.650 -0.300 0.583 0.912 0.5 .........

0.700 -0.188 0.615 0.863 0.750 -0.099 0.641 0,824 0 . 800 -0.035 0.659 0,795 1.0 0 . 850 0.014 0,673 0,774 0.900 0.056 0.6£8 0 . 75l 0.930 0.095 0.6@6 0. 7 39 _.s ..... o.qso 0.123 0.704 0.726 o.o o.2 c.4 o.B o.e 1.o 0.980 0.156 0.714 0, 7 11 X / C 1.000 0.199 0. 7 26 0.693 SIOENRLL , Z / C= 1.375 o- RIRFOIL LONER SURFRCE X / C Cp P / PT M X / C Cp P / PT M -3.75 0.03! 0.678 0.766 -2.50 -0.011 0.666 0.785 0.025 0.204 0 727 0.690 -2.00 -0.009 0.687 0.784 0.050 -0.039 0 658 0.797 -1.50 0.002 0.620 0.779 0 . 100 -0.301 0 583 0.913 -1.00 -C.042 0.657 0.798 0.200 -0.4 7 3 0 534 0.990 -0.50 -0.113 0.637 0.829 0.300 -0.49] 6 529 0.999 0.00 -0.083 0.646 0.816 0.400 -0._05 0 65 7 0.954 0.50 -0.099 0.641 0.823 0.500 -0.32 7 _.5 7 6 0.924 ].00 -0.052 0.654 0.802 0.600 -0.244 0.600 0.887 ].50 -0.036 0.659 0.796 .

i 0.700 -0.16 7 0.621 0.853 2.00 -0.017 0.664 0.787 0.600 -0.0 77 0.642 0.813 2.50 -0.014 0.665 0.786 i 0.850 -0.028 0.661 0._92 3.75 0.010 0.672 0.776 0.900 0.030 0.678 0.767 0.930 0.059 0.686 0.754 = 0,950 0.094 0.696 0.738 SIDEWALL , Z / C" -1.375 0.980 0.140 0.709 0.719 X / C Cp P / PT _i SIDEWALL Z'O -3.75 0.033 0 679 0. 7 65 • -1.00 -0.015 0 6_5 0.786 t X / C Op P / PT M -0.50 -0.002 0 669 0.781 0.00 -0.029 0 661 0.792 -3. 7 5 0.050 0.683 0. 7 58 0.50 -0.005 0 668 0.782 -3.00 0.[07 0.671 0.777 1.00 -0.031 0 660 0.79_ -1.25 0.051 0.684 0.758 1.25 0.023 0.6 7 6 0.7 7 0 1.50 -0.008 0 667 0.783 3.75 0.008 0.672 0.776 2.00 -0.011 0 6_6 0.785 i 2.50 0.002 0 670 0.779 ' 3.75 0.020 0 675 0. 7 71 "I I ( e ) M _ = 0 . 778 , a - 2 . 0 3 ° , Rec ,_ = 7.8 X 10 6 . ' Ft gu t e 1 7. - Cont _ue d .

:

4s

•-_ _ ' I Wmw._ _ _ :- . _-_ q .q ,: 4 "i

I

t I o - AIRFOIL UPPER SURFACE

f

NRCB 0012 BIRFOIL x / c Cp P / PT M 0.000 i.090 0,980 0.169 O.02E -0.431 0,549 0.967 0.050 - 0.634 0.491 1.061 -1.s r j 0.0 7 5 - 0.805 0.443 1.145 o _ o 0.100 - 0.8 7 8 0.422 1.182 o o 0.150 - 0.9 7 5 0.395 1.233

!

-1. 0 . ---_-- oo 0.200 - 1.06 7 0.359 1.284 0.250 - I.089 0.362 1.297 o _ o 0.300 - 1.136 0.349 1.325 - 0 .s.- _--_ - _ o 0._ q] - 1 . 164 q 341 1 . 341 o o o 0.400 - 1 . 1 7 4 0.338 1.3 4 7 o 0. 4 50 - 1 . 182 0.336 1.352 Op o.o [] o 0.500 - 0 . 608 0.499 1.049 # woo= 0.550 - 0 ,4 9 7 0 . 530 0.99 7 o I 0.600 - 0.364 0.568 0.937 0.650 - 0.246 0.601 0.884 o. s 0.700 - 0.149 0.629 0.842 ; 0.750 - 0.082 0.648 0.813 !

0.800 - 0,034 0.662 0.792 z.o L. 0 . 850 0 . 016 0.676 0. 77 0 * 0.900 C.061 0.688 0. 7 50 0.930 0.092 0.697 0. 7 3 7 [ l.s . -----,----- _---- - -----,-----------,------ 0.950 0.123 0. 7 06 0.723 o.o 0.2 o . 4 o.6 0.e 1.c 0.980 0.160 0. 7 !6 0. 7 0 7 X / C 1.000 0.212 0.731 0.684

