search.jsp?R=19930090937 2020-06 … › archive › nasa › casi.ntrs.nasa.gov › ...REPORT NO. 628--NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS ao, the section lift-curve slope

NACA-TR-628

REPRODUCED 8Y

NATIONAL TECHNICALINFORMATION SERVICE

U.S. DEPARTMENT 0F COMMERCE

SPRINGFIELD, VA. 2216!

https://ntrs.nasa.gov/search.jsp?R=19930090937 2020-07-20T13:03:49+00:00Z

NOTICE

THIS DOCUMENT HAS BEEN REPRODUCED

FROM THE BEST COPY FURNISHED US BY

THE SPONSORING AGENCY. ALTHOUGH IT

IS RECOGNIZED THAT CERTAIN PORTIONS

ARE ILLEGIBLE_ IT IS BEING RELEASED

IN THE INTEREST OF MAKING AVAILABLE

AS MUCH INFORMATION AS POSSIBLE.

REPORT No. 628

AERODYNAMIC CHARACTERISTICS

OF A LARGE NUMBER OF AIRFOILS TESTED IN THE

VARIABLE-DENSITY WIND TUNNEL

By ROBERT M. PINKERTON and HARRY GREENBERG

Langley Memorial Aeronautical Laboratory

73038--38----1

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

HEADQUARTERS, NAVY BUILDING, WASHINGTON, D. C°

LABORATORIES, LANGLEY FIELD, VA.

Created by act of Congress approved March 3, 1915, for the supervision and direction of the scientific

study of the problems of flight (U. S. Code, Title 50, Sec. 151). Its membership was increased to 15 by

act approved March 2, 1929. The members are appointed by the President, and serve as such without

compensation.

JOSEPH S. AMES, Ph. D., Chairman,

Baltimore, Md.DAVID W. TAYLOR, D. Eng., Vice Chairman,

Washington, D. C.WILLIS RAY GREGG, Sc. D., Chairman, Executive Committee,

Chief, United States Weather Bureau.WILLIAM P. MACCRACKEN, J. D., Vice Chairman, Executive

Committee,

Washington, D. C.CHARLES G. ABBOT, Sc. D.,

Secretary, Smithsonian Institution.LYMAN J. BRIGGS, Ph. D.,

Director, National Bureau of Standards.ARTHUR B. COOK, Rear Admiral, United States Navy,

Chief, Bureau of Aeronautics, Navy Department.HARRY F. GUGGENHEIM, M. A.,

Port Washington, Long Island, N. Y.

SYDNEY M. KRAUS, Captain, United States Navy,

Bureau of Aeronautics, Navy Department.

CHARLES A. LINDBERGH, LL. D.,

New York City.DENIS MULLIGAN, J. S. D.,

Director of Air Commerce, Department of Commerce.AUGUSTINE W. ROBINS, Brigadier General, United States

Army,Chief Matdriel Division, Air Corps, Wright Field,

Dayton, Ohio.

EDWARD P. WARNER, Sc. D.,Greenwich, Conn.

OscAR WESTOVER, Major General,United States Army,

Chief of Air Corps, War Department.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 Ae_'onautieal Laboratory, Langley Field, Va.

JOHN J. IDE, Technical Assistant in Europe, Paris, France

LANGLEY MEMORIAL AERONAUTICAL LABORATORY

LANGLEY FIELD, VA.

Unified conduct, for all agencies, ofscientific research on the fundamental

problems of flight.

II

TECHNICAL COMMITTEES

AERODYNAMICS AIRCRAFT STRUCTURESPOWER PLANTS FOR AIRCRAFT AIRCRAFT ACCIDENTSAIRCRAFT MATERIALS INVENTIONS AND DESIGNS

Coordination of Research Needs of Militwry and Civil Aviation

Preparation of Research Programs

Allocation of Problems

Prevention of Duplication

Consideration of Inventions

OFFICE OF AERONAUTICAL INTELIJGENCE

WASHINGTON, D. C.

Collection, classification, compilation,and dissemination of scientific and tech-

nical information on aeronautics.

REPORT No. 628

AERODYNAMIC CHARACTERISTICS OF A LARGE NUMBER OF AIRFOILS TESTED IN

_[HE VARIABLE-DENSITY WIND TUNNEL

By ROBERT M. PINKERTONand HARRY GREENBERG

SUMMARY

The aerodynamic characteristics o9f a large number o.f

miscellaneous airfoils tested in the variable-density tunnel

have been reduced to a comparable.form and are publishedin this report .for convenient reference. Plots o.f the

standard characteristics are given .for each airfoil and, in

addition, the important characteristics are given in tabularform. Included also is a tabulation o.f important char-

acteristics.for the related airfoils reported in N. A. C. A.

Report No. _60.

This report, in conjunction with N. A. C. A. Report No.610, makes available in comparable and co_venient .form

the aerodynamic data .for airfoils tested in th_'_variable-

density tunnel since January 1, 1931.

INTRODUCTION

A large number of miscellaneous airfoils not included

in the systematic investigations reported in references 1and 2 have been tested in the variable-density tunnel.

The larger part of these airfoils consists of unrelatedsections, tests of which were requested by various

agencies; and the results, except those published in

reference 3, have not heretofore been available in pub-l_shed form. The rest of the airfoils consist of small

groups of related sections tested to study the effects of

certain local variations in shape.

One of these local shape variations involved changes

of the nose shape, consisting primarily of changes of theleading-edge radius. The effects of these changes were

determined by tests of modifications of the GSttingen398 (reference 4), of the Clark Y (reference 5), and of

the N. A. C. A. 2412 (unpublished). References 4 and

5 present data on the effect of sharp leading edges.The modifications to the N. A. C. A. 2412 consisted in

varying the leading-edge radius from normal to zero(N° A. C. A. 2412, ±_o A. C. A. 15, 16, 19, and 20) and

in dropping the leading edge from the normal position(N. A. C. A. 17 and 18). A second local shape variation

involved the rear portion of the airfoil and consisted

in. reflexing the mean line. Such modifications weremade on the GSttingen 398, the Boeing 106, and the

N-60 sections, and the results of the tests were pub-lished in reference 6. A series of related forward-

camber airfoils having reflexed mean lines was tested,

and the results were published in reference 7. Anotherseries of reflexed airfoils, for which the results have not

been published, includes the N. A. C. A. 21, 23, 24, 25,26, and 27 airfoils.

The results of these tests, including both published

and unpublished data, have not heretofore been avail_able in comparable form nor convenient for ready refer-

ence by the user. It has therefore been deemed desir-able to collect these data into one report.

This report, in conjunction with reference 2, makesavailable, in convenient form, comparable data for sec-

tions tested in the variable-density tunnel since Jan-

uary 1, 1931. The important fully corrected character-istics for the miscellaneous sections described earlier and

also for the sections reported in reference 1 are tabulated

for easy reference. In addition to the tabulated data,plots of standard aerodynamic characteristics are pre-sented for the miscellaneous airfoils.

TESTS AND APPARATUS

Routine airfoil tests were made in the variable-density

tunnel at an effective Reynolds Number of approxi-

mately 8,000,000. Tests of some of the models wereextended through the range of negative angles of attack.

Airfoils for which these results were obtained are desig-nated "inverted" sections. The duralumin models were

of rectangular plan form with a 5-inch chord and a

30-inch span. A description of the tunnel, the test

procedure, and the method of constructing the models

is given in reference 8.The precision of the tests and of the results is dis-

cussed in references 1 and 9.

RESULTS

The method chosen to present these results is in-tended to be convenient for designers. The important

characteristics, fully corrected as described in references

9 and 10, are presented in tables I and II and are com-

parable with those given in reference 2. These im-

portant characteristics are:

c_, the section maximum lift coefficient.

a_0, the angle of zero lift.

REPORT NO. 628--NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

ao, the section lift-curve slope.

Czopt, the optimum lift coefficient, or the section

lift coefficient corresponding to c_0m__.

Cdo,,,, the minimum profile-drag coefficient.

cma.c., the pitching-moment coefficient about the

section aerodynamic center.

a.c., the aerodynamic center, or the point, with

respect to the airfoil section, about which

the pitching-moment coefficient tends to

remain constant over the range of lift

coefficients between zero and maximum

lift.

c.p., the position of the center of pressure in

percentage of the chord behind the

leading edge.

m6_ the lift-curve slope for aspect ratio 6.

A more complete description of these characteristics is

presented in references 9 and 10.

Tables I and II contain these data for available

sections tested in the variable-density tunnel, except

those given in reference 2. Reference is made to the

original publication for the airfoil results that have

been previously reported.

Plots of the standard clmracteristics (figs. 1 to 88)

are given for the miscellaneous sections (exclusive of

those for the N. A. C. A. 22112, 23112, 24112, and 25112

sections, which are published in reference 7) because

they are not available elsewhere. Plots for the sections

in table I are given in reference 1.

LANGLEY MEMORIAL AERONAUTICAL LABORATORY_

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS,

LANGLEY FIELD, VA., October 1, 1937.

REFERENCES

1. Jacobs, Eastman N., Ward, Kenneth E., and Pinkerton,

Robert M.: The Characteristics of 78 Related Airfoil Sec-

tions from Tests in the Variable-Density Wind Tunnel

T. R. No. 460, N. A. C. A., 1933.

2. Jacobs, Eastman N., Pinkerton, Robert M., and Greenberg,

Harry: Tests of Related Forward-Camber Airfoils in the

Variable-Density Wind Tunnel. T. R. No. 610, N. A. C.A., 1937.

3. Anderson, Raymond F.: The Aerodynamic Characteristics of

Airfoils at Negative Angles of Attack. T. N. No. 412,N. A. C. A., 1932.

4. Jacobs, Eastman N.: Characteristics of Two Sharp-NosedAirfoils Having Reduced Spinning Tendencies. T.N.

No. 416, N. A. C. A., 1932.

