NACA TR 460 the Characteristics of 78 Related Airfoil Sections From Tests in the Variable-Density Wind Tunnel

8/8/2019 NACA TR 460 the Characteristics of 78 Related Airfoil Sections From Tests in the Variable-Density Wind Tunnel

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REPORT No. 460

THE CHARACTERISTICS OF78 RELATED AIRFOIL SECTIONS FROM TESTSIN THE VARIABLE-DENSITY WIND TUNNEL

By EASTMAN N. JACOBS, KENNETH E. WARDand ROBERT M. P I N K E R T O N

Langley M emorial Aeronautical Laboratory

REPRINT OF REPORT No. 460, ORIGINALLY PUBLISHED NOVEMBER 1933

27077 0-36-1


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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICNAVY BUILDING, WASHINGTON, D.C.

(An independent Govern ment establ ishm ent, crea ted by ac t of Congress approve d March 3,1915, for the supervision ands tudy of the pr ob lem s of f l igh t . I t s member sh ip w as inc r eas ed to 15 by ac t approved March 2 , 1929 (Publ ic , No. 908 , 70of memb ers who are appointed b y the Pres ident, all of whom serve se, such without com pensation.)

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.LY MAN J. BRIGG S, 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.WILL IAM 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. GU GG ENHEIM, 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, Matriel Division, Air Corps, Wright Field, Dayton, Ohio.

EDWARD P. WARNER, M.S.,Editor "Aviation," New York City.ORVILL E 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, LanJOHN J. IDE, Technical Assistant in Europe, Paris, Franed.

EXECUTIVE COMMITTEEJOSEPH S. AMEs, Chairman.DAVID W. TAYLOR, Vice Chairman.


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REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSof the mean line 2s referred to throughout this report as thecam ber of the airfoil and the position of the m axim umordinate of the m ean line as the position of the cam ber.A n airfoil , produced as described abov e, is designated bya num ber of four digits: the first indicates the cam ber inpercent of the chord; the second, the position of the camberin tenths of the c hord from the leading edge; and the lasttwo, the maximum thickness in percent of the chord.Thu s t h e N .A.C .A . 2315 a i r f o il h a s a m ax imum c am be ro f 2 p e r c e n t o f t h e c h o r d a t a p o s i t io n 0 . 3 o f t h e c h o r df r o m t h e l e a d i n g e d g e , a n d a m a x im u m t h ic k n e ss o f 1 5percent of the chord; the N.A.C.A. 0012 airfoil is as y m m e t r ic a l a i rf o i l h a v in g a m a x im u m t h i c kn e s s o f 1 2p e r c e n t o f t h e c h o r d .In addition to the systematic series of airfoils,several supplementary airfoils have been included ino r d e r t o s t u d y t h e e f f e c ts o f a f e w c h a n g e s i n t h e f o r mo f t h e m e a n l i n e a n d i n t h e t h i c kn e s s d i s t r ib u t i o n .

Preliminary results which have been published in-clude those for 12 symmetrical N.A.C.A. airfoils, the00 s e r i e s ( r e f e r e nc e 2 ) a nd o t h e r s e c t i on s h av i ng d i f f e r -ent nose shapes (reference 3); and those fo r 42 cam-b e r e d a i r f o il s , t h e 4 3 a nd 6 3 s e r i e s ( r e f e r e n c e 4 ) , th e 4 5and 65 series (reference 5), the 44 and 64 series (refer-ence 6), and the 24 series (reference 7).

If the chord is taken alongthe ordinates y are given by

f y = a d ^x + ax + a 2The equation was adjusted tob y i m p o s i n g t h e f o l l o w i n g c o nconstants:

(1 ) M a x im u m o r d i n a t e 0 .1 ax=0.3dy(2 ) Ord i n a t e a t t r a i l ing e d gex=1(3) Trailing-edge anglex=1y(4 ) N o s e s h a p eX=0.1The f o l l ow ing equ a t i o n s a t i sa b ov e -m en t i o n e d c ond i t i o n s r ea thickness of approximately 2

t y = 0.29690. 1 / 0 . 12600x 0.10150

./ - oo. A. C.t_erOe

+ Co G/0/;2456789v = 0.29690 Arx_- 0.12600 x -0.35160x' +0.28430 x' -0.10150x'Basic ordinates of N.A.C.A. f amily airfoils (percent of chord)

5. 0O r d _ _ _ _ . I1 1 -5 7.3581 5.9261 7.0001 1 0 . 8 0 5 1 1 &9091 9.6031 9.002110.0031 4 9 . 0 7 2 1 8 . 8 2 3 1 0 7 . s o d 1 7 d u, 1 8L.E. radius, 4.40. FIGURE I. Thickness variation

The tests were made in the variable-density windtunnel of the National Advisory Committee for Aero-n a u t i c s d u r i n g t h e p e r i o d f r o m A p r il 1 9 3 1 t o F e b r u a r y1932.

