REPORT No. 460

THE CHARACTERISTICS OF

78 RELATED AIRFOIL SECTIONS FROM TESTS

IN THE VARIABLE-DENSITY WIND TUNNEL

By EASTMAN N. JACOBS, KENNETH E. WARDand ROBERT M. PINKERTON

Langley Memorial Aeronautical Laboratory

REPRINT OF REPORT No. 460, ORIGINALLY PUBLISHED NOVEMBER 1933

27077 0-36-1 1

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

NAVY BUILDING, WASHINGTON, D.C.

(An independent Government establishment, created by act of Congress approved March 3,1915, for the supervision and direction of theselentificstudy of the problems of flight. Its membership was increased to 15 by act approved March 2, 1929 (Public, No. 908, 70th Congress). It eonsistaof members who are appointed by the President, all of whom serve se, such without compensation.)

JOSEPH S. AMEs, Ph.D., Chairman,President, Johns Hopkins University, Baltimore, Md.

DAVID W. TAYLOR, D. Eng., Vice Chairman,Washington, D.C.

CHARLES G. ABBOT, Sc.D.,Secretary, Smithsonian Institution, Washington, D.C.

LYMAN J. BRIGGS, Ph.D.,Director, Bureau of Standards, Washington, D.C.

ARTHUR B. COOK, Captain, United States Navy,Assistant Chief, Bureau of Aeronautics, Navy Department, Washington, D.C.

WILLIAM F. DURAND, Ph.D.,Professor Emeritus of Mechanical Engineering, Stanford University, California.

BENJAMIN D. FOULOIS, Major General, United States Army,Chief of Air Corps, War Department, Washington, D.C.

HARRY F. GUGGENHEIM, M.A.,Port Washington, Long Island, New York.

ERNEST J. KING, Rear Admiral, United States Navy,Chief, Bureau of Aeronautics, Navy Department, Washington, D.C.

CHARLES A. LINDBERGH, LL.D.,New York City.

WILLIAM P. MACCRACKEN, Jr., Ph.B.,Washington, D.C.

CHARLES F. MARVIN, Sc.D.,Chief, United States Weather Bureau, Washington, D.C.

HENRY C. PRATT, Brigadier General, United States Army.Chief, Mat€riel Division, Air Corps, Wright Field, Dayton, Ohio.

EDWARD P. WARNER, M.S.,Editor "Aviation," New York City.

ORVILLE WRIGHT, Sc.D.,Dayton, Ohio.

GEORGE W. LEWIs, Director of Aeronautical Research.JOHN F. VICTORY, Secretary.

HENRY J. E. REID, Engineer in Charge, Langley Memorial Aeronautical Laboratory, Langley Field, Va.JOHN J. IDE, Technical Assistant in Europe, Paris, Franed.

EXECUTIVE COMMITTEE

JOSEPH S. AMEs, Chairman.DAVID W. TAYLOR, Vice Chairman.

CHARLES G. ABBOT. WILLIAM P. MACCRACKEN, Jr.LYMAN J. BRIGGS. CHARLES F. MARVIN.ARTHUR B. COOK. HENRY C. PRATT.BENJAMIN D. Fo ULOIS. EDWARD P. WARNER.ERNEST J. KING. ORVILLE WRIGHT.CHARLES A. LINDBERGH.

JOHN F. VICTORY, Secretary.

E

REPORT No. 460

THE CHARACTERISTICS OF 78 RELATED AIRFOIL SECTIONS FROM TESTS IN THEVARIABLE-DENSITY RIND TUNNEL

By EASTMAN N. JACOBS, KENNETH E. WARD, and ROBERT M. PINKERTON

REPRINT OF REPORT No. 460, ORIGINALLY PUBLISHED NOVEMBER 1939

SUMMARY

An investigation of a large group of related airfoilswas made in the N.A.C.A. variable-density wind tunnelat a large value of the Reynolds Number. The tests weremade to provide data that may be directly employed for arational choice of the most suitable airfoil section for agiven application. The variation of the aerodynamiccharacteristics with variations in thickness and mean-lineform were therefore systematically studied.

The related airfoil profiles for this investigation weredeveloped by combining certain profile thickness forms,obtained by varying the maximum thickness of a basicdistribution, with certain mean lines, obtained by varyingthe length and the position of the maximum mean-lineordinate. A number of values of these shape variableswere used to derive a family of airfoils. For the purposesof this investigation the construction and tests were limitedto 68 airfoils of this family. In addition to these, severalsupplementary airfoils have been, included in order tostudy the effects of certain other changes in the form of themean line and in the thickness distribution.

The results are presented in the standard ,graphic formrepresenting the airfoil characteristics for infinite aspectratio and for aspect ratio 6. A table is also given bymeans of which the important characteristics of all theairfoils may be conveniently compared. The variation ofthe aerodynamic characteristics with changes in shape isshown by additional curves and tables. A comparisonis made, where possible, with thin-airfoil theory, asummary of which is presented in an appendix.

INTRODUCTION

The forms of the airfoil sections that are in commonuse today are, directly or indirectly, the result ofinvestigations made at Gottingen of a large number ofairfoils. Previously, airfoils such as the R.A.F. 15and the U.S.A. 27, developed from airfoil profilesinvestigated in England, were widely used. All theseinvestigations, however, were made at low values ofthe Reynolds Number; therefore, the airfoils developedmay not be the optimum ones for full-scale application.More recently a number of airfoils have been tested inthe variable-density wind tunnel at values of theReynolds Number approaching those of flight (refer-

ence 1) but, with the exception of the M-series and aseries of propeller sections, the airfoils have not beensystematically derived in such a way that the resultscould be satisfactorily correlated.

The design of an efficient airplane entails the carefulbalancing of many conflicting requirements. Thisstatement is particularly true of the choice of the wing.Without a knowledge of the variations of the aerody-namic characteristics of the airfoil sections with thevariations of shape that affect the weight of the struc-ture, the designer cannot reach a satisfactory balancebetween the many conflicting requirements.

The purpose of the investigation reported herein wasto obtain the characteristics at a large value of theReynolds Number of a wide variety of related airfoils.The benefits of such a systematic investigation areevident. The results will greatly facilitate the choiceof the most satisfactory airfoil for a given applicationand should eliminate much routine airfoil testing.Finally, because the results may be correlated toindicate the trends of the aerodynamic characteristicswith changes of shape, they may point the way to thedesign of new shapes having better characteristics.

Airfoil profiles may be considered as made up of cer-tain profile-thickness forms disposed about certainmean lines. The major shape variables then becometwo, the thickness form and the mean-line form. Thethickness form is of particular importance from astructural standpoint. On the other hand, the form ofthe mean line determines almost independently someof the most important aerodynamic properties of theairfoil section, e.g., the angle of zero lift and thepitching-moment characteristics.

The related airfoil profiles for this investigation werederived by changing systematically these shape vari-ables. The symmetrical profiles were defined in termsof a basic thickness variation, symmetrical airfoils ofvarying thickness being obtained by the applicationof factors to the basic ordinates. The cambered pro-files were then developed by combining these thicknessforms with various mean lines. The mean lines wereobtained by varying the camber and by varying theshape of the mean line to alter the position of themaximum mean-line ordinate. The maximum ordinate

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

of the mean line 2s referred to throughout this report as thecamber of the airfoil and the position of the maximumordinate of the mean line as the position of the camber.An airfoil, produced as described above, is designated bya number of four digits: the first indicates the camber inpercent of the chord; the second, the position of the camberin tenths of the chord from the leading edge; and the lasttwo, the maximum thickness in percent of the chord.

Thus the N.A.C.A. 2315 airfoil has a maximum camberof 2 percent of the chord at a position 0.3 of the chordfrom the leading edge, and a maximum thickness of 15percent of the chord; the N.A.C.A. 0012 airfoil is asymmetrical airfoil having a maximum thickness of 12percent of the chord.

In addition to the systematic series of airfoils,several supplementary airfoils have been included inorder to study the effects of a few changes in the formof the mean line and in the thickness distribution.

Preliminary results which have been published in-

clude those for 12 symmetrical N.A.C.A. airfoils, the00 series (reference 2) and other sections having differ-ent nose shapes (reference 3); and those for 42 cam-

bered airfoils, the 43 and 63 series (reference 4), the 45and 65 series (reference 5), the 44 and 64 series (refer-

ence 6), and the 24 series (reference 7).

If the chord is taken along the x axis from 0 to 1,the ordinates y are given by an equation of the form

f y = ad ^x + ax + a2x2 + a3x' + a4x4The equation was adjusted to give the desired shapeby imposing the following conditions to determine theconstants:

(1) Maximum ordinate 0.1 at 0.3 chord

x=0.3 y=0.1dy/dx = 0

(2) Ordinate at trailing edge

x=1 y=0.002

(3) Trailing-edge angle

x=1

dy/dx= —0.234(4) Nose shape

X=0.1 y = 0.078

The following equation satisfying approximately theabove-mentioned conditions represents a profile havinga thickness of approximately 20 percent of the chord.

t y = 0.29690.1/ — 0.12600x — 0.35160x2 + 028430x3— 0.10150x4

. / - ^^olo^° a - N. A. C. A. familyt_e

r

O ^e

+ Clark Yo Gdtt. 398

/0 ./; .2 .4 .5 .6 .7 .8 .9 /.O

±v = 0.29690 Arx_- 0.12600 x -0.35160x' +0.28430 x' -0.10150x'Basic ordinates of N.A.C.A. family airfoils (percent of chord)

5.0Ord____.I O 1 31 -157 4.3581 5.9261 7.0001 10.8051

1&9091 9.6031 9.002110.0031 49.0721 8.823107 .sod 1 7d u, 1 84.8721 92.4131 01.344 1 1 0. 210

L.E. radius, 4.40.FIGURE I. Thickness variation

The tests were made in the variable-density windtunnel of the National Advisory Committee for Aero-nautics during the period from April 1931 to February1932.

DESCRIPTION OF AIRFOILS

Well-known airfoils of a certain class including theGottingen 398 and the Clark Y, which have proved tobe efficient, are nearly alike when -their camber isremoved (mean line straightened) and they are reducedto the same maximum thickness. A thickness variationsimilar to that of these airfoils was therefore chosen forthe development of the N.A.C.A. airfoils. An equationdefining the shape was used as a method of producingfair profiles.

This equation was taken to define the basic section.The basic profile and a table of ordinates are given in

figure 1. Points obtained by removing the camberfrom the Gottingen 398 and the Clark Y sections, andapplying a factor to the ordinates of the resultingthickness curves to bring them to the same maximumthickness, are plotted on the above figure for com-parison. Sections having any desired maximum thick-ness were obtained by multiplying the basic ordinates

by the proper factor; that is

±y,=6- t (0.29690.1/x-0.12600x-0.35160x2

+0,28430e-0.10150x')

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL

where t is the maximum thickness. The leading-edgeradius is found to be

a

r` 2 0 20 ae) =' .Iota

When the mean lines of certain airfoils in commonuse were reduced to the same maximum ordinate andcompared it was found that their shapes were quitedifferent. It was observed, however, that the rangeof shapes could be well covered by assuming somesimple shape and varying the maximum ordinate andits position along the chord. The mean line was,therefore, arbitrarily defined by two parabolic equa-tions of the form

yo= be+ b ix+ b2 X2

where the leading end of the mean line is at the originand the trailing end is on the x axis at x=1. Thevalues of the constants for both equations were then

expressed in terms of the above variables; namely,(1) Mean-line extremities

X=0 y^=0

X=1 y'=0

(2) Maximum ordinate of mean line

x=p (position of maximum ordinate)

and

yr=(1 p)2 [(1-2P)+2Px-el

(aft of maximum ordinate)

The method of combining the thickness forms withthe mean-line forms is best described by means of thediagram in figure 2. The line joining the extremitiesof the mean line is chosen as the chord. Referring tothe diagram, the ordinate yt of the thickness form ismeasured along the perpendicular to the mean line

from a point on the mean line at the station along thechord corresponding to the value of x for which yt

was'computed. The resulting upper and lower surfacepoints are then designated: -

Stations x„ and x,Ordinates y„ and yt

where the subscripts u and l refer to upper and lowersurfaces, respectively. In addition to these symbols,the symbol 0 is employed to designate the angle be-tween the tangent to the mean line and the x axis.This angle is given by

6 = tan-1 dx

y Oa lxa. ya B=Ion-' dx./0- 9 yt

v Mean /insP1

Chordp ^ x

Or /xt, yt/ x„ = x - y, sine Yu ' Y + yt cos B-./OL Rodius fhrough end of chord xt = x + y, sin a yt = yt - yt cos e

/.00

Sample calculations for derivation of N.A.C.A. 6821

z v, ue tan a sin v aos a y, sin e y. cos a z, v. x, m

0 0 0 10.40000 0.37140 0.92840 0 0 ........................ 0 00.01250.3000

0.03314.10503

0.00489.06000

.383330

.357930

.933751

0.011860

0.03094.10503

0.00084.30000.

0.03683.16503

0.01438.30000

-0.02805-.04503

.am1

.07988

.0221.04898

0-.07347-.17143

-.07327-.16897

.99731

.98662-.00585-.0037

.07906

.00218.80585

1.00037.12863.0218

.59415

.99963-.0307-.0218

Slope of radius through and of chord.

FIGURE 2.-Method of calculating ordinates of N.A .C.A. cambered airfoils.

yo=m(maximum ordinate)dye/dx = 0

The resulting equations defining the mean line thenbecame

Myr = p2 I2Px - el

(forward of maximum ordinate)

The following formulas for calculating the ordinates

may now be derived from the diagram:

xa =x-y, sin 6ya =y,+y, cos 0x l =x+yt sin 0y t =yr -y, cos 0

Sample calculations are given in figure 2. The centerfor the leading-edge radius is placed on the tangent tothe mean line at the leading edge.