5. Weick, Fred E., and Scudder, Nathan F.: The Effect on

Lift, Drag, and Spinning Characteristics of Sharp LeadingEdges on Airplane Wings. T. N. No. 447, N. A. C. A.,1933.

6. DeFoe, George L.: A Comparison of the AerodynamicCharacteristics of Three Normal and Three Reflexed Air-

foils in the Variable-Density Wind Tunnel T. N. No.

388, N. A. C. A., 1931.

7. Jacobs, Eastman N., and Pinkerton, Robert M.: Tests in the

Variable-Density Wind Tunnel of Related Airfoils Havingthe Maximum Camber Unusually Far Forward. T.R.

No. 537, N. A. C. A., 1935.

8. Jacobs, Eastman N., and Abbott, Ira H.: The N. A. C. A.

Variable-Density Wind Tunnel T. R. No. 416, N. A.

C. A., 1932.

9. Jacobs, Eastman N., and Sherman, Albert: Airfoil Section

Characteristics as Affected by Variations of the ReynoldsNumber. T.R. No. 586, N. A. C. A.. 1937.

10. Jacobs, Eastman N., and Rhode, R. V.: Airfoil SectionCharacteristics as Applied to the Prediction of Air Forces

and Their Distribntion on Wings. T.R. No. 631 N. A.

C. A., 1938.

Roh'o of lift to drog. L_D

C.iO /n percenf of c_ord (from forword end of chord)

qlllIlll

,i

"o ,r__, : ( !

r4-N_ *I

I

o

= _.oment coef., c.....

=_ I 1 t !

= " , II,t 1

I I :

Q I I

"iX _ "_ ¢_

q" _: "1

//,, iF

-I

,ILift coeff/cien/, C_

Dr'oq coeff/c/enf, C_

Profile-alto9 coeff/cieni, C.o

....... •_ _

i' ii \

I I_ \i I_ _,I I I_,bY- 'i i

_",_' [_L

J i

\

/

-,.._: I I ,-

_¢ , , I II t ,

Angle of otiock for znf/nzYe ospecf folio, do (deg.)

Roh'o ol r Hit io drag. LCD

I _ " o3

c.p./n percenf of chord(from forword end of chord)

Momen/ coe£, c==.o.

4 REPORT NO. 628--NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

[ Sta. l r. L'w'r

I _21 2.92z25 _Ol /.eoI 25 _7 1.42

5.01 l/ 1.00

7.51 t21 '2

_oI ,,, _2r4 !620 I/ )0 22 _ _ I VO )2

40)/ 71 .o050 I r7) .02601 )G I .08

701 rbl .1780 I 31 .309n I 81 .45951 41 .53

/OO I '_1 ,87

L.E.Rod:O.97-T.E. Rad.: .25

r

?

!i

I 0 0I A/rfo//.'Boelng 103A.R.N: 3,170,000

/ I S/ze:S"x30" Vel. (ff/sec.): 68. 6/ , Press.(sfhd. aim.):21./,Dofe:/O-20-3

1_2

_' Where fesfed: L.MZA./_.,Test:V.DT. 707' Correcfed -.4

-8-4 0 4 8 /2 /G eO 24 28

Angle of ailack, (x (deq.)

//

E2

_ o_0 @ i

f O.O05e ahead of el4 _ :_, .... .05e above cho'rd I -8

-.3 -- /03A -_ :V. DE 707 -/2_,370,000.

-- Corrected fo ro/[o

LiFt coefFzbien_.C,o

FIGURE 3.--Boeing 103 k airfoil.

h,,0

28_- o

e4_ 20_

_. zo _ 4oF

b'

-!i2

Doeimg 103 A O'nver_.),_._..3,/ 2gH Size:5 "x30" Vel. (ff/sec,): 68. 7

t Press.(sthd. aim.):20.8, Dote:/O-21-3/Where fester: /.M.A. L, Te_f..V.D,E709Corrected for tunnel-wall effec_

0 4 8 12 16 ZO 24 28Angle of arrack, _ {de_.)

-- -- 2.4 .48

-- -- 2.2 .44

- - 2.04oi

- q- _ /.e .3s

i 1.4_2.28 @

-

-- _ b

_ _ .2 .oe

-.2

-.4

FIGURE 4.--Boeing 103 A airfoil (inverted).

.Boeing 103Ab"nverfed) Tesf: E D. T. 709Dofe:/O-Z/-3/, R.N. :(effecfive) 8,400,000 -/2Correcfed fo /'nf/_ife r_h'o

-4 =2 0 .2 .4 .6 .8 ZO 12 24 ZG 1846

L/fl coefficient,C,o

(6a/_) op "o.qoJ 7_ad_o a#ugu+ Joj ¥_D/4 D _o al_uV

° lu o_ a/

=_,_.

lililI" I" i" i"

°'°_o "_ao_ luamo/#

(z0 "tua/Rg./aoo &DJO

70 "/ua/_../Jtao_ ,tJ!7

_. _ • " i° i"

,t , I I .....

...... .... :_ _- - -c ..... _- _. _:______ I I [ I I /I_----r------_ -_ _ ,_.Jl-¢,_

......... "_ i _ _ '_ _ "_ " .__ __ _ ._ ,e_ _.

.......... _ _, ,\ _ _._

....... " - :. ÷----/-'_Z --- _- i "_----_ .... _--7--- <_-_ ,_

....... -7 --k ..... _ --i- _ ;_'_ _.-- , , _- - _---_t _ '_

-- I 1 '

(pJOt../3 JO pu9 pJOhlJO.,J IJJOJJ) pJOLI3 .,.lo/u_,DJad u/"d'a,_ ._ |

(7_'7 '6oJp Ot /J!l Jo o_/D,y

OO'_, ¢J

C3

.g

.o

oor3h..o

?

?


L' V'I

)81 E 9_!61 / 5,41 tie `

o,

'21 64 Percent of Chord

]

4_s,_-_,,x_o.W_.:Z_;e'c():_°I Press.(slHd atm.):ZO. #,Dote: 3-2g-3/

I Where fested:L.M.A.L.,Test:V.DT538

I ICorrecfed for tunne/-wo//effecl

i .,.G.'C

l

4 I2 20 4O 6O 80 /00

2.4 .48

2.,2 .44

2.0 .40

1.8 .36

1.8 .32

/.4_.28¢

,.2_.24

88 m 8

.G"J .12c_

.4 .08

.2 .04

0 0

-.4

0 4 8 /2 /G 20 24 28

Angle of o/tack, _¢ ('deg.)

.026

.024

.022

.020

_.018

i_'°/G

.014u

.012

_,.o/o

_ .008<

.008

•O04

.002

0

4_ -.I

8 -.2

-.j_

FIGURE 7.--Boeing 106 R airfoil.

I I i

r,_8

44

4o'_

36"_

32.6.p.

/ _, e_

/ 2o b

"IL• 12 "_

_ _" .., __ 8<u

:: _ _ " " O_

_003 e _heO d Of C/4 l -4

1i I -8

__iAirfoil:BoeinglOGR Test:V,i ,T,538Oate:3-2G-3/, /?.At..'(effecfive) 8,320,000

-- ---- Corr, ected fo /nf/_He,ospect cah'o

-2 0 .2 .4 .# .8 ZO L2 Z4 Z6 Z6

Lift coefficient. C,o

L v>

6

-I tO-1 52-_ 24-2 _2-2 iB-2 ;'6,-2 77,

-2 _1;-2 )9;"2 )5(._ tO("2 'B _.

l_ ;6(

'2, :B:"2, '4. _'2. O_

I. 3."

/. 4_/. 31

• O_0

P.,

I/23

/

Z_A/_fo//."Boeing III R._.'_,950,000Size:S"x30" VeL (ff/_ec): 70.7Pre_.(sfHd ate) :fO.8.Dofe=I-4-33¥Ie fesfed:i.M.A.L..Test=V.DT539

Corrected for lunne/-wo/l effecl

0 4 8 12 IG 20 24 28

Angle of of/ack. _ (deq.)

!_ I̧) 20 40 GO 80 /00

Percen! o f chord I'

2.2 .44

1.6 .32

.4_.28¢

LZ Vil'kl,. =4

'.2

-.4

.026

.024

.022

,020

.018

.G .OIG

_.014OU

I_IeURE 8,--Boeing 111 airfoil•

Z4 Z6 28

CHARACTERISTICS OF AIRFOILS TESTED IN THE VARIABLE-DENSITY TUNNEL

.4 .08

.2 .04

0 0

Correcfed for iunne/-woll effecl " -.4

0 4 8 12 16 20 Z4 2B 32

Angle oir oHock, _ (deg.)Fious¢ 9.--Boeing 111airfoil (inverted).

--_o_ ___o_

°-_°o_ _o_a-ao 8o ,ooPercemf o f chord

2.4 .48

2.2 .44

2,0 .40

1.8 .36

1.8 .32

1.4_.28_

2 g.249J , _

,o_.2o_oa

8U.l_

.6 "a .12_

.4 .08

.2 .04

,_,_ 0 0

A/rfoi/." Boeing 112 R.AZ.."3, I00, 000Vel. (ff /sec.): 68.9_ -.2

Dale:i-3-33

Where fesfe Tes/:V.DT. _38Correcfed for funnel-woll effecf -.4

0 4 8 /2 /6 20 24 28

Angle of ol/ock, oz (deq.)

• 022

i

o.008

Correcfed fo

-2 0 .2 .4 .6 .8 lO L2 L4 LG

L/F/ coefffcienl, c,o

_3068----38_2

7

F_GURZ10.--Boeing 112 airfoil.

II

I .

i

I

Lift coeff/cien;_• . . • .

Drag coefficient, C_

O0

Ang/e of aHack for /nf/nHe asp.ect folio, _to (dec].)