DESCRIPTION OF AIRFOILSWel l -know n a i r f o i l s o f a c e r t a i n c l a s s in c l ud i ng t h e

This equation was taken to deThe basic profile and a table offigure 1. Points obtained by f r o m t h e G o t t i n g e n 3 9 8 a n d t happlying a factor to the ordithickness curves to bring them


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CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WINDwhere t is the maximum thickness. The leading-edger a d i u s i s f o u n d t o b e

ar 0 20 ae)= .IoaW h e n t h e m e a n l i n e s o f c e r t a i n a ir f o i ls in c o m m o nu s e w e r e r e d u c e d t o th e s a m e m a x im u m o r d i n a te a n dcompared 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-t i o n s o f t h e f o rm yo= be+ b ix + b 2 X 2w h e r e t h e l e a d i n g e n d o f t h e m e a n l i n e i s a t th e o r i g i nand the trailing end is on the x axis at x=1. Thevalues of the constants for both equations were thenexp r e s s e d i n t e rms o f t h e a b ov e v a r i a b l e s ; n am e ly ,( 1 ) Mean- l ine ex t remi t i e s

X=0^=0X=1'=0(2 ) M a x im u m o r d i n a t e o f m e a n l in e

x=p ( p o s it io n o f m a x im u m o r d i n a te )

andyr=(1 p)2 [(1-2P)+2

( a f t o f mT h e me t h o d o f c o m b i n i n g t h e t ht h e m e a n - l in e f o r m s i s b e s t d e s c r ibdiagram in figure 2. The line joiniof the mean line is chosen as the cthe diagram, the ordinate yt of themeasured along the perpendicularfrom a point on the mean line at thchord corresponding to the value w a s ' c o m p u t e d . Th e r e s u l t in g u p p e rpoints are then designated:Sta t ions x and x,Ord ina t e s y and yw h e r e t h e s u b s c r i p ts u and l r e f e r tsurfaces, respectively. In addition the symbol 0 is employed to desigtween the tangent to the mean liTh i s a n g l e i s g i v e n by

6 = tan-1 dx

y Oa lxa. ya=Ion-' d./0-ytMean /ins

P1ChordpO r /xt , yt/ = x - y, sine Yu ' Y + yt cos B-./ O Lodius fhrough end of chordt = x + y, sin a yt = yt -yt cos e /Sam ple ca lcu la t ions fo r deriva t ion o f N .A .C .A . 6821z v, ue t an a sin v a o s a y, sin e y. cos a z, v . x0 0 0 10 .40 0 0 0 0.37140 0.92840 0 0 . . . . . . . . . . . . . . . . . . . . . . . . 00.01250

.30000.03314.10503

0.00489.06000

.383330

.357930

.933751

0.011860

0.03094.10503

0.00084. 3 0 0 0 0 .

0.03683.16503

0.0..am1 .07988. 0 2 2 1 .048980 -. 07347- . 1 7 1 4 3 -. 07327- . 16897 .99731.98662 -. 0058 5-.0037 .07906.00218 .805851.00037 .12863. 0 2 1 8 ..9

Slope of radius through and o f c h o r d .FIGURE 2.-ethod of calculating ordinates of N.A . C.A. cambered airfoils.

y o =m ( m a x i m u m o r d i n a te ) The following formulas for calculat


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06- G 09

001Z-O550-018CL0 025

2 2 0 6 2 3 0 6 2 4 0 62 2 0 9 2 3 0 9 2 4 0 9

' 2212_ 2 3 1 224122 2 1 5 X3152218 2 3 1 8 2 4 1 8

C__' _.1 ' -2421^-----2 , 5 0 6

250928- 20 6 4306 4406 4 50 6

4209 4309 4409 45099212 4312 4412 45124215 4315 4415 45154218 4318 4418 4518

4221 4321 4421 45216206 6306 640 6 6 5 0 6620 9 630 9 64 0 9 6 5 0 96212 6312 6412 6512

6218 6318 6418 6 5 186221 6321 6421 6521

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSA f am i l y o f r e l a t e d a i r fo i l s w a s d e r i v ed i n t h e m anne rdescribed. Seven values of the maximum thickness,0 .06 , 0 .09 , 0 .12 , 0 .15 , 0 .18 , 0 .21 , and 0 .25 ; fou r va lue s

of t he c am ber , 0 .00, 0 .02, 0 .04 , and 0 .06; and s ix va luesof t he po s i t i on o f t h e ca m ber , 0 .2 , 0 .3 , 0 .4 , 0 .5 , 0 .6 , an d0.7 were used to derive the related sections of thisfamily. The profiles of the airfoils derived are shownco l l ec t i ve ly in f i gure 3 .

For the purposes of this investigation the construc-t i o n a nd t e s t s w e r e l im i t e d t o 6 8 o f t h e a i r f o i l s . Tab l e sof ordinates at the standard stations are given in thefigures presenting the aerodynamic characteristics.These ordinates were obtained graphically from thecomputed ordinates for all but the symmetrical sec-

models, which are made of duof 5 inches and a span of 30 instructed from the computed ordescribed in reference 8.

Routine measurements of lm o m e n t a b o u t a p o i n t o n t h e cc ho rd b e h i n d i t s f o rwa rd e nd weNumber of approximately 3,0approximately 20 atmospherwe re f i r s t te s t e d t o s t u dy t h e v aeach group containing airfoils obut having the same mean lihaving a thickness of 12 perc

FE3.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 whichthe surfaces are faired. In the construction of them ode l s t h e t ra i l in g e dg e s w e r e r o und e d o f f .

tested to study the variationm e a n l in e . RESULTThe results are presented in


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Lw0r.. 9 4 7 U i 0

/2- / .307/.777 y W -/0yp-241-2 .673- 2 . 6 6 9 O0000 100Per cent ofch-d l0.4 40 9204 0. O B, y1 . 83 6. 0 7 .L 6 . 3 2 V 8.06L 426% 0 .05.v/.2V .24 ^ v.04

K4 00.0 3u. 8 8 . 1 6 00 2o60./20 /.4^ .0B.2040-.z2 .. 0 0 /-2.902a- 2 . 2 8 2,832- / .3/2- 7 2 4. 4 0 31- 0 . 4 0L D c . p . CA i r fo i l: N . A . C . A . 0 0 0 6 R . N . : .^ 2 1 Q 0 0 0Sze: 5"x30"e % ( 0 . ./ s e c . ) : 6 6 . 5P r e s . ( s t h d . . o t m . ) : 2 0 . 8 D o f e : l-4-32 _ ' 2W h e r e f e lt e d . L . M A . L . T e s t . U . D . T . 7 4 4Cor rec ted fo r tunne l -wo lleffect. -. 4.4