l

SIOEWRLL,Z / C = 1.375 I o - AIRFOIL LOWER SURFACE _ / C C_ P / PT M i X / C Cp P / PT M - 3. 7 5 0.027 0.679 0 7 65 i -2.50 -0,014 0.668 0 7 82 0.025 0.212 0. 7 31 0.684 -2.00 -0.012 0.668 0 7 82 0.050 -0.036 0.661 0.793 -1.50 - 0.001 0,6 7 1 0 77 7 0.100 -0.295 0.587 0.906 -I.00 - 0.0 4 5 0 . 659 0 796 i 0.200 - 0. 4 66 0.539 0.982 - 0.50 - 0.116 0 , 638 0 82 7 I 0.300 -9. 4 7 8 0.536 0.988 0.00 -0.074 0 . 651 0 808 ,_ 0.400 -0.390 0.561 C . 948 0.50 -0.098 0.644 0 819 0.500 -0.320 0.580 0 , 917 1.00 -0.051 0 . 65 7 0 ? 99 0.600 - 0242 0.603 0,882 1 . 50 -0.032 0,662 0 7 90 0. 7 00 -0.164 0.625 0 . 848 2.00 -0.019 0,666 0 7 85 0.800 - 0.0 7 4 0.650 0.809 2.50 - 0.015 0.667 0 783 0.850 -0.023 0.565 0. 7 8 7 3. 7 5 O.Oll 0.674 0 77 2 0.900 0.03{ 0.681 0. 7 62 0.930 0.065 0.690 0. 7 48 0.950 0.101 0. 7 00 0. 7 33 SID E WALL,Z / C = -1.3 7 5 , 0.9 8 0 ? 151 0, 7 1 4 0. 7 11 X / C Cp P / P T M S[OEWRL L , Z - O - 3 . 7 5 0.031 0.680 0 7 6 3 - I.00 - 0,017 0.66 7 0 7 8 4 X / C 0 e P / PT M - 0.50 - 0.001 0.671 0 777 - 3 . 7 5 0 . 0 4 8 U .fi 85 0 . 755 0.00 - 0.02 7 0.6 6 4 3 788 - 3.00 0 009 0.674 0 773 0.50 - 0.002 0.671 0 777 • • 1.00 -0.033 0.662 0 7 91 -1.25 0.051 0.686 0. 7 54 1.50 -0.008 0,669 0 7 80 1.25 0.02 4 0.8 7 8 0. 7 66 2.00 - 0 . 013 0.668 0 7 82 3. 7 5 0.009 0.674 0.773 2.50 0 , 001 0.672 0 77 6 , S . 7 5 0 . 020 0 . 6 77 0 7 68 ( 0 M . = 0 . 77 5,a = 2 . 05 _, Re c, , • 9.9 X 10 6.

F ti ure 17 .- C o ncl uded.

o _-

• o - AIRFOIL UPPER SURFRC£

NRC£ 0012 AIRFOIL x / c Cp P / PT M

, 0.000 0.94 0 . 947 0.279

0.025 -0.882 0.466 1.104 -1 . s , 0 050 -1 . 023 0 . 429 1 . 170 oo o o o o 0 100 -1 . 214 0 . 378 1.265 I 0 075 -1.155 0,394 1.235 -1.o._._ ....... : 0 150 -1,287 0.359 1.304 o ! 0 200 -1.332 0.347 1.329 0 300 -1.223 0.376 1.2 7 0 ---Op " ] 0 250 -1.239 0.3 7 2 1.2 7 8 ,, -os _ 0 350 -1.230 0.3 7 4 1.274 o 0 400 -0.767 0.496 1.053 • a I o o ° 0 o 0 450 -0.478 0.5 7 2 0.929 OF o.o" a 0 500 -0.336 0.610 0.871 8888 0 . 550 -0 . 254 0.632 0.83 7 o 0.600 -0.169 0.654 0.803 o . s _ ....... 0.650 -0.138 0.662 0.791 0.700 -0.097 0.673 0.774 _ 0.750 -0.050 0.685 0. 7 55 0.800 -0.00 7 0.697 0.73 7 !.o 0 . 850 0 . 048 0 . 7 11 0.715 0.90n 0.096 0. 7 24 0.695 :_ 0.930 0.124 0.731 0.684 1.5 ...... 0.950 0.151 0.739 0.573 o.o .2 0.4 o.6 o.8 .o 0.980 0.1 7 7 0. 7 45 0.652 X / C 1.000 0.210 0.754 0.648 SIDEI4RLL , Z / C = 1.3 7 5 o-AIRFOIL LOWERSURFACE X / C Cp P / PT M X / C Cp P / PT M -3 75 0.0 7 9 0. 2 20 0.701 -2 50 0.04 7 0. 7 12 0. 7 14 • 0.025 0.489 0.828 0.526 -2 O0 0.u44 O. 7 tl 0.715 ' 0.050 0.231 0. 1 59 0 . 640 -I 50 0.031 0. 7 08 0.721 0.100 -0.022 0.693 0.744 -1 O0 -0.005 0.698 0. 7 35 0.200 -0.193 0.649 0.811 -0 50 -0.073 0.680 0.763 0.300 -0.22 7 0.639 0.82 7 0 O0 -0.012 0.696 0.738 0.400 -0.206 0.645 0 . 81 7 0 50 -0.047 0.687 0. 7 52 0.500 -0.188 0.649 0.8t1 1 O0 -0.041 0.689 0.750 0.600 -0.]40 0.663 0. 7 90 ].50 0.008 0.701 0.730 0. 7 00 -0.0 77 0.578 0. 7 66 2.00 0.027 0.70 7 0.722 0.800 -0.02 7 0.692 0.744 2.50 0.010 0.702 0.729 0.850 0.024 0. 7 05 0.725 3.75 0.044 0 . 7 11 0. 7 15 O. 900 O. 059 O. 7 t 5 O. 7 09 0 . 930 0.085 0 . 7 21 0 . 700 0.950 0 . 104 0 . 72 7 0.691 5IO£1,1RLL , Z / C"-1.3 7 5 0.980 O. 139 0. 7 35 0 . 6 7 8 X / C Cp P I PT 1'1 51DENRLL , Z'O -3. 7 5 0.089 0. 7 23 0.697 -1 . 00 0.042 0. 7 11 0. 7 16 X / C Op P / PT M -0.50 0.052 0. 7 13 0. 7 12 -3. 7 5 0.095 0.724 0.695 0.00 0.032 0. 7 08 0. 7 20 -3.00 0.011 0. 7 02 0.730 0.50 0 . 039 0. 7 10 0 7 1 7 -1.25 0.093 0.724 0.696 1.00 0.027 0.707 0 7 22 1.25 0.041 0.710 0.717 ].50 0.032 0. 7 08 0 7 20 3.75 0.050 0.712 0.714 2.00 0.026 0.706 0 723 2.50 0.046 0.712 0 714 3. 7 5 0.056 0. 7 17 0 7 0 7 ) (a ) M , , ,, 0.7 , 14, a • 4. 04 ° , a ec, - " ) . O X |0 i .