28_ 0 -- --+--0

24_2o - --

_.zo__ 4oi,1_ ----_Is_eol

.2 e I _

- ] _

-8

4

_2.4 .48

2.2 .44

2.0 ,40

1.8 .36

... _/.4_.28¢

5/korsky GS-M{inv'rf_._R.N: 3`/ 40,000

Size:5"x30" Vel. (ff/_ec.): 69.5 .-.2Press.(sfhd. aim.}:20,4, Dote:/I-3-33Where _esled: L:M A.L., Tesh V.D.E/083

"Corrected for /unnel-wo/I effect -.4

8 12 16 20 24 28 32 3GAnqle of oftack, _ (dog.)

9

.020

#.018

..OIG.tj

_ .0140

•004

.002

FIGURE 13.--Sikorsky GS-M airfoil (inverted).

0.004C oheod of c/4_.04c chord _v 1 I

GS-I Tesf: V.O.71./08¢

•Dole:ll-6-33, 8,340, 000-/2

Correcied lo osp,ecf _oh'o 18./G0 .2 .4 .6 .8 lO L2 L4 LG .

Lif/ coeff/cien/. C,o

I [ i I [/

_.;VTFI l-

g_ It.*._S_ b[

l

Ro/_b of hYl /o drag. Z,X_

C.p. Ib percel_Y Of chord (frofn fOFWOFd efld of chord)

.... J ' --T- _ +-: ; I I

Z_fi-k_lfi- -*-14 LJ !_ ]L_

, .. . .-- .-. ._ ._ ._ 6_

L/f/ coe_'c,'en4

° , , , , _____

-t---+

AnfT/e of o_tock for t'_'_//e ospec_ rot/b, ot_ (de9.)

!

i i 1 i

i [ i i

_. __

INg

'.4

m

N"

p_u_4

'11

_ _tFXX

_, _ _____

Rof/o of fie/o _-o_, _/DI

e.p./n percent of chord(from forword end of chord).

2 : t

:. b

\l t', )

?i" i'- Z

1

." > .'- >. N N ._

L/f/ coe/h'c/en/ Q

oa,Oro_l coeff/c/enl, C_

I

II

• /omen/coef., c..... Pro_/e-dro_ co.effl'cient,, ce_ .

I I .|

- -ll_ _ _

c : i: -\ X

_. 7_ I

i i

w

-- m

m 1

©

_Zp

T_Z

Ang/e of ofock for /nf/n_Te ospect r_t/o, o/_ (deg.)

0

03©

m

--

--_

_0

- _©

S

CHARACTERISTICS OF AIRFOILS TESTED IN THE VARIABLE-DENSITY TUNNEL11

E2

.G .8 LO L2 L4 16 L8L/f/coef#'cien/. C,o

Dale:/O-8-31.R.N..(effeciive)8.060,000Correcled fo /n#'mife,ospecl_,aY/O, -16

0 .2 .4 .6 .8 LO L2 L4 Lg L8L/f� coeff/'cien_, C,o


.006

.004

.002

i

L

A/_Fo//:U._.A.35-A. R.AZ.:3,/80,000.S/ze:S"x30" Ve/. (ff./5ec.):68.4Press.(sfnd atm.):20.8,Dofe: 3-2-32Where tesfed:L.MA.L.,Tesf:V.D.T.769

for funne/-wa// effecf

-8-4 0 4 8 12 /G 20 24 28Angle of oilock,_, (dec].)

FIOURE 20.--U. S. A, 35-A airfoil,

4o_

_2_

i, 1

i : L.' 7--

T C-_

-_ -_ _

--+- -_

-f 5 -/eDate:3-2-32, ,R.N..'(effech've) _2,420,00

-.4L Correcled /o/n_'ni/easpect ra//o-.4 -.2 0 .2 .4 .6 .8 LO L2 L4 /,G L816

L/f/ coefffcien_, e_,,

../

CHARACTERISTICS OF AIRFOILS TESTED IN _ THE VARIABLE-DENSITY TUNNEL 13

FIGURE 21.--U. S. %. 35-B airfoil.

_-_-_-_-1 . . _2._ " 4 _.0/8

.... G .016

-_ - - /.s .3_ _.o/4_OlZ

l t

--_ _ /. 4.._ 28..__, .OlO

F-- ' '_4__o _o.oo_

t .004

oo,_ _ ,

•_ 8alOOF-+-+

_ 'W -.I0 -.e--+ 5 "_

--4 Ai -t "..U.S'.35B(/nv'_IE)R.N..3,'/;_O06 8 -.Z

--_ _ _ _ S/ze:S"x30" Ve/.(fl./sec.):69.1 "__4

' ' Press.(sfhd.alm.):aO.G,Oafe:/O./O-31 --2

" -8 _ --_ _--Wherelesfed..L.MA.L, Tesf_V.D.E_7 _ -"

-8 -4 0 4 8 /2 16 20 24 28

Angle of aHock, _ (deg.)

a

O, OIJ c ahead of _

.05c

I

! ,I '

ii

i

52

48

44

4o_

36,-..

sz•g

_8._

_o_

'_/2 ._-

L

b

b

-4_

-8

FIGUR_ 22.--U. S, A. 35-B airfoil (inverted)•

b: Z,).7 692 _/2-- "Date:/O-/O-3/, R.AZ..'(effecHve)8,280.O00 !-- Corrected to 1Hf/J_ifeaspecf folio

-4 -2 0 .2 .4 .6 .8 ZO 1.2 L4 /.G L816

Liff coefft'cien_,C_o

14 REPORT NO. 628---NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

IIII II IIIIIII I

,20 40 60 80 I00 .022

Percent of chord

ii 2.4 .48 .020

' 2.2 .44 ¢.018

izo .4o :G'OiG

./r /.8 .36

1.6 .32 u/. 4_._.26 _

i

C, _, _ .008:.20_.

.16 u.004

ii ./2,_ ,oo_.o.4 ,08

t _ oi _1 .2 .04

Al'rfoi/." C-G2 R.AZ: 3,/80,000

S/ze:S"x30" Ve/.(fl./sec.):GS.7 --.2Press.(sthd. elm.): 20.SJ)afe :3-20-3/Where tesfed:L.MA.L..TeshV.DT 528Corrected for tunne/-wo/l effecf -.4

0 4 8 12 16 20 24 28

Anqle of oltock, oe (deq.)

FIGURE 2-3.--0-62 airfoil.

i

20 40 6O 80

Percenl of chord

"li 2.2 ..4.4

.40

/.8 .36

" 1.6 .32

1_ /.4_.28_

.16 u

)

: .2 .04

0 0Airfoil: C-72 R.N..: 3,020,000

5/ze:S"x30" Vel. (ft./sec.): 69.9 . ".2Press.(sfhd. alm.):21.O,De#e:3-20-31Where fesfed: L./vLA.L, Tesh V.D.T.SZ9

for funnel-wo// effect -.4

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

An_le oFaitack, o_ (dec].)

L

_ .008

•006

•O04

FIGURE 24.--C-79 airfoil.

I i°___ 0006C oheed of c/4

.04c obove chord

I

I '

i I

iI I

I

iI

I

II

I

i ii

, !Airfoil." C-G2 Tesf: V.D 7:. 528 _/2:Dale: 3-_0-3/, R.N..'(effeci/ve) _,400,000

Corrected to /_f/nile rof/o 16-.4 -.2 0 .2 .4 .6 .8 LO L2 L4 L6 L

Lifl coeffYcien/; qo

IiIii

\

Airfo/l: C-72

I t

I

ITesf _V.D 71529

IS2

48

44

4o_.

36"_

3z.geo_

24_

, /61_

i

-4 _

-8

-12Date:3-20-3�, R.N...(effective) 7,080,000Correcled to /nh'nile ospec¢ rah'o

0 .2 .4 .6 .8 LO L2 L4 /,6 L6TI6

LIH coeffYc/enff. C_o

CHARACTERISTICS OF AIRFOILS TESTED IN THE VARIABLE-DENSITY TUNNEL'15

.02G

.024

.022

.020

#.o/8

.004

_p : .2 .04

, , o

!:5"x30" Vel.(fi./sec.):69.G _.2_.I

Where fesfed: LMA.L.,Tesf:V.DT, 637 4

-8 -4 0 4 8 12 16 20 24 28Angle of oHock, _ (deq.)

FIGURE 25.--0--72 airfoil (inverted).

52

48

44

8 -.2--

R.N..'(effecfive) 8,130,000 -16Corrected fo /n_'nife ospect f-Git'o-.4 -.2 0 .2 .4 .G .8 ZO L2 L4 Zg L8

L/ffcoefF/c/enl,c,o

78068---38----_3

52

48

44

FIGURE 20.--C-80 airfoil.


O, 4 8 /2 16 20 24 28Angle orallack,e_ (deq.)

0 4 8 12 /6 20 24 28Anqle of aflock,e_ (dec].)

.4 .08

.2 .O4

0 0

-2

.02G

,024

.022

.02O

°.018

:_.016

.014

t

_ .008.006

•O04

.002

FIaUR_. 27.--0-80 airfoil (inverted).