. . 40 21604 28 32Angle o f . , tack, a (deg rees) F--.-N.A.C.A. 0000.W.H.u01

28 024 0

kN 200 1 6 ylo /2^g 00 4 u

vo Q.0-4 W

-9 0 Airfoil: N.A.C.A. 0006D a t e . - I - 4 - 3 2Correc ted to in fin ite as2 .4 .6 8 10 1.Lift coefficient, Cs t a .O12 5255 .07 .51 01 5202 540503 .607 06 09 0 1 .304.50/

O p ' r .O1 . 4 2 0,96/6 6 63./50.5/24 . 0 0 94 . 3 0 34 . 4 5 63 5 2-'3 . 4 2 32 . 7 4 6/ . 9 6 7

C.'r.0- 1 .- 1 . 9 6 /6 1-2666- 3 . 1 5 0- 3 . 5 1 2- 4 . 0 0 9- 4 . 3 0 3

cuUv a /0U - CU4 0 -/ 0 O0000Per cen t o f cho rd- 4 . 4 5 6- 4 . 5 0 14 . 3 5 2- 3 . 9 7 /-34232 . 7 4 60 6 6 - 1 . 0 6 6/ . 9 6 7/0 0L . E .1 0 0 ! 0 9 5 )0R o d . :

(A 5J00 . 6 9C

c . p .

LD

11 vi IC

DSU41

28 1? 12421q 2004/o /6D 6ita / 2 ^ B i8 0 / 0 , 4u

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND

.4 4092 0 . 4 0 ^ ' . . 0 8N1.8 .36 .g,.071.6 .32 0.06

e U1.4 .28- 0.05

1. 2G.24 v.04^/ .0 8.208 Q.03u.88.160 .02

0. 6 8 0 . 1 20 /w 4` 1 . 0 8 ,0.2 .04


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8EPORT NATIONAL ADVISORY COMMITTEE FOR AERONAIITICSt

20v o /o/2u O

00 ./0-.440 92.0 .40 -08N/.8 .36 x.07

1.6 .32 0.06C1 U

/.4 .281 0.05,m V

v .04v ^=1.01.208 .0 3A1602o O..6'.120/.4'.08i.2 .0400 u .2

u-.2-.3-.4.4-8. -4 0 4 8 /2 16 20 24 26 32-4Angle of oftoch, o: (degrees) FIURE 0.-. A . C . A . 0 0 1 2 Oit 0.U0U

`o

280 024 0 20

wg20 400 /6 60la/2808 , 0 1 0 0

Ot'wav2 6 0 0

2 4 0 2 0-0 40p /660

1 2 8 09 - /00

4 uu0 Qc-4 4

-8 u

S l a U p ' r .02 . 5 2 6 / 5. 0 3 . 5 5 57 . 5 4 . 2 0 0/ 0 4 . 6 8 3/ 5 5 . 3 4 52 0 5 7 3 82 5 5 . 9 4 13 0 6 . 0 0 24 0 5 . 6 0 35 0 5 . 2 9 4604.563-4.7 0 3 6 6 48 0 2 6 2 3901.445-9 5 . 8 0 7% 0 0 ( . ^ )

/ .2 5 / . 8 .9 4 - 1 . 8 9 4- 2 6 1 5- 3 5 5 5- 4 . 2 0 0- 4 .683- 5 3 4 5- 5 . 7 3 8- 5 . 9 4 1- 6 . 0 0 2- 5 6 0 3- 5 2 9 45 6 3

o O0000P e r c e n t o fc ho r d- 3 . 6 6 4-2623 1 . 4 4 6- . 6 0 7( - . p 6 )L . E . R o d . : 1 . 5 8 Ce.p.

L/

A i r f o i l: N . A . C . A . 0 0 1 2. N : 3 , 2 3 0 , 0 0 0S i z e : SWO". I. ( k / s e c . f : 6 8 . 4P r e s . ( s fn d . o t m . ) :2 0 7 D a t e . , 1 2 - 3 0 - 3 1W h e r e t e s t e d . L . M . A . L . T e s t . , V . D . T . 7 4 3Corrected for funnel-wol/ effect ../2

000.4409$20 .40 r 0 8Cv/.B .36 .07V1.6 .32 0.060 u1.4 .26- 0.05.v

42V

.24wy.04,.0 208 .113.8 w . 1 6 00 2a. 6 ou . 1 20 /v. 4 v .0 8 0tSlo Up'r.0[252.3672.53.2685.0 4.4437.5 5.250/05853/5 6.68/207./7225 7.4230 7 . 5040 7.25450 6.61860 5.70470 4.S80BO 3 . 2 7 990 /.8/09.006l00 (./SB)/L'w'r0-2367-3268-4.443-5.250-5653-6.681-7./72- 7 . 4 2 7-7.502-7.254-6.618-5.704-4.580-3279-/.8/0-/.008(-. 1 5 6 10 a20N p / 0U l 011004000Per cent ofchordL. E. ROd.: 248 Cc . . / .4 .6Lift coefficie


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20/2>a Up ' r . L'w' c U /O

z00av

26 02 4 L . 2 0

ay20x40o /6A 60l01280

8 0 1 0 00 4m.o l0 Q

- , 1 ' C r yu-8

440 92.0 .40 GC 08/.8 .36 x.0746 .32 0.06

1 U1.4 .28c 0.05

/.21.24 x.04M/ .Oy .20^4.03U.8.160 .02.6 u .12 .0/q -. 4 - 4 . 0 8.2 .0403 -.2

-.4 0-.4k-8 -4 0 4 8 12 16 20 24 28 324A n O / e o f o i t o c k , a ( d e g r e e s )F i o n a a 8 .-N.A.C.A. 0 0 1 8 a i r f o f l.