. F @ ure 1 8 .- Airf o il _ d lest c l_m ne l_i d e w alli)t_ u t e m euu t e m ee t, , I:_ ta _ t 6 ('_'A' • 0. / 25, a N • 4 "} .

,- -I - _ % : ;:'1 5 0 "

.-a_-

- " , - - 4 ml , r .

I Y o - RIRFO[L UPPER SURFACE

NRCR O012 RIRFOIL ×zc Cp P / PT M

0.000 0.910 0.939 0.301 0.025 -0.943 0.452 1.128 -1.s o 0.050 -1.075 0.418 1.190 o o o 0.075 -1.211 0.382 1.259 °° 0.100 -1.265 0.367 1.287 , o 0.1&O -1.352 0.345 1.333 -i.0 o 0.200 -i 401 0.332 1,3fiI . 0.250 -! 424 0.326 1.375 ---Cp 0.300 -I 363 0.342 1.310 ,, * -o.s o 0.350 -I 348 0.3 4 6 1.331 o 0.400 -0 944 0.452 1.129 a o o o 8 o 0.450 -0 516 0.564 0.942 Cp O.O n - 0 500 -0 332 0.613 0.866 o _ 0_©0, 0 550 -0.253 0.634 0.834 0 600 -0.193 0.649 0.810 0.s _ 0 E50 -0.1_8 0.656 0.800 0 700 -0.130 0.666 0.785 0 750 -0.090 0.678 0.769 0 800 -0.040 0.689 0 , 749 • 1.0 0 850 0.028 0.707 0.721 ; 0, 9 00 0.062 0.716 0.707 0.930 0.093 0. 7 25 0.894 I : - l .s _ , , , . . 0.950 0.127 0.733 0.681 o.o 0 . 2 0 . 4 o . _ o.B . o 0.980 0.165 0.743 0.665 X / C 1 . 000 0.206 0.754 0,648 SIDEWALL , Z / C = 1.3 7 5 o- AIRFOIL LOWER SURFACE X / C Cp P I PT d 'I X / C Cp P / PT M -3.75 G.OSE r]. 1 16 0.708 i -2,50 O . OIO 0 . 703 0 , 727

t

0,025 0,472 0,824 0,53_ -2.00 0.0,3 0. 7 04 0.726 0 050 0.220 0. 7 58 0,542 -1 50 O.d08 0.703 0.728 0 100 -0.035 0.691 0,746 -1 O0 " 0 036 0.691 0,746 0 200 -0,208 0.646 0,813 -0 50 -0,103 0,674 0.773 0 300 -0.240 0 , 637 0.830 0 05 -0.03 7 0.691 0 . 7 46 0 400 -0.222 0.643 0,821 P 50 -0.0 7 8 0.680 0. 7 63 0 500 -0.194 0.649 0 . 811 1 O0 -0 . 057 0 . 686 0 .7 54 I' 0 600 -O.lll 0.664 0.788 1 50 -0.024 0.695 0, 7 41 0 7 00 -0.090 0.676 0.769 2 O0 0.000 0.701 0. 7 31 0 800 -0.038 0.691 0.747 2 50 0.002 0.701 q.730 0 850 0.004 0.701 0.731 3 7 5 0.026 0. 7 06 0. 7 20 0,900 0,052 0. 7 14 C . 7 10 0.930 0.078 0,721 0.701 0.950 0,10 7 0, 7 29 0,688 SIDE W ALL , Z / 0 - -1.3 7 5 q 0.980 0,1t1 0, 7 3 7 0,675 X / C Cp P / P T M • SID E WALL , Z -O - 3. 7 5 0.0 69 0. 7 1 9 0 7 03 -1 . 00 0.02 7 0. 7 08 0 7 20 X / C Cp P / P$ M -0.50 0.03] 0.709 0 7 19 , -3 . 7 5 0.0 7 5 0. 7 20 0 . 7 01 0. 0 0 0 . 019 0 . 706 0 7 2 4 - 3.00 0.0]3 0.703 0.727 0 . 50 0.024 0 . 707 0 721 -1 . 25 0 . 07 7 0.721 0. 7 01 1.00 0.008 0 . 7 03 0 7 2 8 1.25 0.044 0. 7 12 0. / 14 1.50 0.023 0. 7 0 7 0 ? 22 ; 3 . 75 0 . 032 0.7 09 0. 719 2 , 0 0 0,020 0.706 0 7 23 2.50 0.030 0. 7 0 9 0 7 19 3. 1 5 0.055 0. 7 15 0 7 09 IL

0 ,)M. - 0 .732 . a - 4. o 6" , R, c , . - 1 .9x l o ' . , I

,,-,"_ i_F-qilll, r,,,- ,_ ' " "_t O • _-_31m ' _ o- RIRFO[L UPPER 5URFRCE

NRCFI0012 RIRFOIL × / c Cp r / P: M

0.000 0. e 79 0.932 0.315

. - 0 . 025 -0.992 0 . 44_ !.144 0.05° -1.112 0.412 i.201 -!.5 - _ o o r o / | 0.075 -1.247 0.37 7 1.26_ °° 0.I00 -1.293 0.365 1.297 -1. a -e,-- - o 0.200 -1.423 0.351 1.3fl_ ' _ o 0.250 -l.450 0.324 1.379 ---Cp o 0 . 300 -1.48l 0.31b 1.39 7 -o.s 0.350 -0.880 0.473 1.093 r o _ 0.150 -1.36 7 0.34S 1.332 "* 0.40n -0.781 0.498 1.049 H - I