06

-GX09

001Z-

O55

0-018C -^L

0025

2206 2306 2406

2209 2309 2409

'— 2212_ 2312 ^2412

2215 X315

2218 2318 2418C_^^ ^_' _.^1 '^-2421

^-----2,506 2606 2706

2509 2609 2709

2612 -^2712

2615 -^

8' ^ 2618 2918

-^

^4206 4306 4406 4506 4606 4706

4209 4309 4409 4509 4609 4709

9212 4312 4412 4512 4612 4712

4215 4315 4415 4515 4615 4715

4218 4318 4418 4518 4618 4718

4221 4321 4421 4521 4621 9721

6206— 6306 6406 6506 6606 6706

6209 6309 6409 6509 6609 6709

6212 6312 6412 6512 6612 6712

6218 6318 6418 6518 6618 ^-6718

6221 6321 6421 6521 6621 6721

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

A family of related airfoils was derived in the mannerdescribed. Seven values of the maximum thickness,0.06, 0.09, 0.12, 0.15, 0.18, 0.21, and 0.25; four valuesof the camber, 0.00, 0.02, 0.04, and 0.06; and six valuesof the position of the camber, 0.2, 0.3, 0.4, 0.5, 0.6, and0.7 were used to derive the related sections of this

family. The profiles of the airfoils derived are shown

collectively in figure 3.For the purposes of this investigation the construc-

tion and tests were limited to 68 of the airfoils. Tablesof ordinates at the standard stations are given in the

figures presenting the aerodynamic characteristics.These ordinates were obtained graphically from thecomputed ordinates for all but the symmetrical sec-

models, which are made of duralumin, have a chordof 5 inches and a span of 30 inches. They were con-structed from the computed ordinates by the methoddescribed in reference 8.

Routine measurements of lift, drag, and pitchingmoment about a point on the chord one quarter of thechord behind its forward end were made at a ReynoldsNumber of approximately 3,000,000 (tank pressure,approximately 20 atmospheres). Groups of airfoilswere first tested to study the variations with thickness,each group containing airfoils of different thicknesses

but having the same mean line. Finally, all airfoilshaving a thickness of 12 percent of the chord were

F—E 3.—N.A.C.A. sWoll pmffiw.

tions. Two sets of trailing-edge ordinates are given.Those inclosed by parentheses, which are given tofacilitate construction, represent ordinates to which

the surfaces are faired. In the construction of the

models the trailing edges were rounded off.Three groups of supplementary airfoils were also

constructed and tested. The derivation of these air-

foils will be considered later with the discussion.

APPARATUS AND, METHODS

A description of the variable-density wind tunneland the method of testing is given in reference 8. The

tested to study the variations with changes in the

mean line.RESULTS

The results are presented in the standard graphic

form (figs. 4 to 80) as coefficients corrected after the

method of reference 8 to give airfoil characteristics forinfinite aspect ratio and aspect ratio 6. Where morethan one test has been used for the analysis, the infiniteaspect ratio characteristics from the earlier test havebeen indicated by additional points on the figure. TableI gives the important characteristics of all the.,airfoils.

Lw0r.

.947 U i 00/2

- /.307/.777

y W -/0y p-241-2.673-2.669

O 20 40 60 80 100Per cent ofch-d •l0

.44 .09

20 .40 G.OB,y

1.8 .36 u .07.

L6 .32 V

8.06

L4 .26% 0.05.v

/.2V .24 ^ v .04K

40 20 °.03u

.8 8 .16 0 .02o O

60./2 .0/

.4^ .0B 0

.2 .04

0 0 ^-.z

2..00/

-2.902a 7-2.282,832

- /.3/2- .724.4031-0.40

L D c. p.

C

Airfoil: N.A.C.A. 0006 R.N.:.^21Q000Sze: 5"x30" Ve%(0../sec.): 66.5Pres.(sthd.. otm.):20.8 Dofe: l-4-32

_' 2 . 3

Where felted.L.MA.L. Test.• U.D.T. 744Corrected for tunnel-woll effect. -.4 -.4

..40 4 8 1216 20 24 28 32Angle of .,tack, a (degrees)F-- 4.-N.A.C.A. 0000.W.H.

u

01

28 0

24 0k

N 20^

0 16 yl lo /2^

g0

0 4uvoQ.0

-4 W

-9 0Airfoil: N.A.C.A. 0006 R.N-: iDate.-I-4-32 Test: V LCorrected to infinite aspect ro

2 .4 .6 8 10 1.2 1.4Lift coefficient, C

y36 v

l32

28 ^.O

24 020 w

16,

12ĈIE8 ^^

4,^u

0 0-4 0

m

-8 a

-/2

-/6

sta.O12525

5.07.51015202540503.607060901.

304.50/

Op'r.O1.420,96/666

3./50.5/24.009

4.3034.456352-'

3.4232.746/.967

C.'r.0

-1.-1.96/961-2666-3.150-3.512-4.009-4.303

cuU

v a /0U -C O

U4 0 -/0

O 20 40 60 80Per cent ofchord

-4.456-4.5014.352-3.97/-34232.746

066-1.066-/.967

/00L.E.100!095)

0Rod.:

(A 5J00.69

Cc. p.

LD

11 vi I

C

Airfoil: N.A.CA. 0009 R.N.:3,2/0,000Size: 5 -x30" Ve/.(Alsec.):68.5Pres.(stnd.otm.):20.8 bbafe: /-6-32Where tesled:L.M.A.L. Test:VOT 746Corrected for tunnel-wall effect.

D

SU

41

28

1? 1

2421

q 2004/

o /6D 6it ^a /2^Bi

8 0 /0,

° 4u.o04

c-4 F-8 u

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL T

.44 .09

20 .40 ^'.. 08N

1.8 .36 .g,.07

1.6 .32 0.06

e U

1.4 .28- 0.05

1.2G .24 v.04

^

/.0 8.208 Q.03u

.88.160 .020

. 680

.12 .0/w

•4`1 .08,0

.2 .04

0 0 y -.2

°u-.2 ^ -.3

-.4 0 -.4-6 -4 0 4 6 12 16 20 24 28 32 -4

Angle of oftack, a (degrees)Fla". 6.-N.A.C.A. 0000 MIMI.

h36 wl32 ag

ea

24 l20 w

/6 pv/2

8'^k

4^

Op

-4 0

"a ceAirfoil.• N.A. C. A. 0009 R. N.: 32/0,000Dote. /-6-32 Test: V.D.T. 746Corrected to inf)iVM aspect ratio

0 .2 .4 .6 .8 10 /.2 14Lift coefficient. Cl

8 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAIITICS

t

20

v o /o ./2

u O

00 ./0-.44 .09

2.0 .40 -08N

/.8 .36 x.07

1.6 .32 0.06C1 U

/.4 .281 0.05,m V

v.04v ^=

1.01.208 .03A .16 02o O

..6'.12 .0/

.4'.08 0i

.2 .04

0 0u .2u

-.2 +^ -.3

-.4 -.4-8. -4 0 4 8 /2 16 20 24 26 32 ` -4

Angle of oftoch, o: (degrees)

FI°URE 0.-N.A.C.A. 0012 Oit 0.

U0U

`o

280 0

24 0 20w

g20 40

0 /6 60l ^a /2 80

8,0100

0 4v.g ul

C-4 0.

-8 u

Ot'w

av

26 0 024 0 20-0 40

p /66012 80

9 -/00

° 4 uo u

0 Qc

-4 4

-8 u

Sla Up'r.0 0

2.5 26/55.03. 5557.5 4.200/0 4.683/55.34520 573825 5.941306.00240 5.60350 5.294604.563-4.70 366480 2623901.445-95 .807%00 (. ^)

/.25 /.8.94-1.8940

-2615-3555-4.200-4.683-5345-5.738-5.941-6.002-5603-5294

563

oO 20 40 60 60

Per centofchord

-3.664-2623

1.446- .607(-. p 6)

L. E. Rod.: 1.58 C

e.p.

L/

Airfoil: N.A. C.A. 0012 R.N:3,230,000Size: SWO" V.I.(k/sec.f: 68.4Pres. (sfnd. otm.):207 Date. , 12-30-31Where tested.• L.M.A.L. Test., V.D.T. 743Corrected for funnel-wol/ effect.

./2

0010

.44 .09

$20 .40 r 08

Cv/.B .36 `.07V

1.6 .32 0.060 u

1.4 .26- 0.05.v

42V .24•ŵy.04

,.0 208 .113

.8 w .16 0 .02a

.6 ou .12 .0/v

.4v .08 .0t

.2 .04 j-./vO 0 y -.2u-.2 3

-,4 0-.4-6 -4 0 4 6 12 16 20 24 28 32 4Angle of ot/oc/r, of (degrees)

Flo- 7.-N.A.C.A. 0015 etrlall.

Slo Up'r.

0 0[252.3672.53.2685.0 4.4437.5 5.250/05853/5 6.68/207./7225 7.4230

7. 50

40 7.25450 6.61860 5.70470 4.S80BO 3.27990 /.8/09 /.006

l00 (./SB)/ O

L'w'r

0-2367-3268-4.443-5.250-5653-6.681-7./72- 7.427-7.502-7.254-6.618-5.704-4.580-3279-/.8/0-/.008

(-. 15610

a 20

N p /0U l 0

11

0

0 20 40 60 80Per cent ofchord

L. E. ROd.: 248 C

c. .

/L

F

Airfoih .A. 0015 R.N.:3,200,000 Ve/.(ft./sec.): 68.4fm):2/.O Dote:/2-9-31.• LMAL. Test: VD.T. 728

or tunnel-wall effect

.4 .6 8 1.0 /.2 1.4

Lift coefficient. C.

Lift coefficient C

20

/2>a Up'r. L'w'

c U /O

z

00av

26 0

0

24 L. 20a

y20x40

o /6A 60l01280

8 01000 4m.o l

0 Q-,1'Cry

u-8

44 .09

2.0 .40 GC

08

/.8 .36 x.07

46 .32 0.06

1 U1.4 .28c 0.05

/.21.24 x.04M

/.Oy.20^4.03U a

.8.160 .02

.6 u .12^ .0/q-

.4 -4 .08 0

.2 .04

0 03

-.2

-.4 0-.4k-8 -4 0 4 8 12 16 20 24 28 32 -4

AnO/e of oitock, a (degrees)Fionaa 8.-N.A.C.A. 0018 airfofl.

10 264/Z53.9,11",SO 5.332

6.300to/0 7,02420 6.0/8-20 662569/30 9.003

-2.8412 -.?.922

-5.332-6.300-7.024_6.0/66.606

^c Ov ^ _/0C o

0 40 60 BO /0Per cent ofchord

-6.9/2-9.00340 6.507.84/

04160 6845-6.84570 543660 393590Z/ 7295 1.210

(./089)AX

L.E,Had:

-6.705-7.94/-5.496-3935-2.172-/.2/(-.0 9)3.56 C

c. p.

L/D

C,

Airfoil:N.A.CA.00/8 R.N.:,1150.000Size: S"x30" Ue(.(H./sec.): 68.8Pres.(stnd. atm.): 20.9 Date: 1-6-32Where tesfed:L.M.A.L. Test.• VD.T, 747Corrected for funnel-wolf effect.

Airfoil: N.A.C,A. 00/8Dote: / - 6 -32Corrected to infinite a4

2 .4 .6 .8 /.0

Lift coefficient.0

48

44.

401360)

l32

28 ti,O

24 pl

20 u/6 p

/2 ig

8 l

k4^

Op

-4 0v

-8"'

.44

R. .40

/.8 .36

/.6 .321

14 .28c.v

1.21.24 1vtE/.0y.20°u

us .l6 0o O

.60t: ./2

.4-'.08

.2 ,04

0 0

-2

-.4

-8 -4 0 4 6 /2 16. 20 24 26 32Angle of attack, of (degrees)

FM 9.-N.A.C.A. 0021 al/3olL27077 0-35--2

Lift coefficient,

St. up'r.

l0 33/425 4.57506.22/7.5 7.350l0 6./95/59.354-9.35420 to 125 39730 540/0/550 9.2660 7.96670 6.4/28041090 253395 /.4/2-/.4/21011(.221,1-.2211/ 0

L'wr.

-3.3/4-4.576-6.22/-7.350-6./°5-/0.04/-/0397-/0.503-/0/55-9.265-7.986

C C /Ou s° 0

k _/0y o0 20. 40 b'0 80 t0

Per centofcho rd

-

-6.9/2 -4590-2.533

OL. n Had.: 4.65

Cc.p.

L/D

a

Airfoil: N.A.C.A. 0021 R.N, 3,190.000Size: 5-"x30" t/ei.(H./sec.): 68.6Pres.(stnd.atm.):20.8 Date:1-7-32Where tested'L.M.A.L. Test: VD.T. 748Corrected for tunnel-wall effect.

lOu0OacN

2B 0 0

24 a 20k

V20 0 40

/6t 60l

/2480

60(000 4 u.o

lC Q

C

-8 u

9CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND TUNNEL

5/a.0

255.07.5/O

20253040506070609095

00

252.44

/57.25

Up'r.

-

3.354.625.55-26.27

7747937.977.667.026.074.90352/.931.05(./3)

LWr.

O-/.46-/.96-235

9-3/-3.44-3.74-3.94-4.03-392-3.56'-3.05-2.43-1.74- .97- .ss(-613)

D 20y o !0V t 0lR

p -/0

O 20 40 60 60 11.Per centofchord

DL.E. Rad: 1.565tope of-d-0

L/ c.p

C

2212 R.N:3,220,000Size: 5"k30" V IMIsec.):68.4P e5.(5ti7dolm.):208 Dote:12-2-31Where tested:L.MA.L. Test.-VDT 719Corrected for tunnel-watt effectj

Aif.il.-N.A.C.A.

agOaW

28 0

0

324 ,b 20020040

lp /6^ 60l l

0 12 80

8'-/00k c0 4 vo u.

l

R 0 Q_4 c0.

u-8

io REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

Up'r.