1 0 2 6 4 /Z 5 3 . 9 , 1 1S O 5 . 3 3 26 . 3 0 0o/0 7,02420 6.0/8-2 0 6 62 5 6 9 /30 9.003

- 2 . 8 4 12 - . ? . 9 2 2-5.332-6.300-7.024_6.0/66 . 6 0 6

^ cv ^ _ / 0C o000O0P e r c e n t o f c h o r d-6 .9 /2- 9 . 0 0 340 6.5 0 7 . 8 4 /4 16 0 6 8 4 5 - 6 . 8 4 570 54366 0 3 9 3 590Z/ 729 5 1 . 2 1 0(. /0 9 )AXL.E,Had:-6.705-7 .94 /-5.496- 3 9 3 5-2.172-/ .2/(-.0 9 )3.56 C

c . p .

L/D

C ,Airfo i l :N.A.CA.00/8. N . : , 1 1 5 0 . 0 0 0Size : S "x30"e ( . ( H . / s e c . ) : 6 8 . 8Pres. (s tnd. a tm. ) : 2 0 . 9 D a te : 1 - 6 - 3 2Where tes fed:L.M.A.L. Tes t . VD.T, 747Corrected for funnel-wolf effect. Ai r fo i l : N .A.C,A. 00 /8Dote: / - 6 -32Corrected to infinite a42 .4 .6 .8 /.0Lift coeffiient.0

.44R .4 0/.8 .36

/ . 6 . 32 114 .28c.v1.21.24 1vE/.0y.20uus .l6 0o O.60: ./2

.4-.08

St. upr.l0 33/425 4 . 5 750 6 . 22 /7 . 5 7 . 3 5 0l0 6 . /95/59.354-9.35420 to259 7304 0 / 0 / 550 9.2660 7 .96670 6.4/2041090 253395 /.4/2-/.4/21 0 1 1 ( . 2 2 1 , 1 - . 2 2 1 1/L ' w r .-3 .3 /4-4.576-6 .22/-7.350-6./5- /0.04/-/0397- / 0 . 5 0 3- /0 /55-9.265-7 .986 C C /Ou s 0k _ / 0y o 0 20 .0'000P e r c e n t o f c h o r d--6 .9 /2- 4 5 9 0-2.533OL . n Had.: 4.65 C

c . p .L/D

lOu0OacN2B 0 024 a 20

kV2 0 0 4 0/6t 60l/2480

60 (0 00

HARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND


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5/a.0

255 .07 . 5/O202 53 04 05 06 07 0609 0950 0

2 5 2 . 4 4

/57.25

Up'r.-3.354.625.55-26.277747 9 37 . 9 77 . 6 67 . 0 26 . 0 74 . 9 0352/ . 9 31.05( . / 3 )

LWr.O- /.46-/.96-235

93/- 3 . 4 4-3.74- 3 . 9 4- 4 . 0 3-392- 3 . 5 6 '- 3 . 0 5- 2 . 4 3-1.74- 9 7- . s s( - 6 1 3 )

D 20y o !0V tlR p -/0O00001 .P e r c e n t o fc ho r dDL . E . R a d : 1 . 5 65tope o fd-0

L/ c. p

agOaW

28 032 4,2 00 2 0 0 4 0lp /6^ 60l0 12 80

8'-/00k c04 v

ioEPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSU p ' r .

2 S 5 ^ 75 . 0 7 . 4 0 67 S 6 . 7 5 0/ 0 9 .7 5 6 - 9 . 7 5 6/5//./36-/1./362 0 / / . 9 5 3 - / 1 . 9 5 32 5 / 2 . 3 7 83 0 2 5 0 440 2.095 0 / 1 . 0 2 9 - / 1 . 0 2 96 0 9 . 5 0 7 - 9 . 5 0 77 0 7 . 6 3 3 - 7 . 6 3 38 0 5 . 4 6 590 30/61 . 6 8 0 -1 0 0 ( . 2 6 2 )0L'wi:

- 5497- 7 . 4 0 6- 6 . 7 5 0z D/0dV1C o- /0

O000OLP e r c e n t o f c ho r d- / 2 . 3 7 8- / 2 5 0 4-209-5465-30 /6/ . 6 8f - . 2 6 20L C . R o d . : 6 . 8 6c . p . I C . 11r-

C

Airfoil: MA.CA. 0025 R.N.:3,230,000Size: 5"x30 Ve/(fl/sec.): 68.3P r e s . ( s f n d o fm . J . 20.9 Date : 1 -8 -32W h e r e t e s t e d L . M A . L . T e s t : V D . T . 7 4 9C o r r e c t e d f o r t u n n e l -w a l l e f f e c t

lOtUOUcv

28 0324 0 2 1kq2004(1 6 6 1

0 /281B o / O ft i04 m

.olR 0 4.0

4 0.V-8

. 4 42.0 .401.8 .361.6 .32 G / .4 .28 1rL 2,j. 24 v1.0 , y .20A.16./6^0 0.6 u./2.4 08.2 .040 0

- . 2- . 48 -4 0 4 8 12 16 20 24 28 32A n o f a tt ac k , a (d e g re e s )

1'..30.-N.A.O.A. 0 0 2 6 a i r f o i l. Lift coeffici

44

2.0 .40 d/ . 8 . 361.6 . 3 2U1.4 .28 0

w 2j .24 v101 2 0 v o

B .16 0O O6u./24".08

a

2ll./0.09.08.07.06

x.0 5.04.03.020


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2/

/0.09.0607.O6.OS. 0 403.02-a 1.0/0

. 3i r f o i /. N . A . C A . 2 3 0 6_ q 9ote:9-24-31eCorrected to inf in i te aspe-4 .2 0 .2 .4 .6 .8 10 /.2 Li ft co ef f ic ien t .01 .4 4 V2.0 .40 v/.8 .36 .9/.6 .32 0C31.4.28 PN O/, 2 t i .24 m '^/O.w.20$eo./sa.6^./2v. 4 . ^ .08 Y.2 .04 V`7