: j o o s _ 0.450 -0 . 705 0.5_ 1.01_

0.500 -0 . 59! 0 . 548 0 . 96_

Cp o.o i • _ ----_-_-_ o_--_ 0 . 550 -0 . 453 0.584 O . £lt

- _ o 0.600 -0.304 0.623 0 . 651 0 . 650 - 0 .216 0 . 646 0 8!E os _ T 0.700 -0.148 0.6_4 0. 7 68 :

i

' 0.800 -0.042 0.691 0.74£ ;.o] 0.850 0.018 0 . 707 0.722 i ' } 0 . 930 0.0 77 0 . 722 0 . 6£6 ' 1 0.900 0 . 050 0 . 7!5 0 . 70£ _ 1.s_ . • i . ---- --- 0.950 b.102 0.729 0.68_ l _ 0.750 -0 . 095 0.S 7 7 0.767 o.o 0.2 0.4 o.6 ---' o . a i.o 0 . 980 O.lX3 0.73 7 0.675 t X / C 1 . 000 0.167 0 . 745 0 . 66_ SIOEWRLL , Z / C- [.3 7 5 i o- RIR r OIL LOWER SURFFCE X t C Op ° / PT M I -3.75 0.038 0 . 7 1". 0.7.4 i X / C Cp P / PT M -2.50 -0.008 0. 7 60 0. 7 32 0.025 0.4 7 2 0.826 0.530 -2.00 -0.00£ 0. 7 01 ]. 7 bl .

0.050 0.218 0. 7 59 0.640 -1.50 -C.003 _. 7 01 0. 7 30 ' 0.100 -0.036 0.693 0. 7 43 -1.00 "0.054 0.688 0.751 0.200 -0.195 0.651 0.807 -0.50 -0.125 0.569 0. 1 79 0.300 -0.248 0.638 0.828 0.00 -0.049 0.689 0.749 : 0 . 400 -0 . 221 0.644 0 . 818 0.50 -0.098 0.t 77 0 . 768 0.500 -0.19 7 0.651 0.808 1.00 -0.069 0.684 0. 7 5 7 0.600 -0.15! 0.663 0. 1 90 1.50 -0.040 0._92 0.7_5 0.700 -0.106 0 . 675 0 . 771 2 . 00 -0.013 0 . 699 0 . 734 : 0 . 800 -0.045 0 691 0.747 2.50 -0.009 0 . 7 00 0.733 0 . 950 -0 . 009 0 700 0. 7 32 3.75 0 . 016 0.706 0.723 n.900 0.037 0 7 12 0. 7 14 0.930 0.056 0 7 1 7 0. 7 06 ' 0.950 0.082 0 724 0.695 SID E WRLL, Z I C " -1.3 7 5 0 . 980 0.116 0 733 0.682 X / C Cp P / P T Pi SIOEWRLL Z = O -3 . 75 0 047 0.714 0.7!0 • -1.00 0 012 0 . 7 05 0. 7 24 X / C C p P / PT M -0.50 0 022 0.708 0. 7 20 -3. 7 5 0.058 0. 7 1 7 0 . 705 0.00 0 014 0. 7 06 6 . 723 -3.00 0 013 0. 7 0 6 0. 7 24 0 . 50 0 01_ 0. 7 0 6 r1 . 7 23 " 1.00 -0 001 0. 7 02 0.7_9 -1 . 25 0 . 0 6 2 0, 7 19 0. 7 04 1 , 5_ 0 Oil 0. 7 05 0 , 725 1 . 25 0.028 0.710 0.718 2.00 0 002 0 . 703 0. 7 28 3 . 7 5 0.016 0. 7 0 6 0. 7 23 2 . 50 0 01 7 0 . 7 0 7 0 . 7 22 3. 7 5 0.041 0 . 7 13 0 . 7,3 (¢ ) M ." 0. 7 29, a - 3. 9 3 ", Re c , .. 3 , 9 XIf#.

Fi s u t e 18 . - C o nf e t ti.

,t 52 b r I 'k ,- o-fllRFOIL UPPER SURFACE

NRCR O 01 2 R i RFOI L x / c Cp F / P]" M

< O.000 O.863 O.928 O.328 - _ 0.025 -0.990 0.446 1.!40 = -i . _] _-o r, --q 0 . 050 -I . 098 0 . 418 1 . 190 °° f 0.!00 -1.302 0.364 1.293 1 o 0.075 -1.253 0.3 7 7 1.26 7 o 1 0.150 -1.375 0.345 1.332 " o 0.200 -I 429 0.331 1.362 • _ _, _ c , 0.250 -I 456 0.324 1.377 -i.o I o ] -o . s o 0.350 -0 899 0.4 7 0 1.098 ': 0.400 -0 800 0.495 1.055 ' o o o @ o 0.450 -0 7 10 0,319 1.016 L T -_P o J 0.300 -I 490 0.316 1.397 0.500 -0 582 0.552 0.962 ,, Cp 0.0 --- --@-_e@_ 0.550 -0 432 0.591 0.900 i o 0.600 -0 292 0.62 7 0.844

|

' 0.650 -0 214 0.648 0.813 0.5 !_n ]_ . 0. 7 00 -0 155 0.663 0. 7 89 • J / 0. 7 50 -0 I01 0.6 7 7 0.767 _ . 0.800 -0 052 0.690 0.748

I '