2S 5^75.0 7.4067S 6.750/0 9.756-9.756/5//./36-/1./3620//.953-/1.95325/2.37830 250440 2.0950/1.029-/1.02960 9.507-9.50770 7.633-7.63380 5.46590 30/61.680-100 (.262)0 0

L'wi:

-5497- 7.406-6.750

z D /0

dV1R

C o-/0O 20 40 60 BO /L

Per centofchord-/2.378-/2 504-209

-5465-30/6/.68f-.262

0LC. Rod.: 6.86

c.p. 11 IC. 11r-'

C

Airfoil: MA.CA. 0025 R.N.:3,230,000Size: 5"x30 •• Ve/(fl/sec.): 68.3Pres. (sfnd ofm.J. • 20.9 Date: 1-8-32Where tested L.MA.L. Test: VD.T. 749Corrected for tunnel-wall effect

lOtU

OUcv

28 0

1

324 0 21kq2004(

16 61

0 /281

B o /Ofti0 4 m.o u

l

R 0 4.0

4 0.

V

-8

.442.0 .40

1.8 .361.6 .32

G°/.4 .281

rL 2,j. 24

v1.0 ,y .20

A.16v./6^0 0

.6 u./2

.4 08

.2 .04

0 0

-.2-.4

8 -4 0 4 8 12 16 20 24 28 32An of attack, a (degrees)

1'..30.-N.A.O.A. 0026 airfoil.Lift coefficient,

44

2.0 .40d

/.8 .361.6 .32 0U1.4 .28 0

w ^

2j .24 v

101 20v^ o

B` .16 0O O

6u./2

4".08

.2 .04

0 0 w0-.2

`c

a

_40

-8 -4 0 4 6 /2 16 20 24 28 32Angle of ottack, a (degrees)

2 48

ll 44

./0 40

.09 36

.08 32

.07 28

.06 24

x .05 20

.04 16

.03 /2

.02 8'

4

0 p

_.2 -8

.3Airfoil.-NA.CA. 2212 R.N:3,220,000

12

-. 4 -- Dofe:/2-2-3/ Test: VD.T. 7/9 Corrected to infinite ospecfrot/o -lB

.4 -2 0 .2 .4 .6 .8 /.0 /.2 /.4 t.6 18Lift coeff/cient,C

FIGME 11.-N.A.C.A. 2212 airfoll.

2 48

/ 44

/0 40

.09 360l

.06 32 D

.07--28 bO

.O6 24 0

.OS 00,N

.04 /6 003 z

w.02-a 118.0/<

0

0 0^U

O-4 0

v

.3 Airfoi/. N.A.CA. 2306 R.N.:3080,'00 -/2_ q9ote:9-24-31 Test:. V. D. T. 680 _/6

Corrected to infinite aspect ^-otio-4 .2 0 .2 .4 .6 .8 10 /.2 1,4 /.6 18

Lift coefficient.0

1

.44V2.0 .40v

/.8 .36 .9

/.6 .32 0C3

1.4 .28 PN O

/, 2 ti .24m '^

/O.w.20$

eo./sa.6^./2v.4 .^ .08

Y

.2 .04 V`

7

5.0 336 -2.0/7.5 4. 9 -224

20 6.06 -2.5225 6.37 -25130 6.50 -25040 632 -2.3950 5.62 -2.1360 5.07 -1.7670 4./1 -1.3680 2.96 - ,9790 /.64 - .5495 .66 - .33

100 (./01 /-./O)loo - 0

St. up'r, L'^r.m^ l0

I25 1.69 -1.16 U t 02.5 2.39 -/.56C

y _/0

to a. 7 -2.36 0 20 40 60. 80 /015 5.54 -250 Per centofchord

5""' oJrod'usThrough end ofchord: 2175

L.E.ROd.:0.69 C

c. .1

L/D

1

Airfoil: N,A.OA. 2309 R.N.:2,970,000Size: 5'x30" l/e%(R/sec.J: 71,0Ires.(st7d atm.J:203 Dote:9-24-3/Where tested.• L.M.A.L. Test. l!O.T.68/Corrected for tunne%wa//effect

-8 -4 0 4 8 /216 20 24 28 32Angle of attack, a (degrees)

Pim. 13,-N.A.C.A. 2909 airfoil.

.44

R. .40

/.8 .36

1.6 .32

V

/.4 .261.v

1.0 y.20u

8w./6o0 0

.6,"./2

.4 ^ .08

.2 .040 0

-.2

-.4

OU0OacW

280 0

24 0 20w

'20 Q 40

$1660

F12880Bolo

o qmo U

0^.0-q 0.

-8

0

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND TUNNEL 11

0U0c

28 0 03

24 a 20

A20`40

g /6 u 60u /2 u 60

8'-/0

° 4 vv0 1

.c-4 0.-8 u

0

7.5 30/ -/.22

20 4.65 -1.0925 4,91 -1.0430 S.00 -1.00404.86-.9450 4.49 - .8/s0 3.92 - .6570 3.19 - .4860 230 - .3390 /.26-.1995 66 - .13

l00 (.06) (-.06)/00 - 0

5^ up'r. L'^ r. D /0Z25 1.16 - .73 ° g 025 /.70 -.95 ly5.0 2.43 -/./5 ^ 0-/0/0 3.46 -1.22 0 20 40 60 80 /0/5 4.18 -/./6 Per centofchord

C.E. Rod.:0.40Slope afrod'uslhraugh end ofchord: 2115

C. .

LD C

Ca

Airfoil: N.A.C.A. 2306 R.N.:3,080,000Size; 5"X30" Vel(ft./ser,4:69.8Pres.(sfnd.otmJ206 Dofe:3-24-31Where 1-1.1. L,M.A,I, Test: l

12

0U0

28 0

024 0 20k

Q 20 Q 40

p 16, 60

l2 g 80

6,0/00

4u0 Q

C-4 0.

-B

O

OUv

0' 20o4

2k

l

p DD o° 6

8 0 /000 4vo u

0 4-4

V-8

2B 0

0

/6 6O

/2 0

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

20

wo /o ./2m k _/^ o• x Test A

St..

0/.252.5507.510/520253040506070809095

/00

up,,.-

2.243.//4.3/5./B5.866.89].547.88B.00].777.146.215.023.622001.09

/ i3

L'w'r.

0-1.57-2/6-285-326-352-3.82-3.94-3.99-3.64-3.45-z.92

y

0 20 40 60 80 /LPer cent ofchord

-231-/.63- .9/5Z

/ 03 CL L. Rod.: 1.58

/harddh2%/dr ofSlope ofrod'us

LID

a

Airfoil: N.A.CA.2312 R.N.:,1120,000Size: S"x30" Ve%(N./sec.): 69.2Pres.(sf'nd.otm.):20.9 ofe:12-2-31Where tested.' L.MA.L. Test.• V.D.T. 720Corrected for tunnet-wall effect

' -8 -4 4 8 /2 /6 20 24 28 32 -4Angle of attack, a (degrees)

F-B 19.-N.A.C.A. 2312.W.R.

Sla.o

Up'r.-

Lw^.6-

20

/ov o 2/.252.5

2003B5

-1.,96-2.74

U ,^. 0l U5 0 5.26 -3.667.5/ 0

6.287.06

-4.25-4.66 O 40 60 60 10n

20 8.97 -538

30 9.50 -5.5040 9.22 -5.2950 7.47 -4.7760 7.36 -4.0670 5.95 -3.2260 4.29 -22890 1.36 -/.2695 L30 .72/00 /.161 (-./6)

/5 8.25 -5.13 Per cent ofchord

(

/00 - O all

25 9.36 -5.48

5/ape afrodiu5

24cho(dh^sot

L.E. Rod.: 2.47 C

0 c.

L/D

C

Airfoil: N.A.C.A. 23/5 R.N.:3,06C108CiSize: 5"x30" Ve1.(fl,/sec.): 69.8Pres.(s%'d.oim): 2Q8 Date: 9-25-31Where tested.• L.M.A.L. Test: Vb. T. 683Corrected for tunne/-wo// effect

Airfoil: N.AC, 23/2 R.A.N.:Dote: 12-2 3l Test:Corrected to infinite aspectO .2 .4 .6 .8 1.0 /.2

Lift co efficient,

44 .09

2.0 .40 G .OBC LL EE

/.8 .36u.07i6 t

1.6 .32 p,06V u

1.4 .28-^ p.OS.v. a

42V.24 •^ v.04w

/.0U .20 u ".03c

.8./60 .020 0

.6 u ./2 .0/

.4^ .08 0

.2 .04 Ok -. /k

O 0 w -.20U

Airfoil: N.A.C.A. 2315_ _.4 Dote: 3-25-31.4 'gCorrected to infinite os

-8 -4 0 4 6 /2 /6 20 24 28 32 .4 :2 0 .2 .4 .6 .8 40Angle of allock. a (degrees) Lift coefficient, CF1omz 16.-N.A.O.A, 2315 Wdoll.

7

.44 .09

2.0 .40 .V^-.OB

/.8 .36 ^.07

L6 .32 0.06

VQ U

1.4 .26": ^.05.d

l2V .24 v.04

40 .20 1)^.03° C

.8 w

.16 0 .020 0

.6^ .12 .0/

.4'4 .08 0

.2 .04 GkO 0 u

-.2

-.4 Q -.4

36 vl

32

28 iO

24l

20

/6 p12

uOx°4 0w

e

48

36 vl

32,

28

/6 0v

/2 c

8e

0

u

040

W

•8 ^`e

00

44 .09If

2.0 .40 06

/.8 .36 vx.07

l.6 .32 0.06C1 U

1.4 .26c th

1.2,j.24.04v

/.O,n .2011 12.03u

.8 m .16 0 .02

0 0.6.".12 .0/

.4'.08 0s

.2 .04 C-./O 0 y -.2

0u.2 _3r,.rreC.A.-.4-.4

-8 -4 0 4 8 12 16 20 24 28 32 c4 c2 0 .2 .4 .6 .8 /.0 /.2 /.4Angle of ottock, a (degrees) Lift coefficient.FIGURE 16.-N.A.C.A. 2908 MEN].

N01

U

20 v

/6 p

/2

v4u

0

-4 0v

-8

Sto.0

1.25Z.5.0

101520253050708090

10

404.90604.08

upr:-

/.///.572.28

3243.904.374.694.864.60

2.441.351061

3.33

C w1r.0

-0.60-/.04-1.29- 45-1.44-1.37-1.25- /.12- .90- .70- .49- 20- .1 /(-.061

-B, 10t 0

4a-/0p0 20 40 60 80 /

Per cent ofchord

0.4051ope ofnvdi,5through end ofchord: 2120

I I

LID C

Airfoil: N.A.CA. 2406 R.N.:3, 120,000Size: 5"x30" 3e/.(ft./sec.): 69.3Pres. (sfnd. otm):20.7 Dote: 9-8 - 3/Where tesled.• L.M.A.L. Test. V.D.T. 665Corrected for tunnel-woll effect

°U0

N

2B p 0

24 20

y -0Q40

/6D 60

Q12-co 80

8'.100^. c° 48,

0QC

-4 0.

'B U

9-3/110,000D.T. 666

7

48

44

40

44 .09

2.0 .40 x.08C

/8 .36 x.07

L6 .320.06^q U

1,4 .28 0.05N ^

L2,j.24M \.04v

L0.20 ,03--

.8 W .16 .020 0

.6" .12 .0/

.4".08 0

.2 .04 OE-./

0 0 m -. 2°uv

-.4 0 -.4

166

/2 cw

4sU

0-4 00

.6 PQ

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL

13

Oi

O

c0

28 p 03

24 0 20k0 20 0 40

/6a 60

/2g 80

8'.100'• C° 4 u

04C

-4'4U

-B

5^.1.252.55.07.5'/O15RC25304050605.704BO9095

/00too

Up'r./.622273.203.874.435255.816./86.38USS.22. 273.101.72.94

(./0)-

LW-123-166-2./5-2.44-2.60-2.77-2.79-2.74-2.62-2.35-2.02-/.63-124- .85- ,47- ,2B(-./0)

o

-,'b l0U g OY v -/0

O 20 40 60 60 /GPer cent ofchord

G.E. Rod: 0.89/Ih103gh end ofchord: 2/20

C

c. .

L

a

Airfoil., NA.C.A. 2409 R.N.:3,1 /0,000Size. 5"x30" Ve).(ft./sec): 69.3Pres.(sfnd.otm.):20.8 Dofe.3-9-31Where tesfed:L.MA.L. Test.-VDT. 666Corrected for tunnel-wall effect

-6 -4 0 4 8 /2 /6 20 24 28 32 -4 :2 0 .4 .6 .8 /.0Angle of ottock, a (degrees) Lift coeff/cient,CFIGURE 17, -N.A.C.A. 2109 Wrtoil.

7.5 6.06 -4.47

20 8.70 -5.6625 9.17 -5.7030 9.38 -5.6240 9.2S -5.2550 6.57 -4.6760 7.50 -3.9070 6.10 -30580 4.41 -2./590 2.45 - 41795 1.34 - .66

100 (.16) (-.161too - o

S70o. Up'n GOY: ^^ ^0Z25 2.71 -206 u t 025 3.7/ -286 y k _/05.0 5.07' -3.84 p10 6.83 -490 O 20 40 60 80 /L15 7.97 -542 Per centofchord

5/ope ofradiuslhprdh2%20 f

L.E.Rod.. 2.48 C

c. .

LD

Airfoil: NA.CA. 2415 R.N.:3,060,000Size: 5"x30" Ve/(fL/sec.):698Pres. (stud. otm.):20.8 Dote:9-10-31Where tested'L.M.A.L. Test: VD.T.668Corrected for tunnel-wolleffect.

5Iv

28 024 0 20

kC 20' 40

g /s F 60

o /2 8

80/00 4yo u

R 04c_4 0.