.02G

.024

.022.48

.020

.44 #,_.018

.40

/.8 .36

_._1.8 .32 u

1.4_.28_

.2 .4 .6 .8 lO 12 1.4 /.G /.8Lif/ coeff:cien/, Cto

CHARACTERISTICS OF AIRFOILS TESTED IN THE VARIABLE-DENSITY TUNNEL 17

Airfoi/: AI-22 0"nverled), Tesf : V.D.T.E38Date: 7"23-3L R.AL:(effecfive)8./O0,O00 -/Z

Correcfed to/nf/bHe ospe_f folio 160 .2 .4 .R .8 ZO L2 Z4 L6 L8

Lift coefffc/'en_, c,o

2.0 .40

1.8 .36

1.6 .32

/.4_2.28_

i.z4. .20_

0,U

b_z

J.,2_

.4 .08

.2 ,04

0 0

.OO6

•O04

0 .2 .4 .G .8 ZO L2 Z4 /.6

LiH coefFcien_,C,o


(3

"b

28"_ 0

24 _ 20

_e_eo

2,z_8oo%1oo

.0

_'o_

-8

2 0

•:'-'. : 1.5,ol ;,ill :"7Y.'. _..6' ' "2 tl

,_ _.4 :_ :s20 7.7. )S0

L0 4o I

,',u_ _t.6 t__ l 9.1;I -3 6

_01 I.OiII "7 I0

-2 20 40 60 80 I00

- _-t2.4 .48............ i "

r : 2.0 ,40

..... ---........ t--------/'8 .36

"_ _S I .S I I " , :7

_001 ) 0 _ ..... --r-- --I .....

L.E. Rod:O.4S _ .... --].-.-L

T.E.R_d.:I_,I_ " l [ _ .... "

.... C, 2. -- -_ ....

._,s_eo -, .... " _-_< '- -i -- -_......-, ........

_ - ./ .... ±_8 o I00 -- _-- --

_. _ _- =-b'4S_q-- 4c_--- _._-_ o _. -_ = "-_"_ _ =-J- - -J--q-- -J- --

._ _L _ / A/_foif." N-68 R.N.:3,070,O00

_A _" __ M _ S/ze:S"x30" VeL (ff/sec.): 70.0= _ I f Press.(sfhd.afm.):20.E, Oofe:8-1G-3Z -.2

8 - _ ---- Where fesfed:LM.A.L.,Test:V.Dr868- -V Z Z-Correc#ed for funnel-wo/leffecf_ -.4

-8-, 0 4 8 12 IG 20 24 28

Ang/e of oileck, _ {deg.)

1.8 .3_

1.4_.28_

'.2 __.24

._ ,ti

._ .2o_

•G "J.12_

.4 .O8

._ .04

o

•02G E2

48

.022 44

.ozo 4o_

_°.018 36"-"

._ .016 32_,.

.006 12 _L

.004 8_U

b

_ o o_

8 -m -- -8

Correcled fo(G

-4 -2 0 .2 .4 .6 .8 lO Z2 Z4 ZG Z8

Lifl coefF/cien/,C,o

FIeURE _2.--N-68 airfoil.

CHARACTERISTICS OF AIRFOILS TESTED IN THE VARIABLE-DENSITY TUNNEL I9

0

28_ 0

24_ 20 .

_zo _ 4o I

_6_ 6oI

_ 8_o,oo

.0

-O

24 _ 20

_ 20 _ 40

,2 8o

_ o._

-O

st°l Jp:t L',

.751 .92 - _0lOOI 1.0_ "l )6

'[_1¢:N;:I ,_'°S.OI 2.52 -2 ;0

7.51 3.0 7 -3 }7

I,.,20 I ¢.7 -4 _9

40 I _.4 r7SO I _.2 ) I IS ?060 I #.5 t I "4 ;7"tO I Y.G ' I -3 ;17

801 _..6 _ "2 _2901 1.4;I -/ L,¢951 .8 _ I • tO

I00 J 2 0

L.E. Rod.: O.3ET.E.RGd.:O,/3

/jf

/__ _._ __ __

-8 -4

ii

I

20

0

-%

!, I

I20 40 GO 80 IOOPercen! of chord

2.4 .48

! I 2.2 .44

, _ 2.0 .40

1.8 .36

/.G .32

/

II

Ai_foi/." N-69 R.N.:3,070,O005iz.e:5"x30" Ve/. (ff./_ec.): 70.1Pre_s.(sfhd. atm.): ZO.5,Do/e : 8-17-32Where fesfed: LM.A.L.,Te__I:V.D.T 869Correcfed for tunne/-woH effecf

: ] _.+e.zse,

: I _" _ _-',t 1.2_.24_N c, _ - . 2o

' 1

]\

I

0 ,¢ 8 I_ I6 20 24 28

An_le of o/lack, _x (deq)

.4 .08

.2 .04

"_ o

-.2

%4

.02G

.024

.022

.020

_.018

_ .0140IJ

.OOG

• 004

.002

FZOURZ 33.--N-89 airfoil.

Corrected fo

0 .2 .4 .G .8 1.O

Lift coeff/cien_. C,o

!

4

L-8

_.s,1.21.5

1.82.1g.4g.63.4_1

4,6S,4

6.,_ 4 _

3,/

g+__

=e

,OO6

• O04

.002

FIGU_Z 34.--N-71 airfoil.

N'71Dale: 11-2-3_, R.N.."Correc/ed fo

0 .2 .4 .G .8 LO

L/F/ coefficient, C++

L2

52

20 REPORT NO. 628----NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

-8 -4

.4 .08

.2 .04

0 0

Vel. (fl./sec.): 69. 4Pre$s.($thd.olm.)..ZO.d.Oofe: 11-2-33 -.2.

.02G

.024

.022

.020

_.018

:_.o/s

_.0140U

!52

i

0

.006

.004

.002

Corrected to roHo

.40

"/.8 .36

1.6 .32

_S/ze:E"x30" VeL (ff./sec.): 70.9 -.2Press.(sfh_. afrn.):ZO.g,Where fesfed: L.M.A.L.•Corrected For tumnel-woHeffect -.4

Angle of aftacl_,_. (dec].)

.OZG

.024

.022

.02o

.Ol8

:_.o/s

_ .014

8

Dote: 7-17-34, R.N .'(effecHve) 7,920,000Corrected to/nf/nHe d_p. ecf ratio

-.4 -._ 0 ._ .4 .R .8 /.0 L2 /,4 /.G L8

Lift coeff_'cient, C,o

F]OURX 36.--N-75 airfoil.

E2

24 u

Roh'o of lif! Io drog. L//D

c.p./n percent of chord (from forword end of chord)

-t I4-

-+.

Ro/io of lift fo dragoL//D

c.p./n percenf of chord(from forward end of chord)

*----4-----_ "-+---'_"


-- m

m

m

m

m

m

m

m

m

m

m

t-

t-+l.

+.--

4---

LI

t1-+---

4-"-

A/rFo//:AI-TR_vPI_), R.N:3,030.O00

FSize:S"x30" V_/. (fi,/sec._" 70.8 .

Press.(sthd, atm.):ZO.I, Date: 7-20"34

Where tesfed= LMA.L., Tesh V.D.E I158

Corrected for" tunnel-wa//effect

0 4 8 12 16 20 24 28

Angle of aHack, e_ (deq.)

FIGURm 39.--N-76 airfoil (inverted).

R.N.:3,180,O00Size:S"x30" Ve/.(ft./see.): G9.0 _Press.(sfhd. afm.) :ZO.£Oate : 1-23-35Where lasted: L.MA.L..Test:V.DE1213Corrected fortun,ne/-,walle,ffecf

0 4 8 12 IG 20 24 28Angle of (Htack,o_ (dec].)

.4 .08

.2 .04

0 O

%2

-,4

.02G

.022

.ozo

i

.006

•O0 4

.002

FIGURZ 40.--N-80 airfoil.

:Date: 7"20"34Corrected

0 .2 .4 .6 .8 ZO L2 /.4 ZG 18Lift coeff/cien_, e,,

52

Tesf: V.D T.12/3 -/2Dale: 1-23-35,R.N :(effective)8,400,000

Correcled to �mr�nile aspecf ratio •0 .2 .4 .G .8 lO12'_14 "ZG L816

Lift coeff[cl'en_,,c_

/


AicfoH." N-80(inver/ed) Tesf : V.D 7:.121-£Do/e: l'2E'3E, R./¢ .'(effech've) 8,540,000Correc/ed to /nf/nife ospec/ cot/o

:_-'4-4-.2 0 .2 .4 .6 .8 ZO Z2 Z4 Z6 L8

Lift coefEcv_n/, C,o

FIouRz 41.--N-80 airfoil (inverted).

.022

.48•020

2.2 .44 _.018

.4o ._- .016

1.8 .36&O _4

0

1.6 .32 u

/.4_.28_i

_ .008

.006

•O04

.OO2

.

i

IiI

II

I

I

II

I

0.002c ahead of c/4.05c obove chord

A/_foil." N-81Dole: 1-24"33 R./¢:(effeclive)8,500,000Correcled /o/nfzhile o_pecf roho

._ .'J: .20_

G

.16 u

b1.12c_

.4 .08

.2 .04

- --_ff 0 0__ __ A/rfoil: N-81 fl.N...3,220,O00

" L.s,'=e:6"×3o" Vel.(fZ/sec.):68.4....... [Press.(slhd c#m.):ZO._.Dofe: 1-24"35 -.2

--- IWhere tesfed:LMA.L,_esf:VO.Y./214-- --- [Corrected for funne/-woff effecf 1[_.4

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

Angle of oI/eck, o_ (deg.)

73068--38------4

FmuR_ 42.--N-81 airfoil.


%.(3

28_ 0

Z4_ 20

16_ 60

/2_ u 80

e% ,oo

.0

_o_ _--4 _ -

-8

4...0

28_ 0

24_ 20

_s_ so

O_olOO

-4 _,

-8

T

f - z.4 .48

ILL 2.0 .40

1.6 .32

/.4_.28¢

]12_ 24 __ • .Qj. .,_

i I ,_ ,U

.6_.12_

.4 .08

..AirFoil IV _. " 0 0

_ _ _ _Size: 5"x30" Vel. (ft./sec.): 68.5 ._- L Press.(sf}_d.alm.) :20.7,Dafe: l'26-35 ,-'2

-- F -- iWher'e tested: Z.MA.L., Tesh V.O..EIZI6

[-8 L_ LCorrecfed for tunnel-wall effect -.4- -4 0 # 8 12 16 20 24 28

Angle of offack. (X (deg.)