, , i o , 0.850 0 0]2 0. 7 0 7 0 . 722 " - _ , ' 0.900 0 042 0.7]4 0.719

• ] _ 0.930 0 0 7 1 0. 7 22 0.698

1.5_ • 0.950 0 098 0.729 0.687 "- o.o 0.2 o . 4 o . 6 o.8 1.o 0.980 0 129 0.73 7 0.675 X / C 1.000 0 164 0. 7 46 0.661 S[OENRLL , Z / C = 1.375 :_ o- RIRFOIL LOWER SURFBCE X / O Op P / PT M " X / C Cp P / PT M -3 75 0.025 0.71.1 0.7i6 -2 50 -0.020 0.699 0.734 0.025 0. ' {66 0.823 O 53i -2 O0 -0.02i 0.699 0 .7 34 0.050 0.229 0. 7 63 0 634 -1 50 -0.015 0.70] 0.732 0.]00 -0.029 0.696 0 739 -1 O0 -0.066 0.68 7 0.752 0.200 -0.204 0.652 0 80 7 -0 50 -0.135 0.669 0. 7 80 0.300 -0.253 0.638 0 828 0 O0 -0.052 0.69 1 0.747 0.400 -0.22 7 0.6 ' t6 0 816 0 50 -0.10 7 0.6 7 7 0. 7 68 0.500 -0.203 0.651 0 808 1 O0 -0.076 0.685 0. 7 56 , 0.600 -0.]64 0.562 0 7 9] _ 50 --0.053 0.691 0. 7 _ 7 0. 7 00 -0.]t6 6.673 0 77 4 2 CO -0.024 0.698 0. 7 35 0.800 -0.054 0.690 0 7 4 7 2 50 -0.018 0. 7 00 0.733 0.850 -O.Ot8 0.699 0 7 34 3 7 5 0.008 0.706 0. 7 23 G.900 0.025 0. 7 tl 0 7 15 ., 0,930 0.048 0.7t6 0 708 ; 0 950 0.0 7 5 0. 7 24 0.695 S[DENRLL. 2 / 0 = -t.3 7 5 • _ 0 980 O. lt4 0. 7 33 0.681 ' X / 0 r, P / PT M •; ,( _p ' " SIDEWALL, Z=O -3.75 0 . 036 0. 7 14 0.711 --l . O0 C . 000 O. 7 04 O. 7 z5 : _i X / O Cp P / PT M -0.50 0.012 0. 7 0 7 0. 7 21 : _ 0.00 0.006 0. 7 05 0. 7 23 -3.75 0.050 0.717 0. 7 06 0.50 0.009 0.707 0.722 ' i --3'00 0.010 0, 7 06 0. 7 23. 1.00 -0.017 0.700 0. 7 32_ , t . 25 0.05_ 0. 7 18 0 705 1.50 0.001 0.705 _,. 7 ,, 5 1.25 0.021 0.709 0.718 2.00 -0.007 0.702 0.729 _ 3.75 0.010 0.706 0 . 722 2.50 0.007 0.706 0.723 _ 3. 7 5 0.031 0. 7 12 0. 7 13 ,

|

(d) M o_= 0 2 2 7 , a = 4 . 04 ° , Re c , _ -- 6 . 1X 106.

F i g u r e 18. - Con t inued.

5 3 ,.

w" ......... ' "-, _ ,& " -'B z o - RIRFOIL UPPER SURFRCE

NRCR 0012 AIRFOIL x / c Cp P / PT M

0.000 0.865 0.929 0.326 0.025 -0.994 _.447 1.136 -1 . s 0.050 -1.113 0.417 !.192 0 o 0.i00 -1,319 0.363 1.295 o _ v _-- 0.075 -1.270 0.376 1.270 o 0.150 -1 . 390 0,345 1.333 -1 . 0 -[ o 0.250 -1.470 0.324 1.3 7 8 ---Cp o 0.300 -1.508 0,314 1.399 _ o 0.200 -1.444 0.331 !.363 -o.s- 0.350 -0.946 0.460 1.115 0.400 -0.812 0.495 1.055 o o @ o 0.450 -0.706 0.522 1.010 0.500 -0.554 0.561 0.94 7 tp 0.0 _____o .... I_ @ _ _@ _l 01550 -0.394 0.603 0.882 [] 0.600 -0,269 0.635 0.832 0 . 5 o __ 0.650 -0.204 0.652 0.806 0. 7 00 -0 . 156 0 . 665 0.76 7 0.750 - 0.I04 0.678 0.766 0.800 -0.056 0.691 0.747 1.0 I 0.850 0.012 0. 7 08 0.720 0.900 0.04] 0.716 0.70 7 !

I 0.930 0.074 0.724 0,695 ' II , , , I , 0.950 0.!03 0.732 0 . 663 1.5 o.o o . 2 .4 o . 6 o.8 1 . o 0.980 O.138 0. 7 41 0.669 X / C 1.000 O.182 0. 7 52 0.651 i I S_DENRI.L, Z / C = 1.375 i o - RIRFOIL LO_ER SURFRCE X /' C Cp P I PT M _ X / C Cp P / PT M -3 7 5 0.027 0. 7 12 0. 7 14 !

-2 50 -0.017 0.700 0.732 0.025 0.475 0.828 0.525 -2 O0 -0.019 0.700 0 .7 33 0.050 0.236 0.766 0.629 -! 50 -0.011 0.702 0. 7 30 0.i00 -0.029 0.698 0.736 -1 O0 -0 . 064 0.688 0.751 0.200 -0.202 0 . 653 0.804 -0 50 -0.134 0.670 0.779 0,300 -0.255 0.839 0,826 0 O0 -0,049 0.892 0. 7 45 i 0.400 -0.226 0.647 0.813 0 50 -0.I07 0.677 0. 7 68 " 0.500 -0.205 0.652 0.806 I O0 -0,0 7 4 0 . 685 0, 7 55 ,,_ '! 0.600 -0.164 0,663 0.789 1 50 -0.046 0.693 0. 7 44 q 0.700 -0.118 0.674 0. 7 72 2 O0 -0.023 0.699 0, 7 35 0,800 -0.053 0.692 0.745 2 50 -0,016 0. 7 00 0. 7 32 0.85n -0.015 0.701 0.731 3 7 5 0.009 0. 7 07 0. 7 22 - 0.900 0.028 0.713 0.712 0.930 0.054 0.719 0.703 I 0.950 0.082 0.727 0.691 SIDENRLL, Z l C = -1 . 375 0.980 0.125 0.73 7 0 674 ! " R I O Op P / PT M SIOENALL, Z=O -3.75 0.039 0. 7 15 0. 7 10 -1.00 0.002 0.705 0.724 X I O Cp P / PT M -0.50 0.014 0.708 0. 7 20 : 0 O0 0.00 7 0. 7 06 0. 7 23 -3. 7 5 0.053 0. 7 18 0. 7 04 -3.00 0.011 0. 7 08 0.720 0.50 C.0 1 0 0. 7 07 0.721 -1 . 25 0.053 0. 7 18 0 .7 04 1.00 -0.015 0. 7 01 0. 7 31 1 . 25 0.02 7 0 . 211 0. 7 15 1.50 0.004 0. 7 06 0. 7 24 3.75 0.011 0.70 7 0 721 2.00 -0.009 0.702 0. 7 29 : " 2.50 0 . 008 0. 7 0 7 0. 7 22 " _ 3. 7 5 0.034 0. 7 13 0. 7 12 ; (e) M , = 0.725, a = 4.04 ° , Re c _ = 7.9X 10 6 .