-8 u

0

0

14

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

So.!252.5507.5101520253040506070609095

gi

w,

2.152994.134.965.636.617.267.677.687.60.7246.365.183.752.061.14

31-

-465-227-3.01-346-3.75-4.10-423

V s° 0vk-/Op

0 20 40 60 80 /6Per cent ofchord

-4.22-4./2-3.60-3.34-2.76-2.14-/.50- .82- .46

'0

L.E.Rad.: 450Slope ofradiusYh -d.- end ofchord: 2/20

C

Airfoi/: N.A.C.A 2412 R.N.:.250,000Size: 5"x30" Ve/. (ft./sec.): 66.0Pres.(stnd.otm.): 2/.0 Dote:/2-3-31Where tested.• &A.L. Test: V.O.T. 721Corrected for funnel-wall effect

-8 -4 0 4 8 12 16 20 24 28 32 -4 -2 0 . .2 .4 `6Angle of ottock. a (degrees) Lift cot

F-E 16.-N.A . C.A. 2412 aic[oll.

a

v28 p 0

24 a 20kV201 40

0 /6t 60l lo /2.2 80

8 0 /00k

° 4u.oC 04

.c_4 0.

-6 U

/

.44 .09

2.0 .40 U .08d

48 .36 x.07

/.6 .32 o.06

V U1.4 .28- 0.05

•-/.2V.24^ v.04

v^/.Ov.20 12.03

u.8 u .16 .02o O

.60 .12 .0/

.4 v .08 0

.2 .04 V`-.lk0 0 v -.2U

.2 •3 Airfoil:N.A.C.A-4 0-4 Date: 12-3-31Corrected to

9-10-31cted to4 .6

Lift co

36 ^

32

26 2f0

24 0l?0 w

16 8-/2ck

Lk

4 ^.OL

°

-4 0

e

jeTest: V. 721 16.sct ratio10 /.2 1.4 16 /.8^t. C

46

44.

40

N36 N

l32

28 tl

/6 0

/2

4^u0^°-4om

e

./I

44 .09

2.0 .40 G .08v

48 .36 x.07

1.6 .32, o.06^q V

1.4 .28-, 0.05

QUO)

v

.8 v .16 0 .OR--o a

.6 0 .12 .0/k

.4 ^ .08 0

.2 .04 j-/0 0 v -.2

°u-.2 -.3c-.4 0-4--

-6 -4 0 4 6 12 16 20 24 28 32 -4 -2 0Angle of ottock, a (degrees)

Fmv .18.-N.A . C.A. 2415 airfoil.

.44

2.0 .40

LB .36/.6 .32

Ci/.4 .28

vL 2V.24

vLO ,v .2000

U

.6x.1600 0

.6'- ./2

.4.08

.2 .04

0 0

-.2

-.4-8 -4 0 4 8 12 16 20 24 28 32

Angle of attack, Of (degrees)FIOOEE 21.-N.A.C.A. 2421 airfoil.

Lift coefficient,C

sto.0

/.252.55.07.5/015120253012

405060708090as/00(.

/00

UP r.-

3.87S2/7.008.299.28

//.59/2/5

.36

9.7919 4

74

/.7622)-

3.18 -1.66

L'wr.0

-2.82-4.02-SS/-6.48-7./8-6 05-6,52-8.67-8.62

-7.31-6.17-0.671304

-1,06(-.22)0

U cy o /0U r 0

4 a -/00 20 40 60 80 /0

Per cent ofchord

L.E.Rad, 4.855/ape trod,, athro-1gh end ofchord: 2120

dec.P.

/D

Airfoil.-NA.CA.242/ R.N.:3,000000Size. 5"x30" VeL (ft./sec.): 70.5Pres. (sthd.Ol 7.) 0.6 Oate:9-//-3/Where tested. 4.MA.L. Test: VDT. 670Corrected for tunnel-wa/l effect.

UltU0av

28 ° 03

24 ,0 20q20 0 40

o /sa so

o 12 yu° 80

8,0100

° 4 u

C 0 4c

-4 0.

ti-8

v

Q.

ari00l0h0

v.c

k

0v

%C KA.0 A. 24189-11-31clad to inhi,it.4 .6 .8

Lift coeff/cie/ C

7

.44 .09

2.0 .40 x'•.08W

/.8 .36 x.07

L6 .32 0.06G U

1.4 .28`c 0.05v

/.2V .24k m.04w^v

40v.208 L..03u

.8v.161̂ .02--0 0 -

.6./2 .0/k

.4 08 0

.2 .04 Of-./

0 0 w -.20-.2 -.3

-.4 0 -.4-8 -4 0 4 8 12 /6 20 24 28 32 -4

Angle of .Hock. a (degrees)n-RE 20.-N.A.C.A. 2418 airfoil.

48

44

40

36 ml

32 a

28 tf.o

24 0l

20 u4/6 0

/z c.k

8.

4su0^`o

'4 0v

_8 rn

V

Si..L252.5507.5/0/5

506070BO9095

/00/00

20/0./52510.653010.6840/0.71

up'r.3.284.456.037./78.059.34

9.698.657.02SOB28//.55/./9)-

GWr-2.45-3.44-4.68-5.48-6.03-6.74-7.09-7/8-7./2-6.7/-599-5.04-3.97-280-L53- .67(-./9)O

/0u r 0l U0-/O

0 20 40 60 80 /LPer centofchord

L. E. Rod: 3565"p, ofm ' end a

rad'ust,chord: 2/20

0

a.P.

L/D

n

Airfoil. NA.C.A. 2418 R.N.:3,060,000Size: 5'x30" Ve/(f1/sec): 69.8Pres. (sfnd .1-):20.8 Date: 9-11-3/Where tested.-L.MA.L Test: VDT. 669Corrected for tunnel-wall effect.

DO

4'.

v28 0

0

24 0 20k

20 40N ^0 6D60

a 1280

8'.100

0 4v0 Cc

-4 0.

u-8

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL 15

U0tu00acv

28 03

24kq 20F

0 /6

o /2v 80

4u.oOQ

C-4 0.

u-6

.40

.36

.32

G.28-,

vv .24.0h

Wv.20^.0 b,v./6o0 0U.1208

.040

16

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

.44

1.57-1.270

224-2.56

2.9e Per -a ofrhord

An of allock, a (degrees)FIGURE 22.-N.A.C.A. 2608 airfoil.

r. L'w'r.N p /O •/2^$ D

O 20 40 60 80 /00B -2.76 . /D

O

vdfi o

0

24 0 20Q

Q 200400 /6^- 60

.2 l2 809 o /00

° 4u0 Q

.c-4

4u

-B

5/0.0252.55.07.5/0/520253040506070809095

100/00G. E.S/opethrohchord:

Up'

Z2

3-'03.75W. 2SOS5.60-3.5.965/B6.275975.354.44326.99

(.10)-

Rod.:

ug

02-2.97-2.84-2A4-/.97-/.50

ofredius

2/25

-/.06- .67 .36

- .22(-./O)

o0.69

e ndofG$.

0

Airfoil:N.A.C.A.2509 R.N.:,R060,000Size: S"x30" 3e%(ft./sec.J: 69.8Tres. (sfnd. otm.J: 20.7 Dote:30"

teSMCd L.M.A. L. Test: U.D.9-1

T. 673Corrected for funnel-wa//effect

44 .09

2.0 .40 t'..OBC

/.B .36 3.07/.6 .32 x.06

/.4 .28 .05/.2V.24u v.04

c/.Ov.20, x.03

u ^.8,) ./6 0 .02.6 U .12^ .0/.4v .08 0.2 .04 Vr -. /

3.2 _3-.4 E _ 4'

__H

36

322824: p

got/60/28'^4U0j

°-4 0

°

Y.

C"°/' ve

-/2_16Dote:

Airfoil:NA.CA.Corrected9-/531to

2509infinite Test:aspect

R.N.3.060,000l!O.T.ratio 673

-6 -4 0 4 8 12 16 20 24 26 32 c4 c2 0 .2 .4 .6 .8 /.0 /.2Angle of oHOCk, a (degrees) Lift coeff/cient,C

FIGURE 23.-N.A.C.A. 2600 airfoil.

.44

2.0 .40

L0 .36

46 .32UQ

1.4 .28N

L 2V .24m

LO ,y .20 0

Al° o

.6X.12k

.4'.08

.2 .04

0 0

-.2-.4

-8 -4 0 4 8 12 16 20 24 28 32Angle of attack, a (degrees)

51a.0/.252.55.07.5/01520253040506070809095

/oo/00L.E.S/apelhroC&

Op".-2.633.634.965.9/6.66

7.758.486.929/99./66.627.646.284.572.56L41!./sl

-RW..:of,ugh2/25

0-2.11-2,94-3.96-4.60-5.06-5.63-5.87-5.92-5.84-535-462-3.76-2.88-/.9B-/.07-.62!-.lsl02.41ai-

end of

u

U /0_10C O

0

NI#R20 40 60 80 /LPer cent ofchord

i

c. p.

LD

C

Airfoi/.• N.A.CA.25/5 R.N:3,o60,000Size: 5"x30" Vet. fft/sec.): 69 8Pres.(stndot. ):20.6 Doi-S-18-31Where tested.-L.M.A.L. Test.-VDT 675Corrected for tunnel-wall effect

lOU0OCN

26 0

324 0 2(k

q 2004(lo 6D&

0/28(k 8 010(

C0 4v.o u

l0 y

C-4 0.

ti-B

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND TUNNEL 17

r0aa,

26p 0

24 R20kq20a 40

l61 60

0 /2 86

8 0 /OO^- c° 48

O pC

-4 0.-8 u

3.59ssz4304.43

i o -/0 ^ll.1LIJ_LJJ_J-L11J0 20 40 60 80 /00

Per cent ofchorr(

. / /

. l0

.44 .03

2.0 .40 • .OB

1.8 .36 6.07k

1.6 .32Ci 8 .06

1,4 .26^ 0.05

1.2V.241 m•040

LO x.200 Q.0.3u a

.0.160 .02Q)o O

.6X ./2 .01

.4'.08 0

.2 .040 0

O .2

_ _' 2 v "?

-• 4 0 -•4-.4

24.-N.A.C.A. 2612 airfoil.

o v q 674 44

40y

36 v

U32 $i

28 2(p

24 0l

20

160v

12c

8lo

u00

-4 0vU8 e

_/2

-16

4.44

%so3.29zs3 oa/.9733

:42/31

C

e Afinsof

LID

I

c.a,

0^H.D

Airfoil: N.A.C.A.25 /2 R.N.:3,080,000Size: 5"x30" VeG/flfsec.:69.4Pres.(sfnd.ofm):21.0 Dote: /2-3-3/Where tested: L.htA.L. Te5t. , VD.T. 722Corrected for funnel-woll effect.

Airfoil:Date:Corrected

N.A.CA. 2512 R.N:3080,000/2-3-3/ Test: V. D. T. 722

/o infinite aspect ratio4 8 12 16 20 24 28 32

ng/e of oHock, a (degrees)FrovaE

..2 0 .2 4 .6 8 10 /.2 1.4 /.6 l.8Liff coefficient, C

FiomE 26.-N.A.C.A. 2616 airfoil.

270770-$6--3

Uru0v

28

24 lu

kA 20o

0 /6^

.2 /2 u

Bo

0 4u.o

0 yc-4 0.U

-B

36

32 aaP

28 2f6

24 p

20 m

16 1-11./2

k4uU

00

-4 0m

-6",e

-/2

-16

Angle of attack, a (degrees)

1'..27.-N.A.C.A. 2521 WdOU.

10ote: 9-2/ 3/I Corrected to infinite0 .2 .4 .6 .8 1

Lift coefficient

.44 .097 // SV

s 2.0 .40 -.OB

112`L2 B7 5

3

7 LB .36 x.076J[. Rpd.: 4.es 1.6 .32 x.06JPe Ofrod'3S

f C^j

o^d^'z% s 1.4 .28- 0.05va

/.2V.24 y.04C.P._ k

4.03

.e^U 11

.lso .020 0

.6'./2 .0/

.4v .08 0

CD .2 .04 OE -. /0 0 -.2

Airfoil. N.A.C.A.252/ R.N.:,^ /30,000 3Size: 5"x30" 3el(ft/sec): 68.9Pres(sfnd. ahn.): 2/.0 Date.9-2/-31

tested.• LM.A.L.

_ ' 2 .3Where Test: l!O.T. 677 -.4 -.4Corrected for tunnel-wa/l effect ^

-4 0 4 6 /2 /6 20 24 28 32 :4

36 v

32 O

28.6

24 0l

20",v

168-/2Bi

k4^

0

-4 0v

e

ratio

U

av

2824 0k

420

i

60.0 4wux l

04r

-4 0.v-8

18

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

J/

.44 .09S

.40 .08v.36 x.07

.32 0.06V u

.26`c 0.05•v a

Ci.24v N.04v

v .20 $ 4.03u

m /6 p

. 0.02 aoo O .u ./2 .0/k

1 .08 0

.04

0 m -.2uu

m .3 Airfoil. N.A.C.A. 2518

o _-4 Dote: 9-19 3/Corrected to infinite -__ .4 c2 0 .2 .4 .6 .8 /.0Angle of attack, a (degrees) Litt coefficient,FIGURE 2B.-N.A.C.A. 2618 airfoil.

m o /0 2u ^ 00-/0

0 20 40 60 BO /00Per centafchord ^ ./G

7

.44

2.0 .40

/.8 .36/.6 .32

V/.4 .281

v1.2,j.24 ;O^

vLO x.208

u o.sv.ls^0 0

.6X./2ti.

.4 08

.2 .04

O 0

-.2

-.4-8 -4 O 4 8 12 16 20 24 28 32

Angle of oitock, a (degrees)

Slo.0

[252.55.07.510/520253040506070809095/00

-2.052.663.951725.346.256677.267.517.567.236.565.564.152.341.26Ly

0-1.73-2.37-a/7-a66-403-4.45-4.6/-462-4.52-4.03-3.36-2.56-/.77/

-.56- .33

u U /0Yo' 0

1 U4 p -/0

0 20 40 60 80 /CPer cenfofchord

L.E. Rod.: /.56

c'.9 -,ofchoror 2/30

LID c. p.

0

Airf.A.., N.A.C.A.26t2 R.N.:3190,000Size: 5"x30" Ve4(ltlsec.):68.4Pre s. (sthdotm):2/.0 Where tested: L.M. A.L. Test: VDT. 723Corrected for tunnel-wo/l effect

al0uUkO

v28

324 1- 2(

kq20o 4(

0 /sD s(

o 12u 8(

8 104

4 C0 4

h 04C

-q ti

V-8

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND TUNNEL 19

Dl0lU

O

v

26 o

G3

2402(v

y 10 Q 410 /6 6C

8(

60/a0 4m.o u

0 p.c

-4 0.

ti-8

-tl 4

Fxomz 28.-N.A.C.A. 2612 tWoll.