-8 -4

tp'- ' L'v ,'_.

3. _ol 3.:o6._SI I. [07.l ;5 I 1._59..;01 .;5O.,15l . _,5

_::',_1"°)0

FIGURE 43.--N-81 airfoil (inverted),

•02G

4. 'tOI .)05.1 l_TI .._04.1tOI ,_0

3., Igl .tSI.,rRI ._08.,_01 . IE8. _ ._03.'_1 . t5

I. '_ I , 25

."1 0

_. :0

o_111I."a.¢. --_.,olIIIIIIII Ie..,oliiiiiiii I

• o zo _o _o 80 _opPercent of chord

i

q

' p. _o_ L

f u_

2.4 .48

2.2 .44

2.0 .40

/.8 .36

I.G .32

• _:24_

l i:b, :_.V_. .20_

(3 (3

.8u.16u

.G"J .12_

.4 .08

•004

c.D._ / /

//_%.I ,f /

// _z /" /'k

/ i/ / ",

t

_ _ _ A/r-toil: G6##. 387 R.N.:3,1aQO00 0 0

: _/ze.'S"x30" Ve/.(ff./_ec.):68.S --.2: Pr'ess.(sthd. elrn.):ZZO, Dote:4-ZS-32

Where fested: LMA.L.Test:V.D.T. 829' Corrected for tunne/-waffeffecf --.4

0 4 8 /2 16 20 24 2'8

Angle of altack, a (deg.)

FIGURE 44.--G6ttingen 387 airfoil.

O.O07e ahead of c/4.04c above chord

qq

IIt

rest:V.D.r. 829

_8I

I140_

tes__4_

U .#b

-4 _

-8

Oa/e:4"25"32,R.AZ.:(effect/'ve)_400,O00 -/2

Correc_ed to/'ntTnite, a$p, ecf ratio0 .2 .4 ._ .8 ZO L2 L4 ZG 1.816

Lift coeffYcien_, C,o


-8 -4

25

20 40 GO

i JJ:.20_

.16 u

.12_

.Z .04

0 0

VeX, ..2

Where fesfed: L.MA.L.,Tesf :V.DT.£24Correc/ed for funne/-wo// effecf -.4

0 4 8 12 /6 20 24 28

Angle of ailack, et (dec].)

•022

• 020

d.om

. .016.(j

_ .014

8

i

.004

.002

QJ

8

-.3

FIGURE 45.--G6ttingen 898 airfoil•

;/_ 48

44

40_

72.(_

e8

12"_

(j

b

o_

-8

At_-foi/:Gb'Hinqen398 Tesf:V.D.T. 524 -/2

Da_e:3-/8"31, R.N.:(effective)8,II0,000Correcled fo /nf/nife o$pecf t-olt'o

.... _-/6O- .2 .4 .6" .8 LO L2 L4 Lg .8

Lift coefffcien_, C,o

-8 -4

2.4 .48

2.2 .44

2.0 .40

1.8 .36

1.6 .32

/.4_.28¢

.24._._J

.20_

b_

.12_

.4 .08

•2 .04

0 0GB/tinqen 338(/n v'r_l)R.N: 3,090.0005/ze:5"x3,0" VeL(ft./.sec.).'69.7Press.(sfhd.aim.):206, Dafe: 7-24-31 -" 2Where fesfed: L.M A.L., Tesf:I,(D..'E.63_9

Ced for tunnel- wall effecf -4

0 4 8 IZ 16 20 24 28

Anq/e of arrack, (_ (deq.)

•Odg

.024

•022

•020

#.om

_.016

_ .0140U

FIGURE 46.--Oi_ttingen 398 airfoil (inverted).

26 REPORT NO. 628---NATIONAL ADVISORY COMMITTEE FOR AERONAUTIC_

0 3.2Z2. 4.42.'. 5.6

5.t 7.77.: 9.5I( 0.4/._ 1.52( 2.6

"3( 3.54( 3.15( 2. I6( 0._"

7( 8.48( 6.C

0 9( 3.5

I0( .4%.0

28 _ 0

24 _ 20

_/e_ 6o

2le_8oe_o,oo :

.o _ i,_o

-8

2£L',,_I ._ III1[_--3.,61 $_/c _1 I I m.c. "--",_:_Ol_ Cltllllll"j j

?4 ) 20 40 GO 80 I00

76 Percenl 0 f chord

_o 2.4 .48•t51

_z 2.2 .44_6_.812 2.0 .40I

O, / /.8 .36i i

'' I /._ .32I: i

, i/.,_.28C

, 11.2 _ .24C,, _-

: ' • (3 0

: N_ .IG_

,7 \ _.12&

"/" .2 .04

" --T b oA)rFoH:G6H/ngen388-A,R.N..3,1_O,O00 l

_/'ze: S"x30" VeX(fl./sec): 68• 6 J_ 2Press.(sthd. a/m.) :ZO.8.Dote: /0"31-3/I "Where feste d: L.,44.A.L.,Test: P/D7?713ICorrected for funne/-woll effec,f ]-.4

0 4 8 12 16 20 24 28Angle of attack,o_ (deg)

I1 .¢

/"N

\

•Od6

FIGURE 47.--GSttingen 898-A airfoil•

b2

0 .2 .4 .G .8 iO Z2 /4 16 18L/H coeff/c/en_,C_o

48

44

/G

,.'_,'_.1 _ e__;,g §_,o/" _ .,clllllll I I', -o eo _o _o 8o /00

7 Percen / o f chord.,IO I

_I

t4 F-

o.,!,i, !

Ii

il

i ....

i

' ti

i/

!W

_v,

: /./

, I ,A/r'foil:GbYtingen358_B,R._:3,270,OO0,_/ze.'S"x30" Vel. (ft./see.): _Z6Press.(sfHd. atn'z):2/.2, Dote :11-2-31

_-- -- Where Iesfed:L./PZA.L.,Tes/:V.DT.714i

I-- -- Correcled,, fo,_funne/-wo//effeci,, ,-8-4 0 4 8 12 16 20 24 28

Angle ofo//_c/_,o_ (deg.)

2.4 .48

2.2 .44

i/

/

",,.,

2.0 .40

/.8 .36

1.8 .32

/.4_.28_

.e_.z4.g

.OK .20_

2 /s_.6 _ .12_

.4 .08

.2 .04

"b o

-,4

•026

.024

•022

48

44

•020

J.o/8

i_ .016

_ .0140U

.004

•002

FtGUBE 48.--Giittingen 398-B airfoil.

l

I

o"hqo

q

Rahb of liftto drag,LIDl

Oa r_ o_ C_ oa

c.p./npercent of chord(from forward end of chord)

\\ iI

/I x.

/

}-,,

, ___

\

fIi

I I

.L/ff.coeff/cient, C_

grog coeFh'c/en4 C_

Percentof chord

13 ....

E_-- _-

Moment coef., c ..... Pro_'/e-drog coef_/cient, c_

_. "_ "_ "_ _ "_ "_ ._. "_ "_ "_ "_ "_._._. co r_ _ c_ _ _ _ e6 _ _ _ _ _ "J "_ "_ F

"i/ f8. 4-c_c_

Angle of ollock for znf/n/'/e ospect rob'o, do (deg.)

Rol/o of lift to drag_ LIDI

c.p./n percent of chord(from forward end of chord)

I-+-

T

-+- -_-

_c4.-

-+-

T

-4-

C_e_cb_b_u_t_'_ I

-T_ _ _ of chord

_._ •

> ." _FD % _I I _. ._

Lift coeff/c/ent,C._

brog coefHc/ent,C_

• Pro F_le-drog coeihcient, _o

I/L"

' I

, I II

/ II

An_le of oHock for /nf/nffe aspect rot/o, do (deg.)

CJ

©

£t_

t_

e

-28 REPORT NO. 628---NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

8.0,zl '5110.7.

2 5 112.21Oil&&

I_.11I ¢7.51

2 e. ¢8.3d50118.7',4 3 II7.9_

9 I/6.3160113.9{

9 [10.94_ 91 7.4,. .65

_01 3.7( .55

4G_ 551 1.84 .40

4. 1C3 I .1( O

° I

_. ,' [28 _ 0 :'

4o i

UW'," ,_

8.053.254.40 L

3.302.501.8Sl.O0.40.00

.I0

.35

.S&•75

7

io I_Ht-Fq _.-.-_.. ]]

,oll[lllI I I I.,olIllllI I i ]" 0 gO 40 80 80 /00

Percent of chord

i 2.4 .48'22! . .44

i

/ ¢:// i

//

8 olool__ii /_ 4§ #A I I,, _ "I--

if'i"10 I IA/rf°"l.'¢6#l'nqen4ZO. n.AZ.'3.1ZO.O00

-4" I_!!! J_JS/ze:E"x30" Ve/.(f_lsec.):63.61 I Press.(stnd. otm.).'ZO.4, Dote: 3-28-3/

_Where tested: L.MA.L.Test. VD.T £#I

-8 ] l iCorrecfed for tunne/-wo//effecf "

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

Ang/e oroilac& _ {dog.)

__.0 .40

/.8 .36

1.8 .32

_]1.4_m8_

:,3 :_

Q 0

L8 .IS ].G'J.12c_

.4 .08

._ .04

0 0

-.4

.02G

.022

•020

.018

:_.016

_u .014

i

_ .008

.006

•004

.002

FIOURR 51.--G6ttingen 420 airfoil.