F igu re 1 8 .- C on t i nu e d .

j 5 4

k o - RIRFOILUPPER SURFRCE

NRCR 00!2 RIRFOiL x / c Cp P / PT M

0.000 0.84 7 0.924 0.33 7 0.025 -1.017 0.440 1.150 - : .5 j _ - _ 0.050 -I.153 0.405 1.214 , oO o l 0.075 - 1.291 0.369 1.2_4 o ! 0.i00 -1.341 0.356 1.310 ' -i.oo j 0.150 -1 . 409 0 . 338 1 . 347 o 0.200 - 1.462 0 . 325 1.377 0.250 -1.489 0.318 1.393 ___i_ 0 _ 'p 0.300 -1.522 0.309 1.412 -0 . s o 0.350 -0.955 0.456 1.121 0.400 -0.823 0.490 1.063 o @ o 0.450 -0.711 0.520 1.014 .

0.500 -0.550 0.56! 0.947 gp o . 0 _ 4_ _ @ _o_ 0.550 -0.388 0.603 0.881 o 0.600 -0.270 0.634 0.834 0.650 -0.206 0.651 0.808 o.s o .... i 0,700 -0.157 0,663 0,789 0. 7 50 -0.i07 0 . 676 0.769 0.800 -0.058 0.689 0.749 1.o..... 0.850 0.014 0.708 0.720 0.900 0.041 0.715 0.7]0 1 . s l ( 0 . 930 0 . 072 0.723 0.697 ' , , , , , 0.950 O.lOt 0.730 0.685 0 . o 0.2 0 . 4 0.6 0 . 8 1 . 0 0.980 0.136 0.740 0.671 r X / C 1.000 0.181 0.751 0.652 t SIDENRLL , Z / C= 1.375 o - RIRFOIL LONER SURFRCE X / C Cp P / PT M i, X / C Cp P / PT N -3 75 0.022 0.710 0.717 I -2 50 -0.020 0.699 0.734 0 025 0.486 0,830 0,522 -2 O0 -0.023 0.698 0.735 0 050 0 . 244 0.768 0.627 -1 50 -0.016 0.700 0.732 " 0 I00 -0.021 0.699 0.734 -I O0 -0.069 0.686 0.753 !

3 200 -0.198 0.653 0.805 -0 50 -0.140 0.668 0.782 0 3_ -0.251 0.639 0.826 0 O0 -0.048 0.692 0.745 : 0 . 0 - 0.224 0 . 646 0 . 815 0 50 -0 , 110 0.676 0.770 0 500 -0 200 0 . 652 0.806 1 O0 -0.074 0.685 0. 7 55 0 600 -0 165 0.661 0.792 I 50 -0.049 0,692 0. 7 45 i 0 700 -0 118 0,6 7 4 0, 7 73 20u -0,029 0.69 7 0. 7 57 ' 0,800 -0 054 0,690 0. 7 48 2 50 -0,0!9 0.699 0.733 0.850 -0 016 0. 7 00 0.732 3 75 0.007 0.706 0, 7 23 0,900 0 026 0,7ll 0, 7 t6 0,930 0 051 0, 7 18 0,705 0.950 0 079 0.725 0.694 SIBENRLL, Z / C=-1.375 ' 0.980 0 125 0, 7 37 0.675 X / C Cp P / PT H SIDENRLL , Z = 0 -3 76 0.034 0 . 713 0.712 -1 O0 -0.001 0. 7 04 0.726 X / O Cp P / PT M -0 50 0 . 013 0 . 708 0. 7 2 1 -3.75 0.050 0.717 0.706 0 O0 0.006 0. 7 06 0. 7 23 0 50 0.009 0. 7 07 0. 7 22 -3.00 0.011 0. 7 07 0. 7 2! 1 O0 -0.019 0,699 0.734 -i.25 0.052 0.718 0.705 ! 50 0.002 0.705 0.725 1.25 0.023 0. 7 10 0. 7 1 7 2 O0 -0.011 0.701 0. 7 30 3.75 0.010 0. 7 0 7 0. 7 22 2 50 0.005 0.705 0.724 3 7 5 0 . 031 0 . 7 12 0. 7 13 ( O M _ = O. 7 2 6, _ = 3 .9 1 °, Rec , _ = 9 . 3 x106. i ' t Fi gu re1 8. - C o nc l u de d.

5 5 _ ' _ - TESTS CONDUC T ED AT M _ = 0.75, _ = 2 ° , Rec , oo = 107 =, UPPER . LOWER WALLS: O STREAMLINED FOR _ = 2 ° • STREAM L I N ED FOR _ = 0° _ ( " OFF DESIGN " ) _ ' - 1.2 • -.8 I C p _ - , 4 ?