7

.44

2.0 .40

1.8 .36

1.6 .32

Ci

1.4 .28c.W

1.2, .24

/.o'.20

.8 m .160 0

.6 ./2

.4^ .08

.2 .04

0 0

-2

-.40 4 8 M /6 20 24 28 32Angle of attack, a (degrees)

M.. 29.-N.A.C.A. 2712 sftM.

6t.L25L56. 07.510/5202530405060709095100

804.42

UPY.2042623.904.665.266.136.737./27367.437.136.525.572571.44(113)

L'^Y.-17S-240-323-3.76-4.12-456-4.75-4.77-4.67-4.18-3.47-2.6/

v P /0U i Oh 0-10

0 20 40 60 60 /CPer cent of 'd

-1.67- .83- .33- .19(-. 3) O

L.ERod: /.58.l1h ough end.(chord: 2/35

1

LID c. .

Airfoil: N.A.C.A. 2712 R.M-$060.000Size: S"x30" Vel.(ft./sec.): 69.5P es.(sfnd. 0 Dote:12-4-31Where tested.• L.M.A.L. Test: V.D.T. 724Corrected for tunnel-wall effect

Lift coefficient.(

Slo.O

/.252.55.07.5to152025304050

6070809095

/00L.E.5lopethrou

d:chor

LPL,-

3.044.135756.%Z909.159.749.929.949.56875

Z6.134.392.4//.3/1.131

Rod.:

gh end-4//0

L'wi-.

0-/.07-441-L69-/.66-46/-1.55-1.74-496-2.06-2.05-1.85-/.55

cu

v o /0U t 0l Uh

p -/0

0 20 40 60 80 /6Per cent ofchord

ofrodius

-1.21- .BS- .50- .3/(-63)

756

of

Li

III

L/D c. p.

0

Airfoil: N.A.CA.4212 R.N:3240,000Siie: 5"x30" Vel.(f//sec.): 68./Pres.(sYnd.afm): 20.9 Dote:l2-/0-3/Where tel...^L.M.A.L. Tezt:VD.T. 729Corrected for tunnel-wo// effect

Lift coeff%c%eni, C

-.4-6 -4 0 4 8 12 16 20 24 28 32

Angle of attack, o: (degrees)Hausa 30.-N.A.C.A. 4212 Udall.

.44

2.0 .40

48 .36

1.6 .32Ci

/.4 .,?8<,N

2,j. 24 i?v

/0^.20uU

.8m./600 0

.61" ./2

.4 '.08

.2 .04

0 O

-.2

Dt0Uk

v28 i 0

024

a 20kA 20x40l6 16 60

80UB 0/00

M0 4o u

2 0 4-4.

00.u

-B

44

2.0 .40 VcwL8 .36

1.6 .32 0U° u

1.4 .28, o/. 2V.24^ m

tiv

1.0,t .20 40

O ^.6x .12k.4 .08

.2 .04 C

0 0 v°u

.2cF_•4 0

-8 -4 0 4 8 12 /6 20 24 28 32 S`Angle of attack, a (degrees)

7.5 393 -.35

20 6.44 .6825 6.65 B930 7.00 %00

40 6.62 /.0250 6.33 /.0360 5.56 9970 4.54 .86BO 329 .6590 /. ]9 34s5 .97 /5100 LO61 (-.O6)

/00 O

Sta. Vp'r. L'w'r A 200 - 0 N p

/.25 /,39 -.57 02.5 2.05 -.64 ti -/050 3./O -.54 p ffffH/0 4.63 -.12 0 20 40 60 80 /6/5 S. .32 Per cent of chord

L.E.Rod.:04051-through end ofchord: 4115

0L/D I I I C

c.p.

n

Airfoil. N.A.C.A.4306 R.N-W,90,000Size: 5'X30" VeL (f1./sec.): 70./Pres.(s £nd. of 3 Od1.:4-11-31Where lested.• G.M.A.L. Test: V.O.T. 561Corrected for funnel-wall effect

D0U

DW

'80 024,0 2

q20 0 40

o /6 P

60lo 128

80/000

4 U

OQc

-4 0.-8 U

d

20

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

12 48

44

./0 40

09 36

08 n, 32D

.07 28 t

06 14:;z0l

OS 20 m

.04-/6 p

.03 /2'ck

.02 n8. C

O/ 4 t0

0 00u

------ 4 0w

Q. 3 Airfoil N.A.C.A. 4306 R.N.:3060.000 _/2

-.4 4-11-31 Test: V. D. T. 561'4 Corrected to infhde aspect ratio _/6-.4 -2 0 .2 .4 .6 .6 /.0 /.2 /.4 /.6 1.8

Lift coefficienl,CFluvaa 31.-N.A.C.A. UN aidoll.

D

`oUc

28 024 0

0200t

p /6U^ t

p /2 U

wo qvo

u

a 00.C-4 0.

-8

LlOlUkO

m

26 ;p

24 O 2fw

q20p41

/6' 61t

o /2 ^ 81

60 /Ol0 4m.o u

v04

C-4 R

-8

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL 21

cows

- 34- %J7-1.28- 1.0/

o i00

o -l00 20 40 60 60 /00

Per cenfofchard

./2

.l0

44 09$

2.0 40 1.08w).8 .36 u.07w

1.6 .32 0.06cj U

/.4 .28 c 0.0542V .24 v.04

Q) 04Ouv.90^

0.03

.8 i .16^ 02

.6 u ./2^ .0/k

.4 .08 0

J-..2 .04 Ci - /0 O

u2

-2'2 ^ '3-4 ff_4

..4

32.-N.A.C.A. 4308 Wdoll.

48

44

40

36 poi

32O

28O

24 pt

20 uCL

16p

C8t

4yU01)

-4 0W

-B tz-/2

_/6

- 60-_ so29

Co,-- 1s- Os

ao

.05-(-.09)

:T8_9 Crodi3s

fs

n

c ^°n

Airfoil: N.A.CA. 4309 R.N.:3,060,000Size: 5'X30" Ve%(H./sec.): 69.8Pres(stnd. otm.): 20.B D&e.4-/3-31Where tested.• L.M. A.L. Test.• VD..T 563Corrected for tunnel-wall effect Dote:

Airfoi/:N.A.CA.Corrected

4-133/to

4309infinite Test:aspect

V.R.N.:3060,000

ra{ioD. T. 563

0 4 8 /2 /6 20 24 26 32Angle of o{tock, a (degrees)

Fioun

-2 0 .2 .4Lift

.6coefficient.

.8 1.0 1.2 /.4 1.6 18

51a.O

L25 2.642.5

5.07.5/0/520253o40506070609095

100

Up'r.-

3.63

S6.227/28469.349.62/0.009.758.987656.394622541.38(' 13)

L'wY.0-1.29

-/. 75-2.19-2.34-2.39-231-2.17-2.07-2.00-1.86-/.6/-1.28- .95- .64- .38- .25(-Q3)

U cN p

/0

U ^ 00 _/o

0 20 40 60 80 /LPer cent fchord

CL. E. Rod.: 1.58si oe orroe^sthrough end ofchord: 4//S

LID C.P.

a

Airfoil: N.A.C.A. 4312 R.N.:3,/80.000Size: 5"x30" Ve/.(fl./sec.: 68.7Pres.(s{i+d.otm):20.8 Dole:12-14-31Where tested: L.MA.L. Test: V D.T. 731Corrected for tune/-wall effect

)

.44

2.0 .40/8 .36/.6 .32

Ci1.4 .28 c

N

/.2V .24v

LOv.20^u0 0

.4^ .08

.2 .04

0 0

-.2-.4

-8 -4 0 4 8 12 /6 20 24 . 28 32Angle of o{lack, a (degrees)FxoII z 33.-N.A.C.A. 4312 aWoll.

/I

.44 .09S

2.0 .40 G.08,v

1.8 .36 x.07

1.6 .32 0.06V u

44 .28`c 00 .05va

1.2 Ci.24X j.04m o

/. 0,E .20 4.03u

.8 v./600 .02o 'o

s °./2 .0/k

.4".08 0

.2 .04 G-./k0 0 0 -.2

-.2 w-.3v

-.4 Z-4-6 -4 0 4 8 12 16 20 24 28 32

Angle of otfock, a (degrees)

48

44

40

36l

3228 i?

.d

24,l

20

v

`c

4^

00

-4ov

-8

Airfoil: N.A.CA. 4315

Lift coefficient, Q

2.5 4.47 -2.267.5 737 -3.3/

20 /0.60 -a6025 11,32-3.55301/. -3.504011.18 -3.3350/0. / -2.9360 9.01 -2.4270 73/ -L66

BO0

529 -/.309 292 - .7495 1.5B - .44

100 (.l6) (-.16)

sto. UPS'. 4M, D t0/.25 3.32 - 60 u 05.0 6./3 -2.97 y o

v

v k -/0/0 0.36 -3.50 0 20 40 60 BO t0l5 9.85 -3.62 Per Cent of,or,

100 0 C

L. E. Rad.: 2.48Slope afradiusthrough end ofchord:4 /5

c. p.L/D

0

Airfoil., N.A.CA. 4315 R.1i:3,120,000Size: 5"x30" Vel.(ft./sec.): 69.3Pres.(stnd. aim): 20.8 Dole:4-14-31Where Msled.•) A.L. Test.-VDT 565Corrected for funnel-wall effect

L-c°kDW

28 0

0

24 0 20

420040N ^e /6 60

/2^8B o /0

e4

mz° 0 4C-4 R

V-8

0

0

2512. 80

Sto. Up 'r. L0,

Z58.56-4.25

20 /22530 13.00 -50040 /264 -47750 //.65 -4.2460 10.15 -3.5570 6.24 -2.7660 5.95 -/.94

90 329 -/.OB95 1.79 - .64100 (./9) (-./9)too - oL. C. Nod.: 356Through end ofchord: 4 /5

0 - 0 W b0/.25 4.07 -/.90 t 02.5 S.36-2.74 y -/0S. 7.20 -3.68 0

/0 9.64 -4.56 0 20 40 60 W /0/5 //.22 -4.92 Per centofchord

Slope ofrod/us L;,

c.p.

LD

C

Airfoil: N.A. C.A. 4318 R.N:3,09Q000Si- 5'k30" VeZ(ft/sec.): 69.5Pres.(st^7datm.):20.8 Dofe:4-14-31Where tested.-L.MA.L. 7 -est.-VDT 566Corrected for tunnel-wall effect

D0kOav

28 p 0

24 3 20

q 200040N ^o /6' 60

0 /2 oC 80u8 0100

0 4v.o u

4 04C4 0.

-B u

22

REPORT NATIONAL ADVISORY COMMPPTEE FOR AERONAUTICS

FIOREE 39.-N.A.C.A. 9315 Elrtoll.

)

.44V$

2.0 .40v

48 36

/.6 .32 0Ci u

1.4 .28 ova

1.2V.24w m

40.^.20va 0u a4

0 0

.6' .12

.4'.08.

.2 .04 V`

0 0 yU

-.2v

-4 0

-8 -4 0 4 8 12 16 20 24 28 32Angle of attack, a (degrees) Lift coefficient, C

FtomE 35 -N.A.C.A. 4318 MO.

sf.JS2.55.0i0/520253040so6070809095/0000

Up',1.251.682.79ass5.155.906.426.766.906.555.954853.561.961.05(.06)-

L''wr.-.64- 79- .82- .60-.25

.12

.46

.741./01.241.271.16.49

24(-o06)

D /00

u u 0u,A

O 20 40 60 80Per cent ofchord

/G

L. E. od.: 0.4051ape ofrodi35through end ofchord: 4120

CL/D

c.p.

IinC,

Airfoil.-N.A.CA.4406 R.N:3,10Q00054, 5"x30" Vef.(ft/sec.): 69.4Pres.(sfd.nofm.):20.9 Dote:8-21-31Where tested: L.MA.L. Test: VOT. 651Corrected for tunnel-wa//effect

D

ukOw

2B o (

24a 2(

O 2004(

/6 6(^ t

u

80/a`^ C

° 4 u,oa^ 0 Qc

-4 4

U-B

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENBFPY WIND TUNNEL 23

D

tkOD

v

28 0 0

24020

20 40N

/6O 60

o /2 °C80uM 8'.100

C0 4w° u

^° O 4C

-4 0.

8 u

Sto:0

1.252550

,0/0.152530405060//.70809095

/00/00

2013.72

4.841296.26

1262/4.291450/4.0912.96/9./86.643.672.00(.221-

o-2./9-3./8-4.38-564-6.19

S. -42-6.50-6.50-6.23-5.56-4.66

ut / 0lR

o -/00 20 40 60 80 /C

Per cen/ofchord

-3.66-258--1.43.84(-.22)

4.o

L.E. Rod. 65s/ape 1'=,ihrou9chord: 4115 C

c.p.

LID

vi

C

Airfoik NA.CA. 4321 R.N:3/20,000Size. 5"x30" Ve%(f/./sec.): 694Pres.(sfnd.ofm.):20.7 Dote:4-15-WWhere lested.-L.MA.L. Test: V.OT 567Corrected for funnel-wo/1 effect

./2

7

.44 .09a2.0 .40 V .08

N18 .36

k1.6 .32 0.06

C°1.4 .28-, 0.05

W ^1.2V .24 x.04

a '^/.0- .20 u x.03

u a.8 v '16° .02o O

.6X./2 .0/k

.4".08 0Y

2 .04 G f

0 0 m-.20-.2 -.3c4 1-4

44

h36 m

32 O

28 b

20 w

/6 0a

4y

0O'er0

-4 0

-81

^A/rfo/1.NA.CA 4321 R.N. 3,120, 0001Dole:4-15-3/ Test, VD.7.5671Corrected to infinite ospectrobo

0 .2 4 .6 8 /.0 /2 1.4 16 LBL/ft coeff/'c/enl, C

-8 -4 0 4 8 12 16 20 24 28 32 -4Angle of oltock, a (degrees)

Ftovaa 38.-N.A .C.A. 9321 SIM%

.44 .09a

2.0 .40 U.08N

1.8 .36 ^.07

1.6 ,32 0.06

V1.4 .28- 0.05

W/.2V.24 v.04

mlo-.20u x.03u

.8 ^./6 0 .02

.6 0 ./2 .0/k

.4".08 0

.2 .04 0-./O O LIZ -.2

U

-.4 0-.48 -4 0 4 B 12 16 20 24 28 32 -4

Angle of oltock, a (degrees)F[0vae 37.-N.A.C.A. 4908 airfo.