Correc led folio

0 .2 .4 .8 .8 lO L2 L4 ZG L8Lift coefft'cient. C,o

0

28 _ 0

24 _ 20

4o

_le_ 6o

_.,_._ 8 _61o0

-8

z._.;,..r.s9_/° _ O_ go 40 60 80 I00;.I 9 Percent of chord2( . P.50

3( _ "$74( 4 :;22 :"

5_ , '.4s _ 2.2 .446( ; !,46 67( i '.45

8_ .58 _ 2.0 .409( .89 5

L.E..'_'Od. ." /. 40 " I 1.8 .3G

• 1.4_.20@

"+, i I.e_z4 _ .- [/.o_ 2o_

Q 0

x, ...6''J./2_

II I% ,,I _ll .4 .08///11// D¢I It / /

I..J_l I !#/ J..l" _, / _ I .z .o4_lll I Ill I [-- o o

I IAAirkoil.'_'#t. 4ZS_O tff.N.'a080,O00

I [ ISize:E'x30" Vel.(ft./_ec.):8,9,.4.

L/I IPre$s.(stnd. afm.):2L I,Dofe: 4-22-32 -.2

I/Y I Iwme_#ested:L.M.A.L.renhV.aT.eZGYI I ICorrecledforlunnel-wolleffect-.4

i i i i i , _ i i i]-4 0 4 8 12 IG 20 24 28

Angle of oflclck, ol (dec].)

.02G

.024

.022

•020

_.Ol8

-.016

.0148

o.008

•OOS

•004

.002

FIGURE 52.--G6ttlngen 429-AG airfoil.


O

28_ 0

24_ 20

_s_ eo

2,z_8o.__8 _oi00

.0

"_ o__ ._.

-8

\/9

//

2.4 .48

22 .44

.40

1.8 .36

1.6 .3Z

• _.,.24._

.20_

, LJ

b

.4 .08

/ I _' .2 .04

R.N.: 3,010,O00S/ze:E"x30" Vel., _.2

-__ Tesf:V.D.T.825 -.4'1-4 0 4 8 /2 IG 20 24 28

Angle ore/lock, _ (deq.)

.02G

.024

.022

.020

_.ol8

•_ .016

_ .0140

i

o .008

.OOG

•O04

.OO2

ZO02c ohead of c/4 × ,

.05c above chord

Airfoil: GblNngen 429:], Test: V. D. T. 825 _/2

Date: 4 -21-32, R.N. :(effective) 8, 050, 000

Correcled to /nfimiie ospeci folio

Lift coefffcien_, qo

FIGURE &3.--GSttingen 429-J airfoil.

O

• 28_ 0

24 _ 20

_zo_40

_ 86

5.01 7,1 '01 _.

I01 8., I/5 I/o.20 I I0., _2

SO]//"I;'40 [_0., l

,Ol_"i_'601 8.

701 6.40 Ir801 4. L901 2. I h

---e.-.t---

__+__+__

-_- __I _ cp

-- 2:._.+_ _

._ 4_

_ o._

20 _;c•: I

_o F :'l ---_o I

40 I

200 20 40 60 80 I00

Percenl of chord

2.4 ..48

2.2 .44

- " - ._o

1.8 .36

" 1.6 .32

.4 .08

.2 .04

0 0A_foi_: Gbfl/ngen 436. RN'3,050,000

5/ze:S"x30" Vel. (ff/_ec.):69,8 , -.2

"Press.($fmd otm.):2O.,9,,Date :3-27-3/

Where lesfed:L.MA.L..Tesf:V.DT.540

Corrected for funnel-wafteffecf -.4

-_-_0 4 8 /2 /G 20 24 28Angle orollock,_ (deq.)

_ .008

•006

•004

.002

0

8

-.3

0.005C ahead of c/4

.05c above chord

I'1

/

Airfoil:GbtHnqen436 Test: V.D 71.540-DoIe: 3-27-3L R.AZ..(effechve)8,050,O00Correc led Io infinite ratio

-'44 -2 0 .2 .4 .6 .8 LO L2 L4 LG Z8

LiH coeff_czenf, qo

FIGUR]| 54.--GSttingen 436 airfoil.


o"b

28_ 0

24_ 20

_le_so

12°u 80_ e_1oo

-8

S?d

(3

s., /.,5 ,.,_ o11111_., .8o _ _'/_"111°a, .5o _ o_ I9.J .30 - Po., . / 5 - 20 4o 80 80I, .00 Percen_ of chord2., .00e. .zs2.( .GSO. 1.05

9._ /.3s I I7. 1.so I4.: 1.as I !

2._ .80 I1., .45., 0

l J

t i c_,

i /'" ),:,: ii " _w.

Z / "• i

/,l

l

/.22.5.7.I(h

2_3_44

S4G_7_

5 ,o_

28_ 0

24_ _o

_.zo_40

._- 8%0100

.0

-8

X /i b\ \./

[ . '%/ /!I

A/Hfo//.'G6fh'nqenS32,/?.N.:3,070,O00

S/ze:E"x30" VeL(ff./sec.):69.5 lPress.(sfnd. atm.):_Z O,Oofe :_-3-33Where tesfeW: L.MA.L.,Tes/:V.D.T./053

Corcec/ed fo C fun, ne/-,we// effect "-8-4 0 4 8 /2 /6 20 24 28

An_I/e of oilock, _ (deq.)

f_ Dole:6-3-33, R._.'(effech've)8,100,000

Corrected fo /n_'_i_e ospec; _ rczh'o /8 '/6"

L/ft coefEc/enf, qo

FIGUBE 66.--G6ttingen 532 airfoil.

¢o

Z

E_OrJ

;>

I=

C_

_rj

E_or3

m

0Cl3

ok..(E_m¢4

E_0

¢4

_40

('hap) °p 'o+,_c,..;#osd_# a//ugu/ uoj ¥ODI-ID JO allJuv

" _, "

I i_\1_._

LI

I

G_

[ 1 #'_[ I

I

,_1 ___, _(,o _" r

" " " _ 7da/_aoo',_A!7

_- 2_

-_-- _

I P"

pJOq3#O

lua_.Jad

r,.e_r_eqt,he3

"-4 "i< < ..... c) ....... (_ ".:

eq

oo._.. {j

,,4

b

(3

?

(pJOC/O .,{0 DL/o_ pJoA4JOj( WOJJ) pJOLp.,#O /ua.3Jad u� "d'o• £b qO % eO '_ _ _" O0

{_ _1_ "" " ' '

(7/f[ "_SD..,po/#/I jo qqo,y

< .4 < ..... ,;___," r_

_2Ff_;q:gi___ _ 1__o_

."',.4 ,

tl'_,,

I lti t_

se.._3__4.___I_

+-%.

"+l" ,4

0

lo

,,a

32

-8 -4

-8 -4

REPORT NO. 628---NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

2.4 .48

.44

.40

1.8 .36

1.6 .32

/.4_.28_

./2_

.4 .08

.2 .04

0 0

0 4 8 12 16 20 24 28Angle of attock. _x (dec].)

F1e_J_ 50.--Clark Y airfoil (Inverted).

Aicfoi/:ClarR YO'nv_-fU),Tesl:V.D T.688Date:/O'/Z'3/, R.N.:(effective)8,3S0`O00 -12Corrected to/nf/niie folio

0 .2 .4 .G .8 lO Z2 /.4 /.G /.8

L/EIcoefficient,cto

20 40 GO 80 /00

2.4 .48

2.2 .44

2.0 .40

1.8 .36

1.6 .32

1,4_.28_

:.24 _i .u: .20_

rll0

.16 u

.4 .08

.2 .04

0 0

._/ze.'E"x30" Ve/.(ff./sec.):69.4.Pr e_.(sfnd, ofm.).'20.7,Oofe :S-3-32 -.2

Where tesfed."L.MA.L.,Test:V.DE838 _.4

0 4 8 I_ /6 20 24 28An_/e of olfack,_ (dec].)

.OO4

FIGU_]_ 60.--Clark Y-B airfoil.

E2

44

Tesl:V.D 7:.838 -/2Dafe: 5-3 -32, _. ]_.." (effecfive) 8, 240, 000Corrected to /nf/nife folio

0 .2 .4 .G .8 lO /.2 Z4 /._ /.8L/ft coefffcient, c,_


O

28_ 0

24 4 20

40I

L ",£/2_ 80.

8_olOO

_o_._.

-4_-8

k_

28_ 0

24 3 20

_ 20 40

_16: 60

q/Z, 80

e_ ,oo

.0

-4 _.

-,9

i

Airfoil:ClarkY M-IE,R.N.:3,170,000_"x30" Vet.(ff /._ec.):68.3 -,Z

Pr ess.(sfnd, c#m.): Zl.3,Duf e : /O-14-31

Where tesfed:L._A.L.,Tesf:V.D.T. 700 i_.4I t for funnel-walleffecf-8-4 0 4 8 12 /G 20 24 28

Angle ofo/tack,(_ (dec].)

.OZG

.024

.022

.020

e;.Ol8

:_ .OIG

_ .0140

_.o/oI

_.°°8 I.OOG_

•O0 4

.002 l0

d_ -.I

8 -.2 _

:!t_ 2• --. -: 0 .2 .4 .6 .8 LO L2 L4 LSLift coeff/cien/; qo

FIerCE 81.--Clark Y NI-15 airfoil.

.4 .08

.2 .04

0 0

.5ize:5"x30" VeL(ft./._ec.): 70.4 lPreSsl($thd. aim.):20.6,Dafe : lO-/S-3/ -.2Where f es ted: L,M A.L.,Test:V;D.E70_2-Corrected for tunnel-wall effect -.4

-8 -4 0 4 8 12 16 ZO 24 28Angle of altock._ (deg.)

.02G

.024

.022

•02O

r_.o/8

, .016.b

_.014caLI

_.012

.OlO

_ .008.006

.004

.002

0

8-.2 ....