: 0 . 4 " " 0 .2 .4 .6 .8 1.0 = _ - x / c _ ' " (a ) "Of f de s ign" in a ng le of att a ck.

TE S T S C OND U CTED A T Moo = 0. 7 7 5 . _ = 2 ° . R%. oo = 107 U PPER . L OW ER WAL LS : ' - O STREAMLINED FOR M _ = 0 , 775 • STREAM L I N ED FOR M = = 0.75 0 ( " OFF DES I G N" ) -. 8 - .4 • i

' 2 _ '6 '8 ,0

x / c (b) "O ff d e sign" in Ma c h numb er .

_ F i g u re 19.- E ff ects o f off d es ign w all co n tour in g on ai r f o i l pressure coe ffi c i e n t . '

5 6

" , .20 Mo o = 0 . 725 M == = 0.75 , 1 5 " 1 _" . . . ... . .. , O ' _ Cn / a .10 n _ i / r _ T _ 2 1 r _ T . 0 5 O 0.03 0.008 0 0.03 0 0 o o .- I _ I I 0 .01 .02 .01 .02 6" / (b / 2) Figur e 2 0 .- E ff ec t o f si d e w al l bo u nd a ry-lay e r d is pla cem e nt th i ckness on nor mal f o rce coef fi c i e nt.

PRESEN T TESTS , Rec, =_ = 10 7 / I NCOMPRESSIBLE FLOWTHEORY WITH / K / _ RM / _ N-TSIEN SCALING(REF. 7) _ / A . 2 ,. - W / L J .__.. 4) .__- - , e "-'°' 4r" 0 0 0 0 0 0 0 . 1 REF.6 , Rec oo " 8 X 106W I TH T RANSIT I ON F I XED AT 5% C HORD: O UNCORRECTED D CORRECTEDFORWALL INTERFEREN C E , AG= - 1.55 Cn O/ I i ' ,5 .6 ,7 ,8 M == i Fig u r e 2 1 . - Co mpa riso n of p resen t test results with me a sur e ments a nd estimates from references 6 an d 7.

F !

,!

Fi gu r e 22 .- Enve l opes o f press u re d eviat io ns fro m the m ea n , Da t a Se t S ( MN : 0 .77 5, aN = 2° ) .

i

l 58 6 I ¢ I I , , +, , ...+ _ +_ 2 . . ..... +_,C . if.

+ ,+ • , ri F ig u r e 2 3 . - W a ve f or m s a t a = 4 °, D a t a S et 5 ( M N = 0 .77 5 , _ N = 2 °)" i I , 62 , ,_ l _, .

i

OF , P OORQUALITY

UPPERSURFACE ! LOWER SURFACE

i

/ 1 1 1 6 N ¢ !

t

Fi l ure 24. - Comp a ris o n of upper and lower surfacewave fo r ms;a = 4 ° , M _ = O , 7 ? 5, Rec, _ = 10 _ (Data Set S ).

!

t

i"

L " i . MN a N DATA SET O PEN: SENS O R AT x / c = 0.5 O 0.725 4 6 CL OS ED: SENSOR AT x /c , 0 . 8 I " J 0.75 2 1 UNFLAGGED: < _ INCREASING ( _ 0.77.r ; 2 5 _. FLAGGED: a D E CREASING - /_ 0. 8 0 I 4 r " 0 8 0 0 3

5 •

. 4 j : W 0

,, • •

3 _ •

0 • El' 4 ,.

dig o m, qP 072 I i , i J , , , i .- .74 .76 .78 . S 0 .82 .72 .74 .76 . 78 .I J 0 .82 .r : •_ . M _ M ©_ b * "_ (a) Rec ,o . = IX 10 6 . (b) Re c , , _ = 2X 10 6 , M N a N DATA SET OP E N: S ENSOR AT x / c = & 5 O 0.725 4 6 CLOSED: SENSOR AT x / c = 0.8 El 0.75 2 1 UNFLAGGED: a INCREASING _ 0.775 2 5 FLAGGED: _ DECREASING A 0.811 I 4 I_ 0.80 0 3

• ¶

I I i i I I I I i I .72 .74 . 71 1 .78 , S 0 12 , 72 .74 .7 8 .7B S O .112 M _ .. M.

(c) Rec ,. = 4 X 10*. (d) R e c ,. = 5 X 10'.

F igure25.- An_ e of attack for buffet ons e t.

m J

;:) i

| MN a N DATA SET OPEN: _ ENSOR AT x / c - 0.5 O 0.725 4 6 CLO S ED: SENSOR AT x / ¢ - 0 , 8 D 076 2 1 UNFLAGG E D: a INCR E ASING O 0 . 775 2 5 - _ FLA GG ED: a D E CREAJ;IN G A 0. 8 0 1 4 : _ 0. 0 0 0 3

' r 5 r

3 _ - _ a 0 . dee " _ _ i _ - % %

' N

0 • ' ' I _ i i , i _, .72 . 74 3 0 .711 . 0 0 .82 .72 .74 3 6 .70 . E O .82 Me, M N (e) R ec ,.. = 8× lO'. (f) Rec ,.. = fO X lO'.

Figure2 5 .- Conc l ud e d.

i •

O RIG _ A L PA _"_ E _ , _ OF POOR QUALIT' _ f Fis ure 2 6. - Flo _ .fleld = h =d O _ l _ r = phs; M , _= O.' / S, _ = 2_ (Dat = SetI, M N = 0. 7 5, = N • 2 ").

* , . i ORIGINA l . PA(]E" 1_ " . OF POOR QUALi'r _ , t ,4 1,0 .4 Fi g ur e 27,- Flo w-f ield s h adow g raph s ; M = o= 0 .8, a = 0 = (D at a Set 3, M N = 0. 8 , = N = 0°) " 6 7 i .... I • I "-_ .2 .4 .8 1 . 0 : 2 . 4 .6 .8 1.0 Figure28.- Flo w- field s hado w g ra ph s ; M _ = 0.8, a = 1° ( D ata Set 4, MN = 0.8, a N = 1°).