48

44

40

36 w

32

28 ti.d

246l

20'.

168-a

12'^

4su

0ZO-4ov

e

N.A.CA. 4406 R.N..:3,/00,000-21-31 Test: VO.T. 651

L ift coeff/'c%ni. 0,

0

44

2.0 .40

1.8 .36 .^

1.6 .32 0V u

1.4 .28 c oW a

V ^

LO,v.20uU

.$ v./s o0 0

.6 U.12w

.4'.08

.2 .04 t

0 0 m02

c

-.4-8 -4 0 4 8 12 16 20 24 28 32

S. 0 3.74 - /.6575 4.64 -1.74

20 7.33 - /.3025 7190 -L0230 8.25 - .7640.8.35- .3550 767 - .0760 7.00 .1470 5.76 .2660 4.21 .2690 2.33 .1495 1.26 03

100 (.03) 1-.091/00 0L. E. Rod.: 0.69Slope o(rodiusthrough end ofchord: 4 20

Sto. up-,. LWr. a cu0 - O u o

10

/.z5 /.e/ -LOS 02.5 2.61 -1.37 R o-/0/0 5.37 -/.73 0 20 40 60 BO //5 6.52 -155 Per centofchord

c.p.

Lm

0

C

AirfOlL'NA.CA.4403 R.N:3,170,000Size: 5"x30" Ve1.(ft./sec.): 68.6Pros.(stndatirz): 2/.0 Dote:8-24-31Where tesfed L.

'WA.L. Test: V DT 652

Corrected for tunnel-watt effect

D

0av

28 'b 03

24 a 20

020040y ^p 16 60

o /2.g 8

8 0/00c

° 4 u00 4

c-4 0.

V-6

0

.44

2.0 .40

/.8 .36

1.6 .32V

1.4 .28W

A2V.24v

LO y.20°U u

$ .!60 0

.6'./2

.4'.08

.2 .04

0 0

-.2

-.4-8 -4 0 4 8 12 16 20 24 28 32 -

Angle of attack, or (degrees)1NOME 30.-N.A.C.A. 4412 91doil.

Lift coefficient. 0.

1.25 2.44 -/.43

7.5 5.76 -2.74

20 6.60 -2.7425 9.41 -25030 9.76 -22640 .460 -/.8050 919 -1.4060 8.14 -L0070 669 -.6580 4.89 - .39so 271 - .zz95 /.47 - ./6

100 - OL.E. Rod.: 1.565/ape of-d,11,

0 lhrough endpfchord: 4 20

S1o. Opi-. Lm, a c

o -0 ^r / 02.5 3.39 -1.95 y5.0 4.73 -2.49 h 0

-/0

/0 6.59 -2.66 0 20 40 60 60 /0

/5 7.69 -2.66 Per centofchord

l00 1.131 (-./31 C

LID c.p.

C

Airfoil, N.A.CA. 4412 R.N:3,200,000Size: 5"x30" Vel.(ft./sec): 66.6Pres.(sfnd.oim.):20.8 Doie:12-15-31Where tested: L.h1A.L. Test: V D.T. 732Corrected for tunnel-wail effect

0ukacm

2810324 1- 20w

Q20 a4l

ri 16 6

12 8

80/0`^ C° 4 u.0R° 0 4

C_4 0.

_g v

0

0

0

0

24 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

33

ai

2 48

44

0 40

09 36

.08--eat 32.

.07 28

.06 24

.05 20

.614 16

.03

.02 r°8.

0/ 4'

0 0

-4

-.2 -8c

.3 Airfoil. NA.C.A. 4409 R.N.:3,170,000 12_ 4 Dote: 8-24-31 Test: V. D. T. 652 -/6Corrected to inf'nite aspect ratio-4 -2 0 .2 .4 .6 .8 /.0 /.2 1.4 16 /.B

Angle of attack, a (degrees)

Lift coeff/cteni,C

Fmm. 38.-N.A.C.A. 4408 I& M.

2 48

44

./0 40

.09 36

.08 °° 32.

.07 28

.06 24'

^.0$ 20

04 l6

.03 2

.02 a 8'

.0/ 4'

0 0

-.2 -8

Airfoil. NA.CA . 4415 R.M.: 3,110.000 /2_ Dote:8-26-31 Test: l!D.T. 654

' 4Corrected to in fihite aspect rofo -16-4 720 .2 .4 .6 .B LO L2 /.4 L6 /.8

Lift coeff can't C

75 6.91 -3.7/

20 /0.25 -415 -25 /0.92 -3.9B30 //.25 -3.75

//.25 -3.255 /0.53 -2.7260 9.30 -21470 7.63 -/.5580 5.55 -/.0390 308 - .5795 1.67 - .36

00 (.16) (-.16)

S0. UP r. L'0r. ^D l0/.ZS 3.07 -1.79 U 02.5 4./7 -2.48 l U5.0 5.74 -3.27 4 p

-l0

/0 7.84 -3.98 0 20 40 60 BO /015 9.27 -4./8 Per cent ofchard

L. C. Rad.: 2.48 Lcslope o7u9through end o7Chord: 4120

e.p.ZT

L/D

oe

Airfoil: NA.C.A.44/5 R.N:3 /10.000Si- S"x30" Vel.(fl/sec.): 69.5P(sti7d.otm):20.7 Dote:8-26-31Zr.Whe tested: L.MA.L. Test: VOT. 654

Corrected for tunnel-wall effect _4 0-8 -4 0 4 8 • 12 16 20 24 28 32

Angle of attack, a (degrees)

.44

2.0 .40 U_6

LB .36 ._6

/.6 .32 0V u

1.4 .28 oW ^

/.2 V . 24k m/.0.200

A./6^0 0

.6u .l2

.4'.08

.2 .04 c

0 0 m02 cv

DO

UkO

CW

28 i 03 .24 'a 20

q20040

0 16--60

x 80/0`• C0 4 v.o ua0 0 4

.c44

-8 u

0

0

0 /0

44 .09a

2.0 .40 ^ 08N

AS .36 ^.07

1.6 .32 0.06G u

/.4 .08- 0.05

1.2V .24 •F v .04v `^

40 .y .200 ^.03.0

.8v.16^ 02-0 0

6 u .12 .0/k

.4 08 03

. 2 .04

0 0 m -.20-.2 u-.3

v-.4 0 -.4

-8 -4 0 4 8 12 16 20 24 28 32 .4Angle of attack, a (degrees)

FIGURE 41.-N.A.C.A. 4418 airfoil.

chord

/.25 376 -2//

7.5 6.06 -4.67

20 //.72 -55625 12.40 -5.4930 12.76 -5.2640 12.70 -4.70s0 /1.65 -4023.60 10.44 -2470 6.55 -2,4580 6.22 -/.6790 346 - .9395 /.89 - .55

Slope ofrod)u5D through Z'endof

5/a. Up •r. Lm,o l0° - ° us 0

2.5 Soo -299 W k _/05.0 6.75 -4.06 C o

15 10.66 -5.49 Per centofchord/0 9.// -5060 20 40 60 80 /0

4.E.Rad.:3.56 C If

c. .

0 L/D

n

Airfoil. N.A.CA. 4418 R.N.:3,100.000Size: 5"x30" ve/(f//sec.): 69.5

I-rl' Dcle:8-27-3/Where tested: L.MA.L. Test: l!0.T 655Corrected for tunnel-wall effect

aO

k2W

28 024 0 20

q 2004N ^

/6^ 6

o /2r8u

8 0/0`• C0 4 v4 u

0 4c

U

-8

0

0

0

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL

25

FIGURE 40.-N. A.C.A. 4415 airfoil.

48

44

40h

36 w

32 v

28 Z{g

24 0l

20 m

168a v

2.'ck

4^

Oa

C ` -4 o

-B

-/2I: NA.CA. 4418 R.N.: 3,/00,0009-27-31 Test: VD. T. 655 -16cted to infinite aspect ratio.4 .6 .8 LO L2 1.4 /.6 /.8

Lift coefficient, C

270770-35-4

26 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

zo

D

t`o

v28 0

3241,20

Q 20x40y ^o /6^ 60

b

0/280

8 0/00

° 4 u00 Q

C-4 0.

-B

1252.550]5/B15253050BO706090

100l0 0

2013.174014.16

4.455.B47.82924%3512.0413 B614.2713. lB//.609.506.9/3B5

/.-

-2.42-3.46-4.78-5.62-6.15-6.75-6.9B.-6.92-s.76-6./6-5.34-4.40-•235-23/-/.27

F00

L^ r D 10g 0

W w _/0h p0 20 40 60 80 lPer cent ofchord

LG Bod.: 4.65Slope ofradiusthrough end ofchord: 4/20

C

.c. pr-

L/D

C

Airfoil NA.CA. 442/ R.11:3.110,000Size: 5"x30" Ve/(H/sec.): 69.4Pres.(stird ofm): 20B Dote:8-28-31Where tested: L.M. A.L. Test: VD.T 656Corrected for tunnel-wall effect

N

B v . /s 0 .02

z

./2-

48

44

O

0

00 ./0 r 40n y

.44 .09-- -36 v8 ^

2.0 .40V .08 a; 32 U

1.8 .36 u.07 26 e

1.6 .32 0.06 24 0V U ^

/4 .28'^ 005 20 uv ^ Q

/.2V.24 y v.04 168

/.'O w .20 um °.03 12U R ^

° o 0.6 u ./2 .0/ 4

S uk.4".08 0 0

0 0 -.2 -8 u'u e

-.4•4 Dote. B-28-31 Test: VD.T. 656 -16.2

w '3 Air foil, N. A. A. 4421 R.N:3,110,000/2

R- Corrected to infinite aspectrotio-8 -4 0 4 8 12 16 20 24 28 32 -4 72 0 .2 .4 .6 .8 LO /.2 1.4

Angle of attack, a (degrees) Lift coefficlent,CFIGURE 42.-N.A.C.A. 4421 airfoil.

0U

W

28 p 0

24 0 20k

Q 20F40V ^g` /6't 60

a 12- BO

8,0/00k c20 4.o

u

0 Qc

-4 0._8 d

25

7.5 3.25 - .97

20545 -:3225 59B .0230 6.36 .3440 6.74 ,9350 6.65 /.3560 613 /.5670 5.21 /.5360 390 /.25

290 /8 .7295 1.17 35

i°o°o /- /-0sl

5f. UPr.G'

'

r. D 10/. -. UC

2.5

.667/U _/0

05.0 260 -/.00 h p/0 362 -.89 0 20 40 60 80/5 4.74 -.64 Per centofchord

L.E. Rod.: 0.4051ope frood usthrough entl ofchord: 4125

L D Cc. p.

0

Airfoil: NA.C.A. 4506 R.N,:$05Q000Size: S"x30" Ve%(H./sec.)Pres.(st'n:

70.0d o

M.tm.): 20.6 Dafe: 4-/5-31

Where fesfed• L.A.L. Test: V.O.T.568Corrected for tunne/-/l effect

e 44

0040

36-0.44 .090 0^2.0 .40 -08 ro 32 O

1.8 .36 .07 28/.6 .32^ x.06 24:944 .28, 0.05 '01

y N

/.2V.24^ y.04 /60k

/.0.1.200u 0.03 uo 12'u.81./60 .02

.6 u .12^ .0/,o

w 4u.4 .08 0 0

r °

vO O y -.2 -8 ^`

°u e

•2 c •3 Airfo#-N..A.C.A. 4506 R.N:3.050,000 -l2

-.4 - 4 Oote: 4-/5-3/ Test: V AT 568 _l6Corrected to infinite aspect ratio-8 -4 0 4 8 /2 16 20 24 28 32-4 -2 0 .2 .4 -6 .8 /.0 /.2 l.4 46 /.8Angle of otfock, o: (degrees) Lifl coefficient.

FIGURE 43. N.A.C.A. 4803airfoil.

51./.252.55.07.5/0/5202530,40506070809095100

/00L. E.Slopethroughchord:4

up',13S2.473.544.36SOS6.126.897.467.856./97.977.276./24.56256/.(.09)-Rod.:afrad'us

end

V0,-1.12-1.50-1.84-1.99-2.05-/.96-1.75-/.47-1.16- .52

.03

.42

.62.60.35/5f-.0910

0.69of

25

D /OU ^ 0L, -/0

0 20 40 60 80 /0Per cent ofcho^d

C

LID

i

C

Airfoil, N.A.C.A. 4509 R.N..:3,120.000Size: 5"x30" V.I.(fG/sec.): 69./P es.(s fnd. almf:20.9 Dote: 4-15-31Where fested: L.MA.L. Test: V D.T. 569Corrected for tunnel-walleffect

a0Uk

v

28O324 0 2iw

N 20041

p /6 61D o°12^Bi

8 0 /Oic

° Suov^ 0 Q.0

-4 0.

G-B

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL 27

.44

2.0 .40

/.e .36

/.6 .32

V/.4 .28c

,W

/.2V .24v

LOv.20^

8x./60o O

.6h ./2

.4'.08

.2 .04

O 0

-.2

-.4-8 -4 0 4 8 12 16 20 24 28 32

Angle of attack, a (degrees) Lift coefffcient,Q

Ul°tU

aCv

28 0

24 3L. 2^o

X20041N ^o /6^ 61

o /2 Cu

e

B o /Oi

0 v4o u

v^ O4C

4 0.v-8

-0 -4

Proves 44.-N.A.C.A. 4608 airfoil.