I

_. l.Olcabove chard-.3 Clark YM-IE(in vetted) Tes_: V.D.T. 702

-- -- Date:lO-I5-3/. R._ ,'(effech've) 7,_70,000 -lop

Corrected to /Hf/n/te r_t/o L8,/G-'44-2 o .2 .4 ._ ._ Io /2 /4 _Lift coefficient, qo

FI(}I/RE 82.--Clark Y M-15 airfoil (inverted).


0

h..0

28_ 0

z4_ 20

_.zo _o40q_le_60

_lZ_8o8_olOO

_4 _o

o_

-8

SJ Up'

( 3.Z_ G..

2 7._5 9.Z I l.(I 12(I 13._

2 14..3 1424 14.,

5 13..6 I I._7 9£6 6._

9 3.:5 /.:

16 .

I

I

i

i

i

i

:

i

, t

r

I

-8 '-4

3 56

98II

- 94"1 5,9

2 _5"2_5"3 _2"3 /53 97

• 2 93• 2 46-19,9"1 46

• 75- 4G

2O

"_/°111__o _o_ o_1111"-.a-¢ -

O_2o!11111_iil il "k"-IO

20 40 I00

Percenf Of chord

//

/

/

/

24 .48

22 .44

2.0 .40

1.8 .36

_1.6 .32

/.4_.28_

' i ':z_24

/: ._ _" '.o_.2o_

/, / o"o,_ .8u.16°___ / ._ t_

.6 "4 .12c_

f / \ .4 .08j ,,t \

'J %_. .Z .04...'Fc, "-..0 0

A/r-/'all: C/o,'-k YM-/8. RN..3,120,0005/ze.E"x30" Ve/.(ff/sec.):6_.O.Pr'ess,(sfmd. afrn.):2/. I, Dofe :lO-I5-31 -'2Whece fes/ed: L.M.A.L.,Tes/:V.DT.70/COCFleC/ed fo,_ fun,ne/-,wo//e, ffeci "-.40 4 8 /2 IG 20 24 28

An_le of o//clck, (x (deq.)

•02G

.024

.022

•O2O

i_°/s

_ .0140

i

_ .008.006

•O0 4

.002

52

48

44

4o_

3G_

32 _

ee_

24 _,

/s2_

/2 ._.t.

U

q 0 0_6

8 -.z-- -8

Airfo/l."Clark YM-18 Tes_:V.D.T.701 -12

Oate.'lO-IS-31. R.AZ.'(effecfive) 8,240,O00 !Correcfed to /nh'nife folio

-4 "=.2 0 .2 .4 .G .8 ZO L2 L4 ZG L8 IG

L/f/ coeff/c/ent, qoFIGURE63.--Clark Y M-18 airfoil.

0

_b

24 _ 20 _--

_ _o_4o_

-_ Lo- b

8"_ /oo-

__. _ -

o._ Z-4 _ -

-8 --

_- - _- - _-

:__ ii'i

--8 -4 0 4 8 /2 16 20 24 2.8Anq/e of affack, _ (deq.)

,026

.024

.022

•020

:_.o/6

.014

i ,

h_o.008

•006

.004

.002

0

-,I

-.z.w.

-4 -.2 0 .2 .4 g .8 ZO L2 L4 ZG L8LiH coeff/c/enf, C,o

FIOUR_Z 64.--Clark Y M-18 airfoil (inverted).


.02G

.024

.022

•020

u .0/8

:_.O/e_ .0/4

i

•O04

• 002

Dale: 6-22"34. R,N.." (effective)8, I10, 000Corrected to/nf/nife ospec_ ralt'o "16

-4 -.2 0 .2 .4 .6 .8 LO L2 L4 L6

LIH coeffYcien_, c,,

FIGURE 65.--Clark Y-W} airfoil•

2.391 2.39 [ _ _,i '

3 73 1.32 u _" _ I4.44 I,O0 _ _ "_

s.4o .64 I6.05 ,43 '0_6.56 •297,31 .10 )f chord7.77 .0_

&oo I o7.80 I7.20 t '6.261 _5.03 ! ,3.571 l1.91 l1.021 1

p"/

\

/ \

/

IJ

rc

Al'r'foi/."Clark Y-8 R.N.:3,010,O00

.02G

• 02 4

.022

2.4 .48•020

2.2 .44 _.0/8

2.o .4o ._, .OIG

/.8 .36l O _ 4_9

1.6 .32 °u

1.4_:28_

i .G o:.2o_

- _)0

.16 u

.12_ .004

.002

.4 .08

.2 .04

0 0

5/ze:5"x30" Ve/. (ff./_ec.): 70.5 -.2'Pr-ess.(sfnd. aim.): 20.5Date: 6-25-34Where tested.. L._A.L.,Test:V.D.E //4/Correc fed for funne/-woH effect -.4

I I I I

-8-4 0 4 8 /2 /G 20 24 28

Angle oFalf_ck, _ (deg.)

0

-.2 above chord

Al"rfo17." Clark Y-8 Te_f:_D.T. 1141 -/2Dale: G'25"34, R._L .'(effech've) Z 950, 000

Cart-erred to /nf/nite r'o//o L8.16,-4 -2 0 .2 .4 .G .8 LO L2 L4 16

L/It coefF/cl'enl, e_o

FIGURE 66.--Clark Y-8 airfoil.

"10

i

.=

Ratio of lift lo drag, LiD_ be r_

C.p./'n percent of chord{from forwoFd end of chord)

2

t I

bbU-t--bt-t-bl--l

Liftcoeff/o'en/, _

_ .

Oroq coefficient,C_ I

Momen: coef., c_o, . Pro_/e-drog co eff/c/'_ni,._o

I I I I "(_ "(_ .(_ (_3 (_3 (_ (_ _ (_ "(_ "(_ _ "_.... qb _ (:b qb _ _ _ _ _ % _ %

'fii! il -_. --

ico -

col I _ _ r_

Angle of o/lock for :bf/n/'/eospecl rol:o, d o (deg.)

0

i

ROtl'O Of lift t0 droq. L,/D_ I% be IM& _ e.:b < Oo be o'._ qb ._ co

c.p. :n percen/ of chord(from forword end of chord)

_ . . '_. • - .....

0 _ ._ Percentn _ _ of chord

Lift coefficient, C_

Orog coefficient, C_

Moment coef, c .... /°roP//e-drog coefP/'cien:, c_

cl

'

r_ co _ eb _ co r_ o_ eb _, co % o_ eb 4_ c_An_le of o/lock for :;_;_:'te ospect rot/o, OZo (de_,)

L_

©

o

?N

N

©

©NN

©N

N©_Z

Sr_

O3

>.

#q

Zw_

o

h_

0

I


k_O

28_ 0

24_ 20

_,_b ao

8_olOO

-4"

-O

28_ 0

24 _ 20

,o_e_ 6o

8_,oo

.0

_4

--8"

o'r._.58

zzsI t o252,_l_a2z5.0114,857.5J I S.63/0 / 9.05/5 _Y.IO201_1.3730 I _ ?.00

=401_1.445011_.78

' 60 I I 7.20

7n I 1 Y.8380 I Y.83901 _._7951 ?.81iooI .Z3

-._______+_

___+____+_

---+---_

--_4-/t-

____+_

__+.__ _._.__

__,_____+_

-8 -4

FIGURE 7L--Clark Y-22 airfoil.

3,50 3.50[Z25l 5.45 1.93• "_.'. _.50 1.47b.o! 7.90 931_' 9.85 5"31

/Ul 9.60 ¢211s[12.60 tsI201 _1.36 _3130111.70 3Ol40 I 11.40 )Ot50 [I _.52 301SOl _./5 _Ol7ol 7.41 ;'618O I 5.6e ysi90l 3.84 1.021951 2.93 1.401

/oo I ?.os La5 I

L.E.Rod.: 1.50 I

•: li,

i /'

i i

_o to- ?0

_ f9 40 GO 80 I00

il Percenf o f chord 2._'_2"40.44.40"4_

/ 1.8 .36

" 1.6 .32

\ / / _--\</ . /

g N , .4 .o8/ \ o

," _'-.--I .2 .04 J. _-.I

R.N.: J,OSn O00_, 0 0 _mAIrFolY: NA CA. CYH_ 2

Sl'Ze:S"x30" Ve/. (#./_ec.):#_.S __ 2Press.(sfnd. alm.):_L/,Oofe.'3-25-31_ " _ -.3

Where tesfed:L.MA,L,Tesf:VDT536| 4

Correcfed for tunne/-wo/leffecf ]-' _ _.440 4 8 /2 IG 20 24 28 -2

Angle of off.ok, o_ (deq_

FIGURE 72.--N.'A. C. A. CYH airfoil.

.022

•020

e2.018

. .016.ta

_.0140

_ .008

.00_

.004

.002

AirFoI"/:N.A.C.ACYH

Oale: 3-25-31,R.N..'(effecfl've} 8,060,000Correcfed to �mr�nile

0 .2 .4 .G .8 ZO Z2 L4 Z6

Lift coe(ffc1"enl, C_o


1-

7-r

4-{--_, I-F

T-F

._l_ 8o! _l

_o_.•._ -F

-_ i-

.4 .08

.2 .04

0 0

-8 -4 0 4 8 12 IG 20 24 28Anq/e of oifack,(_ (de9.)

.O2G

.024

•022

.020

d.o_8

.G.OIG

_ .0140k)

FIGURE 73.--N, A. C. A. CYH airfoil (inverted).

;to.

0

25 1_55.0

/0 ;

20 ,

25304050GO70 •80

9095'00

?0

{

t

oGIOOI._4_

_: o_,_ --

73P3

47t

-8for/unnel-woHeffecf

-8 -4 0 4 8 /2 /G 20 24 28Ang/e of a/lack._ (deq.)