5 .0 3 3 6 -2 .0 /7 .5 4 . 9 -2 2 420 6.06 -2.5225 6 .37 -2513 0 6 .5 0 -25040 632 -2 .3950 5.62 -2.1360 5 .07 -1.7670 4 . /1 -1 .3680 2.96 - ,9790 / .64 - .549 566 - .331 0 0 ( . /0 1 / - . /O )lo oSt . u p ' r , L '. l0I25 1 . 6 9 - 1 . 1 6t2.5 2.39 -/.56 y _/0t o a . 7 - 2 . 3 6000 .0015 5.54 -250e r c e n t o f c ho r d5""' o J r o d ' u sT h r o u g h e n d o fc h o r d : 2 1 7 5L . E . R O d . : 0 . 6 9c .

1L/D

1

. 44R .4 0/.8 .36

1.6 .32V/.4 .261.v

1.0 y.20u

8w./6o0 0.6,"./2. 4 ^ . 0 8

OU0OacW280 0

24 0 20w' 2 0 Q 4 0$1660F12880

B o l oo qm

0

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND

0U0c

280324 a 2 0A20`40g /6u 60u /2 u 60

8'-/0vv0 1.c- 4 0 .-8 u

0

7.5 30/ - / .2220 4.65 -1.0925 4,91 -1.0430 S.00 -1.00404.86-.945 0 4 .49 - . 8 /s 0 3. 92 - .6 570 3 .19 - .4860 2 30 - .339 0.26-.199 56 - .13l00 (.06) (-.06)/005 ^ up'r . L'^ r ./0Z25 1.16 - .73g2 5 / . 7 0 - . 9 5y5.0 2 .43 - / . /50-/0/ 0 3 . 4 6 - 1 . 2 200000/5 4 .18 - / . /6e r c e n t o f c ho r dC . E . R o d . : 0 .4 0S l o p e a f r o d ' u sl h ra u g h e n d o fchord: 2115

C .LDC aA i r fo i l: N . A . C . A . 2 3 0 6 R . N . :3 , 0 8 0 , 0 0 0S i z e ; 5 " X 3 0 "e l ( f t . / s e r , 4 : 6 9 . 8Pres.(sfnd.otmJ206 Do fe:3-24-31W h e r e 1 - 1 . 1 . L , M . A , I , T e s t : l< D . T . 6 6 0- 4 Correc ted fo r tun ne l -wal l e f fec t 00v0-. 2-. 4-6 -4 0 4 6 12 16 20 24 28 32A n o f a t tac k , a ( d e g re e s ) FIGURE 12 .-N.A.C.A. 2 3 N a i r f o il .


14/61

12

0U02 8 002 4 0 2 0kQ 2 0 Q 4 0

p 16 , 60l2 g 06 , 0 / 0 04 u0 QC- 4 0 .

-B

OOUv0

' 2 0 o 42

klp DD o 6

8 0 /0 0

2B 0

0/6 6O/ 2 0

REPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS20

wo /o/2m k _ / ^ x Tes t ASt..0/.252.5507 .51 0/52 02 53 04 05 06 07 08 09 095

/0 0

up,.-2.243.//4.3/5 . / B5 . 8 66 . 8 9] . 5 47 . 8 8B . 0 0] . 7 77 . 1 46 . 2 15 . 0 23 . 6 22 0 01.09/ i 3

L'w'r.0-1.57-2/6-285-326-352- 3 . 8 2- 3 . 9 4- 3 . 9 9- 3 . 6 4- 3 . 4 5- z . 9 2

y00000LPer cen t o f cho rd-231-/.63- .9/5Z/ 0 3 CL L . R o d . : 1 . 5 8

/ h ar d d h 2 % / d o flo p e o f r o d ' u sLID

a

Airfoil: N.A.CA.2312 R.N.:,1120,00 0S ize : S"x30"e % ( N . /s e c . ) : 6 9 . 2Pres.(sf 'nd.otm.):20.9fe :12 -2 -31W h e r e t e s t e d . ' L .M A . L . T e s t . V . D . T . 7 2 0C o r r e c t e d f o r t u n n e t - w a l l e f f e c t'8482604 2 8 3 2 -4Angle of at tack, a (degrees) F-B 19.-N.A.C.A. 2312.W.R.Sla.o Upr.- Lw^.6- 20/oo 2/.252.5 2003B5 -1.,96-2.74 U , ^ .l U5 0 5 . 2 6 - 3 . 6 67 .5/ 0 6.287.06 -4.25-4.66 O0000 n20 8.97 -53830 9.50 -5.5040 9.22 -5.2950 7.47 -4.7760 7.36 -4.0670 5.95 -32260 4.29 -22890 1.36 -/.2695 L3072/00 /.161 (-./6)

/5 8.25 -5.13e r cent ofchord(/00 - Oall25 9.3 5.485/ape afrodiu5

2 4h o ( d h ^ s o tL.E. Rod.: 2.470.L /D

Airfoil: N.AC, 23Dote: 12-2 3lCorrec ted to in fiO .2 .4 .6 .8 L i f t c o e f f i c

440 92.0 .40 G .O BC LL EE/.8 .36u.07i 61 .6 .32 p ,06V u1 . 4 . 2 8 - ^ p . OS.v. a42V.24 ^ v.04w/ .0U . 2 0 u " . 03

.8./60 .020 0.6 u ./20/.4^ .087 .4 4092.0 .40 .V -.OB/.8 .36 ^.07L6 .32 0.06VQ U1.4 .26" : ^.05. dl2V .24 v.0440 .20 1)^.03.8 w . 1 6 00 20.6^ .120 /.4 ' 4 . 0 8.2 .04 GkOu - . 2- . 4-. 4


15/61

0 044 .09

If20.406/.8 .36 vx.07l.6 .32 0.06

C1 U1.4 .26c th1.2j.2404

v/.O,n .2011 1.03u.8 m .160.020 0. 6 . " . 1 20/.4'.08s.2 .04 C-./

Oy -.20u2_3,.rreC.A..4-.4-8 -4 0 4 8 12 16 20 24 28 324 c2 0 .2 .4 .6 .8 /.0 /.2A n g l e o f o t to c k , a ( d e g r e e s )i ft c o e f f i c i e n t .