.44

2.0 .40

48 .361.6 .32

Ci/.4 .281

W2,j. 24 i?

/.0 r .20 0u

.6 .1600 0

.6°./2k

4".08

.2 .04

0 0

-.2

-.4

O 4 8 12 /6 20 24 28 32Angle of attack a (degrees)

F'lovac 46.-N.A.C.A. 4512 airfoil.

5o.12525SO7.5/0152025304050

709095/00

/00

606.43805.23

Up',2.333.224.505.466.257.46a348.959.379.649.29

7.062.93/.58(./2)-

L'-r.

-2.07-2.67-2.99-3.18-3.28-3./7-2.95-266-/-/.97

.29- .70-.2,9-:04

.00- .04(-. 12)0

vD /0OO0 20 40 60 60 10

Per cont ofchord

CLX. Rod: 1.56Slope ofrodusthrough a 2Zchord: 4/25

LID C.P.

r

AlrfOlL'NA.CA.45/2 R.N:320Q000.Size: 5'k30" Ve1.(fL/sec): 68.2Pres.(sfnd ofm):2/./ Dafe:/2-/6-3/Where tesfed'LAIA.L. Test:V.DT 733Corrected for tunnel-wall effect

Lift coefficient,C

48

44

40

N36 w

a32 O

28 ZS

.d24 p

20 u

/6gv

12 1J6 ^^

k4y

40-4 0v

-B

28 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

D

s°

OcN

2B o 0

24 0 20ti

y 20040l

/6^ 60

o /2c80

8,0100

4 C0 v.o u

04C

-4 R

v-8

20/0ow o

.12u ^

7

St..0

/.252.4507.5toIS2025

6070BO90

100

3010.804011.019501062

Up".-

2.94

4 495.6.60].4s8.859.6//0.47

9.56299SB9332

-

L'w^-.o

-/.88B

-300 -2464

8-398-4.30-4.59-450

-4.16-3.44-262-1.e5

0. o

0 20 40 60 BO 10Per cen/ofchord

-1.20- .69- .35

O Ci

L. E. Rod.: 246Slope o/ radiusI= 9,5 end ofchord: 4125

C.P.

LID

C

Airfoi/-NA.CA.45/5 R.N.:3,080,000Size: 5"x30" Vel tft./sec.): 69.6P es.(sfndofm.):20.7 Dote:4-/6-3/Where tested'L.MA.L. Test: VD.T. 571Corrected for funnel-wall effect

.44 .09ti

2.0 .40 •x.08v

48 .36 x.07L6 .32 x.06

v/.4 .28- 0.05

va1.2V .24^ v.04

v

/.O.w.20' x.03U

1 h

.B m'/6^ .02o '0

.6 u .12 .0/w

.4JY

.08 O

.2 .04 V-./O 0 w -.2

U

-.4 0-.4-8 -4 0 4 8 12 /6 20 24 28 32 -4 -20 .2 .4 .6 .8 /.0

Ang/e of Mock, a (degrees) Lift coefficient,CFcaysE 46.-N.A.C.A. 4518 airfoil.

skav

26 0 024,b 20

O 20 0 40y ^/6^ 60

o /280

60/o0`^ C0 4vo u

04c

-4 0.

-8

'r.

u

Slo.

0/.252550/0203040506070609095

/00/00

/5/0.25

2511.96

UP-

3.564.796.49

6.74//.27

12.37/2531/.94/0.726.926573 692.01(.19)-

LWr

0-2.25-316-4427

-5.4/-569-6.01-5. '9'-5.66-4.69-3.94-296311-1.34- .7/- .44(-./9)0

y a cua

/0

l 04 0 0

0 20 40 60 80 ICPer centafchord

L. E. R. d.: 3.56d.Slope of-d,,,

c hord 4125of

c.p.

IL

C

•Airfoil N.A.CA. 45/6 R.N:3130.000Size: 5"x30" 3e).(ff./sec.): 66.9Pres. (sthd afm): 2L0 Dote:4Wherefested.-L.MA.L. Test.VOT 572Corrected for tunnel-wc ,H effect

.//

I

44 .09 - -

2.0 .40 .x.08--_.._ ..._.......v Cno

/B .36 y.07k

1.6 .32 0.06C

1.4 .28`c 0.05W aL2^.24X v.04

v1.0 .a .20 4.03

U

.8v./6o 02

.6 0

.120 .0/ a'.4 .08 0

.2 .04 V`-./

0 0 m -.20.2 .3 Airfoi/: NA.CA. 4518 R.N: 3 /30.000

_ _ Dote: 4-16-31 Test, VD. T. 572.4 .4 Corrected fo inflhVie ospectrofio

40

36 wl

32 a28 ti

168

k6i

4yu

4040

m

e

-8 -4 0 4 8 12 16 20 24 28 32 -4 -2 0 .2 .4 .6 .8 /.0 L2 14 /.6 LAngle of otfoch, a (degrees) Lift coefficient, 0

Frooxx 47 .-N.A.C.A. 4518 airfoil.

S

0

m

26 O024 t. 20

kQ20E

o 40y

16 -60L 00/2280

60100c

0 4u0 Q

c-4

-6

sl.

1.252SSO7.5/020

40506070809095

/00100

1511.632513.4630'3.06

UP'r.4.235.607500.90/0.00

1273

139713.2711.869.657.264062.24

(22)-

L'v, r.

-2.56-3.B6-505-5.90-6.50-7.17-7.42- 7.38- Z/6-635-5.27-4. /2-3.00-1.97- /.05- .63(-22)0

U /O

u i 0 94MmN k -/Op 0 20 40 60 80 /C

Per cent .{chord

LE.Rod.: 4.855/opeofrodiusthrough end ofchord: 4/25

Ci

c.p.

L/D

Co

Airfoi/: NA.C.A. 452/ R.N.:3,150,0006/ie: S° x30" Ve/.(ft./sec.J: 69.0Pres.(sfnd.otm).• 20.6 Dote: 4-/7-3/Where tested:L.MA.L. Test: V.D.T.573Corrected for tunnel-wall effect _4 0

-6 -4 0 4 8 /2 16 20 24 28 32Angle of otlock, a (degrees)

FIGURE 48.-N.A.C.A. 45

7

.44

2.0 .40W

L8 .36 o

1.6 .32 0

Ci u

1.4 .2Bc 0v $

L2 V .24 v

v 0LO 0u

ev.160o O

.6^./2

.4 .08

2 .04

0 0 y

ou.2

c

//j -4

,44

2.0 .40CN

/.8 .36 .0

/.6 .32 0V u

1.4 .28 C 0N

L2V .24w vv '^

/.0_v .20 uu p,

.Bo .lso

.6' ./2w

.4'.08

J.2 .04 VE

0 0 y0

-.2_4 0

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND TUNNEL 29

/2 48

.//

E44

Vco./0P 40

.09 0 311

.08 hl

32 Do,.07 28 tt06

024 p

l.05- zo

v

.04 p16

.03 2

02 ° B0/

0

qtu0

00

0C p -40

_2 v-80e

.3-.4

Airfoi..• N.A.CA. 4521 R.N3: /50,000Dote: 4-17-31 Test: VD.T 573Corrected to infinite ospect rotib

/2_16

.4 .2 0 .2 .4 .6 .8 LO 1.2 /.4 t.6 L8Lift coeff/cient,0

toll.

OLkav

28 0 03

24 0 20

4 20 a 40g16D60

o /280

8 0 /00

4 uo u

0 Qc

-4 0.

- 8 u

S^./.252.5SO7,5/015202530405060706090100/o01-T ROd:/7_6T_

Up ^.2.263./34.36S.6.027.176.0/8.6090l9369.166.567.445.66323!./2)-

Gwr.-1.57-2./6-2.81-3.17-3.40-3.56-3.50-331-3.00-2.27-/.4/- .56

./0.40.3/(-.%210

QD /0 ITTi 0

-/OO 20 40

Per cent60 60 /C

ofchord

0

5/ape cf "ofthrough end ofchord: 4/30

c.p.L/D

a

Airfoi/.• N.A.C.A.46/2 R.N.:3,2/0,000Si 5"x30" Vel.(fl./sec):68.3P es.(slnd.olro):21,0 Dole: /2-/7-3/Where tested.-LM A.L. Test: V.D.T. 734Corrected for tunnel-wall effect

X140

+-H 24

16

8

4

0

Airfoi/:NA.C.A. 4612 R:N:3,210,000Dote: 12-17-31 Test: V D. T. 734 -l(Corrected to 1/7fhffe aspect rotio

-8 -4 0 4 B l2 /6 20 24 2B 32 -4

Angle of ottock, a (degrees) Lift coeff/cie,L CcF-it. 49.-N . A.C.A 4612 airfoil.

44

2.0 .40 UN

18 .36 .0

16 .32 0V U

/4 .28cv ^

A2,j. 24 bv '^

/.Oy.20°u ^4

0 0.6 .12

.4 .08

.2 .04 y`

0 0 yu

2c

E_.4

-8 -4 0 4 B /2 /6 20 24 20 32 £

l0 5.64 -3.56

20774 -377256.3/ -3.6030 9.71 -15640 9.06 -2.5650 6. - /.6460 6.4747 - .6570].6] .34BO 6.21 .9590 3.7395 .4202)

100 L/2) (-/00 0

0

St . up L--No /0

/.25 221 -/.6/ U t 0253.04 -222 k -/050 4.24 -292 y °10 5.13 -3.32 O 20 40 60 80 /L/56.95-3. 79 Per ceniofchord

Ci

chord.

.78

L. E. Rod.: 1.56Slope ofrodLsihraugh4/3sendof

n

Airfoil: NA.C.A. 4712 R.N:3,160.000Si-S"x30" 1/e/(tf./sec): 68.7Pres. (sind.oim):210 Dote:12-18-31Where fested'L.MA.L. Test: V.D.T.735Correctedfor iunnel-wo//effect

0U

v

28 D 0

324 0 20

20 0 40l

p 16 ^ 60L

o / 0t 80k

6 °loo0 40.0 U

v

C4

0.

-8

7.5 6.42 - .46

20 //.74 .2625 //.92 .033011

- . /O4011. -./750 /0.49 :.1260 9.// .0570 7.37 .0/80 5.30 .0290 2.99 - ,03

loo (,/2) (-.",/00 - O

Sfa. up'r. L'0, O cu0 - 0 y /O

/.2S 370- .79 U l 02.5 4.99 - .94 y M. 1050 6.92 - ,79 y p

/s //.09 Per centofchoro/0 9.56- ,15 0 20 40 60 80 10

95 1.55 -:03 ( L

L E. Rad.: 15B5lope ofrodi3sihro39h end ofchard: 6110

c.LID.

n

Airfoil: N.A.C.A. 6212 R.N.:,^240,000Size: S"x30" Vel.(ft./sec.): 66. lPres.(st'nd. ofm):20.9 Dote:12-21-31Where tested: L.M.A. L. Test: V.O.T. 737Corrected for funnel-wall effect

°C

Oav

28 p 0

24 kk 20^o

V20 40

o /6. 60

12,80

8 0 /00

° 4u

0 4c

-4 0.

-8

30 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

4844

0 40

09 36

o.08 32

.07 28

.06 24

°.OS 20

.04-/6

.03 ao /2

.02 8

.0/ 4

0 0

-4

-8

.3 Z- toil. IV. A.0.A. 4712 R.N.: 3, 160, 000 /2_ Dote: 12-18-31 rest: VD. T. 735

' 4 Corrected to infhfte aspect ratio lB-2 0 .2 .4 .R A CO 12 14 1R 4R

Angle of ottoc/, or (degrees) Lift coe fficienf, CFIGURE 50.-N.A.C.A. 4712 airfoil.

7

.44

2.0 .40 GC

/.8 .36

1.6 .32 0V

1.4 .28 0N ^

L2V.24- v

v40i .20 ou h

.8 tE ./6o

.6u

.4". 06

.2 .04 Ci

0 0 yu

_40

-8 -4 0 4 8 12 /6 20 24 28 32 c`Angle of offock, a (degrees)

./2 48

44

0 40

Co, ;.09--36

0.08 32,

.07 28

.06 24'

°.O5 20

04 /6

.03 /2

.02a

8

.0/ 4

0 0

-41

_.2 _6

.3 Airfoil: N.A.CA. 6212 R.N. 3,240.000 -/2-4- Dote: /2-21-3/Test: V D.T 737 _16Corrected to infinite ospecf ratio-4 -2 0 .2 .4 .6 .8 LO l.2 /.4 1.6 /.8

Lift coefficient, CFIGURE 51 .-N.A.C.A. 6212 airfoil.

sf..1252.55075to/520253040506070809095

100l00

UP r1.632463.794.67SB07.268.238.809.006.766.177205.904.272.341.24(06)-

L r.- .40-.34

.OS.50

.96/.792.452.643.002.982.862.622.211,63.86.43

(-.06)O

v ^ /Ou 0ly 0 -/O

0 20 40 60 80 100Per centofchoro

0L.E.Rod.: 0.405/ape of'oo-lhra3qh end ofchord: 6//5

LID C.P.

C

Airfoil: N.A.C.A. 6306 R.N:,$080,000Size: S"x30" Ile%(fr/secf:69.8P es. (st'nd. otm.):20.6 Dofe: 4-/7-3/Where tested.• L.M.A.L. Tesf: VD.T. 575Corrected for tunne%wol/effect

uk0

v28 0 024 k̂ 20

q 20040

0 /6 60

/2U 80

B 0/000 4 W.o u

v02

C-4 0.

-8

./O

.44 .098

2.0 .40 x'-.08

48 .36 ^.071.6 .32 0'.06--

G U1.4 .2B c 0.05.v/2V.24-Zû v.04

v `^40y.20, k'.03

u O,.8v.16o .02o a

.6.12 .0/w

.4 J .08 0g

.2 .04

0 O -.2

-.2 -.3c-.4-.4

-8 -4 0 4 8 /2 16 20 24 28 32 -4 -,Ang/e of aHo'k. a (degrees)

FIGURE 62,-N.A.C.A. 6306 airfoil.