68 _ ' ..................................... • . . _ r -_ - ..-" .s-. " - -, .- - ., • .6 ----_-- - '_ . 4 .6 .8 .0 1.0 x / c x / c i i _ .0 , Figure 3 0.- Flow.field s h adow g rap h s; M _ o = 0. 725 , _ = 4° ( DataSet6, :' f N -- 0.7 25 , c_ N = 4 °) .

_-_- ...,--. _ r _m l l. _ _ : . . . . _, _ OE POO ff q u_ , _i ,', _.

t Figure 31 . - F low-field shado w graphsshowing effect o f a n gle o f attac k ; M oo= 0 . 75, Rec, oo= 6X l 0 s (Data Set 1 , MN= 0 . 7 5 , _ N -- 2° )._B_-3. 2 °.

71 i _ .

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t ; Fi g u re 32. - F low- fi eldshadowgrap h s sho w ingeffe c t o f an g l eof attac k; M _ = 0.8, Rec , oo = 6X 10 6(D a t a S e t 3, " , M N =0. 8 , _ m -- 0°) • c '8_" 1.30.

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. F ig ure 33 .-- F low- fi eld s hadowgraphsshowin g e f fect o f angle of a tt ac k; M _ o = 0.725, R ec , _ = 6 X 10 6 (Data Set 6 , ; , : _ MN = 0.725 , e N = 4 ° ). aa _- 3.9 ° .

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M _ B V _ ETONSET

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_ , deg 0 I -4 | | L I - 6 .2 . 4 .6 . 8 X / C Fi g u re3 4.- Appr oximate c h ord wi s el o ca ti on o f ba se of s hock w ave , Re c, o . = 1 0 T.

I 7 4 _ ' :i 1. R ,_t _. 21 G ,_m ,, _t_- t ._, , t i*i 3 . R _i 0 _,', c . t .,o g _,.

NASA T P- 2 485 4 . T i tle a n d Subt i t le § . Repo r t Di ll) STAT I C AND D Y N AMIC P RE SSURE MEASUREMEN T S ON A June 1985 NACA 0012 A IR F O Il . IN T HE A M E S HIGH R EYN OL DS N UM B ER e. Pt a orm i_ O , _ ,i,t i_C o _ FACILI T Y ., . ..

? Au t h or ls) 8 . Pl r l oeming Orglmza t ion Ael:ort NO .

John B. McD e vitt and Arthur F. Okuno 85100 ....... _ o , w _wu , _ t ,&,. " 9 P m 'fo _ m m g Organ J z l l ti on Name l ln d Addre s s Am es R e s e a rch Center 11. Contr a ct or Gr l ln t No .

Mo ffe tt F i e ld , C A 940 3 5 " i3 . r y l_ of Re o o r t l ind Pl ¢ i od Covl , ' m l 12 S pomo r , ng Age n cy N a m e an d Address Te c hn ica l P a per Na tiona l Ae ron au tics a n d S p ace Ad mini s t r atio n t4 . so o _ ,o , i _ _: v Cod e Washington, D C 20546 505-31-01 i 5 Supl _ ement a ry Notes : Poin t of contac t : Arthur F. Okuno, Ames Research Cen t er, MS 229-1, Moffe tt F ield, C A 9 4 035 (415) 694-6211 or F TS 464- 6 211 16 Abstract An e xpe rimen ta l st ud y ha s b ee n c on ducte d o f t h e supe r c ritica l fl o ws at hi gh s ubsonic speeds over a N A CA 001 2 air foi ! in o r de r to acquJ re a er odynamic data s uita b le fo r e v aluatin g num er ica l -flo w c od es . The mea s u r ement s co ns i s ted prima r ily of s tatic a nd d yna mi c p r e ss u r e s o n the airfoil an d te s t-cha- a el wall s .

Sha d ow gr ap hs were al s o ta k en of the flow field near the a i rfoil . The te s t s w er e perform e d at free- s treamM a ch num b e rs from a p p r oxi m ately 0 .7 to 0.8, at an gle s of attac k s ufflczent to inc lud e t h e on s et of bu ff e t, a n d at = R ey n o ld s n umbers (b as e d on ai rfo il c hor d) fr o m 1 milli o n t o 14 miUi on. A uniqu e test sec t i o ii wa s e mpl oy ed which wa s design e d specifically to obtain tw o -dimensional airfoil data with a minimum of wall in t erference effects. Boundary-la y er s uc t i o n panel s were used to minimiz e s idewall interfer e nce e ffect s . Flexible upper and ! l owe r w all s all ow e d test -ch a n n el ar e a- ruling to n ulli fy M a ch number ch anges i n duce d by t h e m ass remov a l , to corr e c t f o r lo n gi t udinal b oun d a ry - la ye r gr o w t h, a nd to p rovid e c ontour in g c o mpa t ibl e w it h t h e s,r ea mlin es of ' ; t h e model i _nf r ee ai r .

17. Key W o rd s (Sugg e lt _ l b y Autho r (fl) 18. O : ttrit) u t t o n Statement Ae ro d yn amic s Unclasslfl e d - Unllmi_ed ; Airfo i l s Tran so n ic a e r od yna mi cs B uff e t F l ow fi e l d sha d ow _ ap h s S ubj e ctcategory - 02 ' 19 . Se c urity CleMJf. (of this repo qt l " _ ;0 . S _ ity _ l t f. (of this pqp) 2 1. No, of PeSos 2 2 . Price' Uncl ass ifi ed U nc l a _ fle d 7 6 A0 5 FOr sal e by the N M ion a d Technical Info _ 'm41 t ton Sen _ ¢ ,_ , Sl _ n l lfleld , V i r _ nil 221( 1 1 NASA- L a ngley , 1985