FIGURE 16.-N.A.C.A. 2908 MEN].

Sto.01 . 2 5Z .5. 0101 5202 53 05 07 08 09 0

10

4 0 4 .90604.08

upr:-/.///.572.283243 . 9 04.374 . 6 94 . 8 64 . 6 02 . 4 41 . 3 51 0 6 13.33

C w 1 r .0- 0 . 60- / .04- 1 . 2 9-45- 1 . 4 4-1.37- 1 . 2 5- / . 1 2- .90- .70- .4 9- 20- . 1 /( - . 0 6 1

-B,10t 04a-/0p0 0000 /Per cen t o f cho rd

0 . 4 05 1 o p e o f n v d i, 5t h r o u g h e n d o fchord: 2120

I I

LID C

A i rf o i l: N . A . CA . 2 4 06 R . N . :3 , 1 20 , 00 0Size: 5"x30"e/.(ft./sec.): 6 9 . 3Pres. (sfnd. otm):20.7 Dote: 9-8 - 3/Where tesled. L.M.A.L. T est . V.D.T. 665Corrected for tunnel-woll effectU0N2B p 024 20y -0Q40/6D 60Q12-c 808'.100^ . 48 ,0QC-4 0.'B U

7

44092.0 .40 x.08C/8 .36 x.07L6 .320.06^q U1,4 .28 0.05N ^L2, j .24 M \ .04

vL020,03--.8 W .16020 0.6" .120/.4".08

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABL E-DENSITY WIND T

OiOc02 8 p 0324 0 20k0 2 0 0 4 0/6a 60

/2g 808'.100'5^ .1 . 2 52 . 55 .07 . 5 '/O1 5RC2 53 005 005.704B O9 09 5/0 0to o U p ' r ./ . 6 22 2 73 . 2 03 . 8 74 . 4 35 2 55.816 . / 86 . 3 8U S. 22273 . 1 01 . 7 2.9 4( . / 0 )- L W- 1 2 3- 1 6 6-2./5- 2 . 4 4- 2 . 6 0- 2 . 7 7-2.79- 2 . 7 4- 2 . 6 2- 2 . 3 5- 2 . 0 2-/.63-124- .8 5- ,47- , 2 B( - . / 0 )o - , ' b l0U g OY v - /0 O0000 /GPer cen t o f cho rdG . E . R o d : 0 . 89/h 1 0 3 g h e n d o fchord: 2/20 Cc .L


16/61

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 - .661 0 0 ( . 1 6 ) ( - . 1 6 1to oS 70o . U p 'n G O Y : ^0Z25 2.71 -206t2 5 3 .7 / -2 86k _ /05 . 0 5 . 0 7 ' - 3 .8 4106.83 -4900000L15 7.97 -542e r c e n t o fc ho r d5 / o p e o f r a d i u slhrdh2%20 fL.E.Rod.. 2.48c .LD

5Iv28 0

24 0 20kC 20' 40

g /s F 60o /2 88 0 / 0

00

14EPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSS o .!252 .5507 . 51 01520253 04 05 060706 09 09 5gi

w2.152 9 9.1 34 . 9 65 . 6 36.617.267.677.687.60.7 2 46 . 3 65.183 .752 . 0 61.14

31-

-465-227-3 . 01-346-3.75-4.10-423

V s 0vk-/Op000006Per cent ofchord-4.22-4./2-3.60- 3 . 3 4- 2 . 7 6-2.14-/.50- .8 2- .4 6

'0L . E.Ra d . : 4 5 0Slope ofradiusYh -d . - end ofchord: 2/20

CA i r fo i /: N . A . C . A 2 4 1 2. N . : . 2 5 0 , 0 0 0S i z e : 5 " x 3 0 "e / . ( f t ./ s e c . ) : 6 6 . 0P r e s . ( s t n d . o tm . ) : 2 / .0 D o t e : /2 - 3 - 3 1W h e r e t e s t e d . & A . L . T e s t : V . O . T . 7 2 1Corrected for funnel-wall ef fect-8 -4 0 4 8 12 16 20 24 28 324 -2 0 . .2 .4 `6Angle of o t tock. a (degree s)i ft co tF-E 16.-N.A C.A. 2412 a ic [o l l .av28 p 02 4 a 2 0kV 2 0 1 4 00 /6t 60lo /2.2 808 0 / 0 0k 4u.oC 04.c_4 0.-6 U / . 4 40 92.0 .40 U . 0 8d48 .36 x.07/.6 .32 o.06V U1.4 .28- 0.05-/ .2V.24^ v .04v^/.Ov.20 1 .0 3u. 8 u . 1 602o O.60 .120 /. 4 v . 0 8.2 .04 V`-.lk0-.2U. 23i r f o i l : N . A . C . A-4-4a t e : 1 2 - 3 - 3 1Cor rec ted to./I

44092.0 .40 G . 0 8v48 .36 x.071.6 32 , o.06q V1.4 .28-, 0.05

Q U O ) v. 8 v . 1 6 0 .OR--o a. 6 0 . 1 2 0 /k. 4 ^ . 0 8


17/61

.4 42.0 .40LB . 36/ .6 .32

Ci/.4 .28vL 2V.24 vL O , v .2000U.6x.1600.6' ./ 2.4.08.2 .04

s t o .0/.252.55 .07. 5/01512025012405 06 0708 090as00(.