Slo.O

/.250

-.75

20

/O

U2

255.0r0S 767.5/0/5

50./B.46

0204060BO/OPer Gent ofchord 0 ./0

.44 .098

2.0 .40fW

L8 .36 •u.07

/.6 .32 '0.060 u1.4 .28-, p.05

v$/. 2V.24 ,4y v.04

v '^/Ov.20a x.03U ^^

.02O ^

.6i .12 .0/

.4^ .08 0

.2 .04 V -./

0 0 y -.2OV-.2 ^-.3

-.4 0 -.4-8 -4 0 4 B 12 16 20 24 28 32 `C -.4

Angle of otlock a (degrees)FIUVSE 63.-N.A.C.A. 6308 airfoil.

SUaN

28 0 0324 0 20

q20 0 40

p 16 D 60l lo /2 ^ 80o

80)00

0 4 u0v^ OQC

40.U

-8

2025304050607060909095/00

looL.E.Shope/hroughchord.'

9.7010.2910.5010.249.506.356334.942.71/.45

cos)-

Rod.:ofrad'us

end

1.021.351.501.531.55 /.4B/29..5050

23!-0

o0.89

of15

C

C.P.L/D

C

Airfoil: NA.CA.6309 R.h!:3.110,000Size: 5"x30" Vel.(R./sec.): 69.4Pres.(sihd.olmJ:20.B Dole:4-18-31Where fested: L.MA.L. Test: V.D.T.576Correc led for funnel-wo//effect

y36

32

28 tt

20 w

/6 0

12'k

k4^

00p

-4 0ro

-8

40

h360l

32

28 tl

160vc

6CO

4^u

0:,L,0

-4 0v

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL 31

AirfOi/:NA.CA. 6306 R.N.:3,080,000Dote:4-17-31 Test: V D.T. 575Corrected to infinite aspect ratio

O .2 .4 .6 .8 /.0 /,2 44 /.6 /.Lift coefficient,C

4-18-31 Test: V. T. 576Gted to fnfnile aspect ratio.4 ".6 .8 /.0 1.2 /.4 16 1

Lift coeffi'cient,C

40

Ll 7.26 - /.47

20 //. 14 -4025 /1.79 - . 1430 /2.00 .00

11.69 .08

50 10.84 .2360 9.50 .3570 7.76 .3990 5.62 .3490 3.08 ./S95

1.66 .03

St... Up. L'w'r. 1b /0/.25 3.05

-6--- U 0

25 4.20 -1.38 yk y05.0 5.93 -1.56 4 0/0 9.36 -/. 29 0 20 40 60 80 /0015 /0.03 - .83 Per cenl of chord

/00l00 (./2) (-./?j CG. C. Rd.: 158S/ape ofrod'us

yn endofchord: 6/I5

L/DC.p.

Ile

C

Airfoil: N.A.C.A. 6312 R.N.:3.f80,000size: 5"x30" Ve1.(R../sec.): 68.5Pres.(sfnd.otm):2/.0 Dote:12-22-31Where lested: L.MA.L. Test: V.D.T. 738Corrected for tunnel-wa//effect

DO

o0

aW

28 0 0324^ 20

q200 40

0o /sa 60

o /2 u 88'-/00

c0 4vO U

v04-4 0.

-8

'r

u

0

.44U§2.0 .40c

/.8 .36/.6 .32 0

V u1.4 .28 o

v1.2x.24

v k1.0 ,v .20

U6^./6 0O O

.6X./2k

.4 .08

.2 .04 G

0 0 m

U2

cF_4 c

32 REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

44G$

2.0 .40W

1.8 .36 w

1.6 .32 0U

1.4 .2,9-, 0

/.2V.24' wv '^

40 .208 o

e`* ./s o0 0

.6X ./2w

.4J.08

.2 .04 G

0 0 wou

.2cv

-.4 0-6 -4 O 4 8 12 /6 20 24 28 32 F

Angle of attack, o: (degrees)FIOVAB 64.-N.A.C.A. e:

./2 48o x est No. 738.// oo q 577 44

do 40

09 36

.08 32,

.07 28

06 24'

.05 20'

.04 /6

.03 /2:

.02 8'

.O/ 4'

0 0-4'

_2 C. -8

' 3Airfoil: N.A.CA. 6312 R.N.:3,180,000 -/2_ Dole: /2-22 3/ Test: V. 0. 738

' 4Corrected to infinile ospect rolio -/B-4 -2 n .2 .4 .6 .,9 LO L2 14 L6 1.8

Lift coefficient.0W.H.

u

ll

i

U

0

'w

v28 0

3

24 0 20k

020;4^p /6 6

l l

o l2r 8u8 0 /0

0 4 vo u

0 4C

-4 4

_8 v

D

0

-8 -4 0 4 8 12 16 20 24 28 32 -4Angle of allocic, w (degrees)

FIGURE 56.-N.A.C.A. 8316.11U1.

Sic. up'r. LM, 0U/0

/.844

t00

/0 9.6] -236 0 20 40 60 BO 10/5 //.45 -2.13 Per ceni ,fcha d

/25 399

"375 948 -2.39

20 /2.60 -1.6325 /3.25 - 1.6230 /3.50 -/.5040 13.15 -/.375012.16-60 r0.67 - .77]O 8.7/ -.50BO 6.30 - .3090 a45 - .2095 /.BJ-./J/00 (./6J (-

L.E. Rod.: 2485/ape ofrod'us

0 through endofchord.' 6//5

25 5.15 -4SO ].OS -2.27

_/0

0

/00 - 0 C

c. p.

o L/D

0

C

Airfoil. N.A. C.A. 6315 R.N:3,100,000Size: 5"x30" 3el(0.1sec.): 69.7

_ Pres. (surd almJ:20.5 Dote:4-20-31Where tesled.- L.M.A.L. Test: V DT 578_ Corrected for tunnel-wo/l effect

40

36

o° 32

28

24

20

/6

6

a° 4

0

4-8

/2Airfoil. NA.CA. 6315 R. N: 3100,000Dole: 4-20-3/ Test: V D.T. 578 -16Corrected to inf nice ospect ratio2 4 R R /0 /2 14 /R IR

Lift coefficient. C

'z.e2 .44 .09

2.0 .40 ..08ev

LB .36

16 .32 0.06U

1.4 .28 0,05my

L2V .24'M x.04v `^

l.Ov,208 11.03--U 4

.8^.16^ .020 0

6X .12 .0/k

.4' .08 0Y

2 .04k _0 O U 2

_ ' 2 .3--4.4 .4

-.4

56.-N.A.C.A. 6318 airfoll.

1.40455.36

-./9l.5aY'us

fC

5

c.R

L/D

n

Airfoi/: NAC.A.6318 R.N:3080,000Size:5"z30" V.Z(ft/sec.): 69.3P es. (sfnd.otm):2/.0 Dofe:4-20-3/Where tested: LMA.L. Test: VD.7.579Corrected for funnel-//effect48 12 16 20 24 28 32

_?91' of attack. a (degrees'Fcccaa

h

vU

Da0

0

160v

l2ck

4

4y

U

030

-4 0v

_/2e

Dole: 4-20-31 rest: V. D. T. 579Corrected to k7finite aspect ratio l

.2 .4 .6 .8 l.0 1.2 1.4 1.6 1.8Lift coe ffcienf,C

O0V

0D

v

28 0

324 a

kq 20 0i0 16l

0 /2

90

0 4 N.0 U

WD CC

-40.Bu

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND TUNNEL 33

w o /0 2u ^ O

o -/0

0 20 4060 60 /00Per cent ofchord 1 ./0

D

tiaC

28 0 I

24 wa 2

q 20x4y ^o 16D6C ^o /2 B

8010

0 4:o uCv0 Q

C-4 0.

-8

Ito./.252.55.07.5l0l520253040506070809095

%00

Up'r.5.707.209.3611.0312.3514.2615.54/62416.5016.0614.6412.99/0607.694.222.31( 22'

L'Owr.-1.79-2.65-363-4./5-444-454-4.65-4.58-450-4.25-3.7/-3.02-230-1.60- .90-.55( 02)

1, o /0u S Ol U0 -/0

0 20 40 60 80 /0Per cent ofchord

L. E. Rod.: 4.855/ape ofrad LSthrough end ofchord: 6//5

C

cp

i

LID

C

Airfoil.•IV.A.CA.6321 R./V.:3/40.000Si- 5'x30'Uel(ff./sec.): 69./Pres. (stird.otm):20B Dof-4-21-31Wherefesd:LMA.L. rest: V. D.r5B0Corrected

fe for tunnel-wol/effect

.//

.44 .05G$

2.0 .40 •.06

1.8 .36 . v0.07

1.6 .32 0.06's

1.4 .28-, 0.05va

420.240 m.04m `^

10y.20 .03.0

.BV./6o .020 0

.6,Ù .12 .0/

.4' .08 0

.2 .04

0 0 0 -.2u-.2 ^ -.3v

-.4 0-.4

h36%

l

32 D

28 21d

24l

20-.v

/6 pv

2c

8c0

4^

0o^0

-4 0w

-8",Q

AirfoiLNA.CA.6321 R.N:3,140,000Dote: 4-21-31 7ez f: V. D.T 580 1_

FTT-R Corrected to infinite aspect ratio4 -2 0 .2 .4 .6 .8 LO 1.2 /.4 l.6 1.8

Lift coefficient C-8 -4 0 4 6 12 16 20 24 2B 32 -.

Angle of atfacl, a (degrees)FrooaE 57.-N.A.C.A. 6321 airfoil.

7.5 4.24 -.06

20 7.42 1.6125 8.16 2./630 8.64 2.6240 6.90 3.1050 9.49 3.1960 7.64 3.05

Se. u,. -,. L'W^. zD /0Z25 /.45 -.52 02.5 2/6 -.55 L,4SO 3.32 -.36 y p-/0/0 506.2B O 20 40 60 80 /6/5 &J9.97 Per centofchord

70 6.35 2.66ao ass 2.ozsa 2.59 /. u95 /.3B 55/00 (.061 (-.061

100 - oL.E. Rod.: 0.40Slope If-d",Clhroughchord: 6/20120

C

Airfoil: N.A.C.A. 6406 R.N.:3,100,000Size: 5"x30 •' Vel. (ft./sec.J: 69.2Pres. (stud. ofm.): 2/.0 'Dote: 8-31-31Where tested.• L.hLA.L. Test V.O.T. 65BCorrected for tunnel-wolf effect

0

w

W

28 p 03

041, 20wq 20 o40

/6160

4^ 12 u 80

8 0 /00kc° 4 u.o °

0 4c

-4 0.-8 u

.2 .04 C0 O o

u-.2v

-.4-8 -4 0 4 8 12 16 20 24 28 32

44U$2.0 .40 c

/.8 .36

1.6 .32 0U

/.4 .28- 0•v a

1.2V .24v '^

LOV.20u^

A ./6 0.6U./2

4^ .08

.44

2.0 .40

1.8 .36

1.6 .32d

/.4 .28 c.w

/.2V .24

40. .20 u

A./6./6O O

.6 ° .12

.4-'.08

.2 .04

0 O

-.2

-.4-8 -4 O 4 8 /2 16 20 24 28 32

Angle of offock, a (degrees)FILM. 69.-N.A.C.A. 64W .M.11.

5.0 4.30 -/./B

20 966 ./725 965 693010.13 %/240 /035 665SO 9.B/ 48660 8.78 1.9270 7.28 L7680 5.34 /.3690 2.95 .74

/00 /.091 (-.09)/00 O

S1a. up}. L'wY. C C /O

(25 206 -, 0 BB U•C O252.96-L// 40_/0

/0 5.4211 -/.66 O 20 40 60 80 /0/5 7.78 -.36 Per cenfofchord

95 /.57 35 C,

L.E. Rod.: 0.89S/ape ofrodiuslhrough end pfchord: sFzo

p.

Airfoil: NA.CA. 6409 R.N.:3,060,000Size: S"x30" 1/eL (f/./sec.): 698Pres.lst 3 otm):20.8 Date: 9-/-3/Where tested.• L.0 L. Test: l!D.T 659Corrected for tunnel-wo//effect

^pU

0

v28 p 0

324 0 20

420040

p /61

60

£'2 7 80

8 0 /00o 4m.o °

l

C 04c

-4u8

34

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

S

u

i

.12 48

44

./0 40

09 36

.0B 32.

.07 28

06 24'

.0$ 20

.04 /6

.03 /2'

.02 0 8

O/ 4'

0 0:

Airfoi/: N.A.CA. 6406 R.N: $ /00,000 -/2_ 4 Dote: 8-31-31 Test: U. D. T. 658 _16Corrected to infinite aspect ratio.4 -2 0 .2 .4 .6 .8 LO L2 /.4 1.6 1.8

Angle of offock, a (degrees) Lift coeffic/ent, 6iF-.. 66.-N.A.C.A. 6406 W.H.

9Yo./2525SO73to1S202530s06070BO909S

5/00

4011.110

up 'r.2733.605.366577.58.A18/03411.1411.65/1.169.956.23a333/.79/./2)

Uw'r.-123-1.64-/.99-,?.-1.99-1.67-1.25-.76- .38-.20

.55

.711

.65

.73

.39/6

('12)

C L /0U C 0h o_/0

0 20 40 60 80 100Per cent ofchord

CL.E. Rpd.: 1.511/ooe otrod/usthrough end of^hord:s/zo

C

Airfoih N.A.C.A.64/2 R.N:3,090,000Size: S VeG(f//sec.): 69.5

sf7dolm):20.8 Dote:12-22-31Where tested•L.MA.L. Test: V D.T. 739Corrected for tunnel-wall effect

.44

2.0 .40

LB .36 0

1.6 .32 0

Ci u1.4 .28c O

v^/.2.24 :0 v

ti

LO1.206U

e^./soo q

.6X./2k

.4 .08

2 .04 C

O 0 v

U_, 2eE_.4 0

O