/0 0

U P r .-3.87S2/7.008.299.28//.59/2/5.3 69.799 47 4/.7622 )-3.18 -1.66

L 'w r .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 r4 a -/0

000000Per cent ofchordL.E.Rad, 4.855/ape trod, at h r o -1 g h e n d o fchord: 2120

dec.P.

/D

UltU0av2 8 0324 ,0 20

q20 0 40o /sa soo 1 2 yu 8 0

8 , 0 1 0 04 u

% C K A . 0 A . 24 1 89-11-31clad to inh i , it.4 .6 .8L i ft co ef f / c ie / C

7.440 92 . 0 . 4 0 x ' . 08W/.8 .36 x.07

L6 .32 0.06G U1.4 .28`c 0.05v/ .2V .24k m.04wv40v .208 L . .03u.8v.16^ .02--0 0.6./20 /k.4 08.2 .04 Of-./0w -.20

-.2.3-.4- . 4-8 -4 0 4 8 12 /6 20 24 28 324Angle o f .Hock. a (degrees) n - R E 2 0 . - N . A . C . A . 2 4 1 8 a i r f o i l .S i . .L 2 52 .5507 . 5/0/55 06 070B O9 09 5/0 0/0 020/0 . /52 5 1 0 . 6 53 0 1 0 . 6 84 0 / 0 . 7 1u p ' r .3 . 2 84 . 4 56 . 0 37 . / 78 . 0 59 . 3 49 . 6 98 . 6 57.02S O B28 // . 5 5/./9)- G W r- 2 . 4 5- 3 . 4 4- 4 . 6 8- 5 . 4 8- 6 . 0 3- 6 . 7 4- 7 . 0 9- 7 /8-7./2- 6 . 7 /-599- 5 . 0 4-3.97-280-L53- .67( -./9)O /0u r 0l U0-/O00000LP e r c e n t o f c ho r dL . E . R o d : 3 5 65 " p , ofmend ar a d ' u st,chord: 2/20 0a . P .L/D nA i r fo i l. N A . C . A . 2 4 1 8 R . N . : 3 ,0 6 0 , 0 0 0S i z e : 5 ' x 3 0 "e / ( f1 / s e c ) : 6 9 . 8P r e s . ( s f n d . 1 - ) : 2 0 . 8 D a t e : 9 - 1 1 - 3 /W h e r e t e s t e d .- L .M A . L T e s t : V D T . 6 6 9Corrected for tunnel-wall effect .DO4'.v2 8 0 024 0 20k20 40N 0 6D60a 12808 ' . 1000 4 v0 Cc-4 0.u-8 CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE-DENSITY WIND


18/61


19/61

.442.0 .40L03 646 .32

UQ1.4 .28NL 2 V . 2 4 mL O , y . 2 0 0A o.6X.12k.4'.08.2 .04

5 1 a .0/ . 2 52 .55 .07 . 5/0152 02 53 04 05 06 07 0809 09 5/o o/0 0L . E .S / a p el h r oC &

O p " .-2 . 6 33 . 6 34 .9 65 . 9 /6 . 6 67.758 . 4 86 . 9 29 /99 . / 66 . 6 27 . 6 46 . 2 84.572 . 5 6L 4 1!. /s l-R W . .:o f,u g h 2 / 2 5

0- 2 . 1 1- 2 , 9 4- 3 . 9 6- 4 . 6 0- 5 . 0 6-5.63- 5 . 8 7- 5 . 9 2- 5 . 8 4-535-462- 3 . 7 6- 2 . 8 8-/.9B-/.07- .62!-.lsl02 . 4 1ai-e n d o f

uU0_ 1 0C O 0NI#R

2 0000LPer cent ofchordi. p.LD ClOU0OCN26 032 4 0 2 (kq 2004(lo 6D&0/28(k 8 0 1 0 (C0 4 v.ol

CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WIND

r0a

a,26p2 4 R 2 0k

q20a 40l6 1 6 00 /2 868 0 / O O^- 48

O pC- 4 0 .- 8 u

3 . 5 9ssz4 3 04.43

i o -/0 ^ll.1LIJ_LJJ_J-L11J0 0000 /00Per cent ofchorr( . / /. l0

.4 4032.040.O B1. 836.07k1.63 2 C i8 .061 , 426^ 0 .051.2V.241 m 040L O x .2 0 0 Q . 0 . 3u.0.1600 2Q )o O.6X ./20 1.4'.08.20 40O .2_' 2v "?

- 404- . 42 4 .-N.A.C.A. 2612 airfo il.

o v q744.44%s o3.29zs3/ . 9 733:4 2/31 Ce Afinso fLID

Ic . a,

Airfoil: N.A.C.A.25 / 2. N . : 3 , 0 8 0 , 0 0 0S i z e : 5 " x 3 0 "e G / f l f s e c . : 6 9 . 4P r e s . ( s f n d . o f m ) : 2 1 . 0 D o t e : / 2 - 3 - 3 /W h e r e t e s t e d : L . h t A . L . T e 5 t . , V D . T . 7 2 2Corrected for funne l-wol l effect .

Airfoil:D a t e :CorrectedN . A . C A . 2 5 1 2/2 -3 -3 /e/o inf inite asp e42 1 60 2 4 2 8 3 2n g / e o f o H o c k , a ( d e g r e e s )

FrovaE. . 2 02 460Liff coefficient, C


20/61

Uru0v28

24 lukA 2 0 o0 /6^

.2 /2 uBo

0 4u.o0 yc- 4 0 .U

-B

.44097 // Ss 2.0 .40.O B1 1 2 `L2 B7 537 L B3 6.0 76J[ . R p d . : 4 . e s 1 . 63 2.0 6JPe Ofrod'3Sf C ^o ^ d ^ 'z % s 1 .42 8 - 0 . 0 5va/.2V.24.04C.P.

_4.03.e ^U1.lso020.6'./2 0 /. 4 v.08

C D .204E - . /Uav2 8

2 4 0k4 2 0i

6 0 .0 4wu

18EPORT NATIONAL ADVISORY COMMITTEE FOR AERONAUTICSJ/.4 409S.4008v. 3 6 x . 07.32 0.06V u.26`c 0 .05v aC i .24v N.04

vv .20 $ 4.03um /6 p. 0.02o.u ./20 /k1 . 0 8.0 40-.2uu

m .3i r fo i l. N . A . C . A . 2 5 1 8o _ -4o t e : 9 - 1 9 3 /Correc ted to in f i__4 c2.2 .4 .6 .8 Angle of at tack, a (degrees)i t t coe f fic ieFIGURE 2 B .-N.A.C.A. 2 6 1 8 a i r f o i l.m o /0u ^ 00-/00 20 40 60 BO /00Per centafchord ^/G


21/61

7.4 4

2.0 .40/ .8 .36/ . 6 .32 V/ .4 . 2 8 1v1 . 2 , j . 2 4 ; O ^

vL O x .20 8u.sv. ls^0 0.6X. /2t i ..4 08.2 .04O 0

-.2-.4

-8 -4 O 4 8 12 16 20 24 28 32An g le o f o i t o c k , a (d e g re e s )

Slo.0[252.55. 07. 51 0

/52 02 53040506070809095/0 0

-2.052.663 .951725 . 3 46 . 2 56 6 77 . 2 67.517 . 5 67 . 2 36 . 5 65 . 564.152.341.26Ly

0- 1 . 73- 2 . 37-a/7-a66- 4 0 3- 4 . 4 5- 4 . 6 /-462-4.52-4 .03-3.36-2.56-/.77-.56- .33

u U /0Y o '1 U4 p - / 0 00000C

P e r c e n f o fc h o r d

L.E. Rod.: /.56c ' . 9 -,ofc ho ro r 2 / 3 0

LID c. p.

0

Airf.A.. , N.A.C.A.26t2. N . : 3 1 9 0 , 0 0 0S i z e : 5 " x3 0 "e4( l t lsec. ) :68.4Pre s . (s thdotm):2/ .0W h e r e t e s t e d : L . M . A .L . T e s t : V D T . 7 2 3C o r r e c t e d f o r t u n n e l -w o / l e f f e c tal0uUkOv28 324 1 - 2 (kq20o 4(0 /sD s(o 12u 8(8 0440 4h04C-q tiV-8 CHARACTERISTICS OF AIRFOIL SECTIONS FROM TESTS IN VARIABLE -DENSITY WINDDl0lUOv26 o32402(v

y 0 Q 410 /6 6C

8 (60/a

0 4m.oF x o m z 28.-N.A.C.A. 2612 tWoll.7 .4 42.0 .401.8 .361.6 .32Ci1.4 .28c.W1.2, .24/ .o ' .20.8 m .160 0.6 ./2. 4 ^ . 08.2 .046 t.L 2 5L56 . 07 . 51 0/52 02 5304 05 06 07 09095100804.42U P Y .2 0 42623 . 9 04 . 6 65 . 2 66.136 . 7 37 . / 27367 . 4 37 . 1 36 . 5 25 . 5 72571 . 4 4(113) L ' ^ Y .-17S-240-323- 3 . 7 6- 4 . 1 2-456- 4 . 7 5- 4 . 7 7-4. 67- 4 . 1 8- 3 . 4 7- 2 . 6 / v P /0U i Oh 0-1000000 /CPer cent of d- 1 . 6 7- .8 3- .33- 1 9(-. 3) OL.ERod: / .58.lh o u g h end.(chord: 2/35 1LID c .


22/61

Slo.O/.252.55.07.5to152 0253 0405060080909 5

/00L.E.5 l o p ethroud:hor

LPL,-3.044.135756.%Z 9 09 . 1 59 . 7 49.929 . 9 49.56875Z.134.392.4//.3/1.131Rod.:gh end

-4//0

L'wi-.0-/.07-441-L69-/.66- 4 6 /

- 1 . 5 5- 1 . 7 4-496-2.06-2.05-1.85-/.55

cuv o / 0U tl Uh p -/0000006Per cent ofchord

ofrodius

-1.21- .BS- .50- 3 /( -63 )756

of

LiIL/D c. p.0

A i r fo i l: N . A . C A . 4 2 1 2 R . N : 3 2 4 0 , 0 0 0Siie: 5"x30"e l . ( f / / s e c . ) : 6 8 . /P r e s . ( s Y n d . a fm ) : 2 0 . 9 D o t e : l2 - / 0 - 3 /W h e r e t e l . .. ^ L .M . A . L . T e z t :V D . T . 7 2 9Cor rec ted fo r tunn e l -wo / / e f fec t

L i ft c o e f f% c %- . 4

-6 -4 0 4 8 12 16 20 24 28 32A n g l e o f a t t a c k , o : ( d e g r e e s )Hausa 30.-N.A.C.A. 4 21 2 Ud a l l .

.442.0 .404 8 . 3 61.6 .32

Ci/ .4 . ,?8

Documents

NACA TR 460 the Characteristics of 78 Related Airfoil Sections From Tests in the Variable-Density Wind Tunnel