.02G

.022

•020

_.o_8

, .OIG.b

_ .014QtJ

i

o.008

.OOG

.004

•002

.OOc aboveAirFoH:NA.CA.-MG

E2

_8

44

zo_

s2_eo _

2o_

k

U

-8

-/2B Dale.'3-19-31,R.N..'(effecfive) 8,000,000

Corrected fo /nf/nife aspec/ folio -16

Lift coeff/cien_, c,o

Frauds 74.--N. _.. C. A. --M6 airfoil.


4.r5"b

28_ 0 --

-+-

24_ zo -I-

40

-_ L F-t-i

8 ,ooH-q

ZZ ZZ Z ZZ -_

Z.Z ZZ Z ZZ _(-

-8 -A 0 4 8 12 16 20 24 28

Angle of attack, (x (deg.)

•026 E2

.024

44

.020

_.018

. .016.b

_ .014

i

h_o.008

.006

•004

.002

Dole:7-24-30, R.N...(effective)8.210,000

Correcled io /_nile ospec___i rol/o /8"/_-4 -.2 0 .2 .4 .G .8 ZO Z2 L4 LG ,

L/F_ coeff/cien_,C,o

FIGURE 75.--N.A. C. A.--M6 airfoil(inverted).

ol : -- .02G

°il_ ii _-o I

,oo111II i . .o2420 40 60 80 I00Percenf o fchord .022

I I 2.4 .48•020

I 2.2 .44r_

i , .018

2.0 .40 ._.G.OIG

1.8 .36 ._._014

/ i.s .32 8b_

1.4_.28C

c£ .G o .t

f \ .IGU b_b

1.12_

.002.4 .08

0

.2 .04

o o8 -:2

-.3

-8-4 0 4 8 /2 /G 20 24 28

Angle of ollack, e_ (deg.)

E2

44

Oole:_-11-32, R.N..'(effech've) 8,240,_00Corrected fo /nf/nile r_ll'o

.4

L/f/ coefh'c/'en_,Go

FIGURE 76.--N. A. (3. A. 15 airfoil.


4.0

28_ 0

24 _ 20

_s_8o

,_ 80

8%,oo

-8

sto.l,'p' IL',0 -- 0

/.25 '._]-/ t62.5 ?.59]-/ ;25,0l _.7 _' "2 _67.5 t6 _' -3 '6

I0 f4"'-3 iE15 _.< g I -3 _620 7.2ql-4 P7

25 _.6 _ I"4 ?030 Z.6,q I"4 _?.

40 _._ql-3 7050 _'._.41-3 _460 _.:;SI-2 }'670 ilg1-2 r4

90 _..( "

95 IJ 4_ - _8/O01t ./ _)l (- '3)/00 - 6

L.E. Rod.: 0..80

3lope of rodiu$H_rouqh end oFchord, O.lO

I

i

i

! °

0

4.0

24_ 20 I

_.eo_4o

2,e_8o :o%1oo

_ o._

-8

2_

_ _cIIIIIII I &_.

_._'_CllllllI I : l- 2(_

) 20 40 60 80 I00

Percenf Of chord

I

./

q

",'" [ I -I' o1 / A/FFoi/.'N.AC.A.16 ,_.N.:3./70.000|

' S/ze:E"x30" Veil (ff./sec):68. 7J_ 2Press.(sfnd otm.):2LO,Oofe :4-30-3_ "

Where fesfed: l._A.L,Tes/:V.DT.833J 4Cor/7,ec/e,d fo r tun, ne/-,woll e,ffec? ]-"

-8-4 0 4 8 12 IG 20 24 28

Angle of oitac/£ ol (deg.)

2.4 .48

2.2 .44

2.0 .40

1.8 .36

1.8 .32

/ k 1.4_.88¢

/ } '.e_.84/ ..e, < / - _q \ ,j " _

i / ;',./ .s ./e_

I j .,,/ x_ .4 .o8/ .'r \ .e o4

.O04

0¢

4_ -. I

8 -2--4..

Alrfoi/:N.A C.A.18 Tes/ : V.D T.833Oa/e:4-30-32.R.N,.'{effech've)8,370000 -/2

Correcied to infinite aspec/ FOlio-4 -2 0 .2 .4 .G .8 ZO L2 L4 LG Z8

Lift coeff/cien/,O_o

FIGURZ TA--N. Ao O. A. 16 airfoil.

-:° 1_"'_':l''_l "_,o _ __- ./ _0! _

z251 ,[6;81-2 T

I0 i/ "3 _5 "?00 20 40 GO 80 I00

'_ "'_1:3 '_e -] IPercen/ o,_hor_, e.e2o bi:i,o / e.4 ._,8

25 7.6 5 .... I30 Z.,f.

40 u_ : ,oso _._ ,,_ .44

80 _." 22 _6

70 _._ : , / 'ao .; -I _ , : 12.0 .40

95 I.*4t " _8 r

I00/001'_"_)1( 0 'a, j 1.8 .38

LIE.Ra_.:O.40 [S(ope of rod/us ' . I._ .32i'hrouqh end ofchor_. 0.95 r _

i /.4_.28¢I'.2 _ .24

o{ o{

.G'_.12c_

I _" i l , _. i I /1 .08

t/I I1." _ I '_,4' t L.,F¢ I'_ I I e .o4

(I L,,'FI i I "-,L I"r'T II I I I-7"o oA/,"FoiI."NA.CA. 17 /_._.:3oZO0,OOOI.5/ze:S"x30 _ Vel. (ff/sec.):GS.4 __ 2PFess.(sfHd otm.):2/.O, Do/e: 5-3-321 "-Where lesfed:L.MA.&,Tesf:V.DT.8341

Cor_,ected for funne/-waHeffecf l-'4

0 4 8 12 IG 20 24 28

Angle ore/lock, ot (deg.)

II/ .j \

• i\ Ii

iiIIII

"r"_

-8 -4

52

48

_4

.ozo 40_

•_ .018 32 c_

_.o_4 88_ta

, 20 _

_o.oos ,s:{• OO8 /g _"

t,,

• 004 8

U

.002 4_b

0 O_

d _

0 -.2 .02c above

A/rFotY.'_A.CA. 17 Test: K O. T. 834Dote: 5-3-32. R.N .'(effective) 8,450,000

_3

--_ -.4 Corrected to /nf/_ile ospecf Folio /674 -2 0 .2 .4 .8 .8 /0 L2 L4 Z6 L8

Lift coefffc/enl, c,_

FIGURE 78.--N. A. C. A. 17 airfoil.


?O

0

"b

28_ 0

24_ 20

_,s_so

2,2_8o_ e_oloo

.0

_ o._

-8

Stc lp : '_'_,'r.I

0 -- -I OO/.2'. /. ¢ -2082/. 2.1 9 -250

5.( 3.: 9 -3 O07.t 4._ 4 -335l_ 5. _ -3 80I'_ G., 9 .3962(. 7. _ -4 I 72_ 7.1 g -420

36 7. 9! -4 lg46 7., 91 "3805E 7., 41 -334

7C . 14

8C 3. 51-1509_ 2J _l - 82

I0_ - 0 I

L'E'Ro_:O'8Oof [Sh p_ o # #dJ JSFh -o_ _2_ _ *d

III

._c_mlleo Io 6o 80 _ooPercent of chord

/ k

! _2.4 .48

2.2 .4.4

2.0 .40

1.8 .36

/.G .32

/.4_.28_

(

-8

i i -_ _ _-- -_ .h_..zo_

.8u.16 u

'. I / \ '" ':'i I IV ><_ "6"J'12C_

I I " •I, /I / ,, .,_ .o8I II/I ..,_ x

' _" .2 .04

_' IA,_/oi/.',_A.CA./a /_.N..:aOZO,O00 o o

I ,Sl'Ze:5"'x30" Vel.(ff./sec.): 70.2Pre_s.(sthd. a/re.):203, Date:5 - G-32 -" 2l Where tested:.L.MA.L.,Tes/:V.DT. 83G

:Corrected for tunne/-wa// effect -.4

-4 0 4 8 12 IG 20 24 28

Ang/e o/all_ck, ol (deg.)

.002

FIGURE 70.--N. A. C. 4.18 airfoil.

$2

48

Airfoi/.'N,A.CA. /8 Test:V,O.F, 83_ -/2Da/e: 5-G-32, R.N.:(effective)8,/00,000

Corrected lo the'n/re aspect folio0 .2 .4 .6 .8 ZO L2 L4 L6 L816

Lift caeff/cien/, C,o

.024

.022

•020

#.ol8

. .016

_.0140U

_2o.008

,006

•004

FIOURE 80.---N. A. C. A. 19 airfoil.

"/2Dale: 6-3"32, R.N...(effechlve) 8,180, OOOCorrected tO /nf/nile

0 .2 .4 .G .8 lO L2 L4 LG L816

L/ft .caefffc_en/, C,o

?o

h.o

_3

28_

24_ 20

q __/s_eo

2,2_8oe_o,oo

° f

-8


-8 -4

Airfoil." N.A.C.A. 21 R,N.:,_080,O00

S/ze.'S"x30" Vel. (fZ/sec.):69.2 .Press.(sfnd. atm.):2/.2,Oafe : 5- 7-32Where tested: L.M.A.L.. _esf : V.DT. _3 7

Corrected for funne/-wal/ e_

0 4 8 /2 /G 20 24 28

Angle of oll_ck, ol (deq.)

0

2.4 .48

2.2 .44

__.0 .40

1.8 .36

1.6 .32

/.4_.28_

2_24_G .u.]o_.2o,_Q Q

,su./_

.6"_./2c_

.4 ,08

.2 .04

0 0

-,4

_ 0

-.2 . I0 c be/ow chor_ iO012e ahead of el -8

Airfoi/:N,A.CA. 20 Test: V. O. T. 845

Dale:G-4-32,R._.'(effeclive) 8,100,0001_3

Corrected td /nf/Hi/e asPlec7 _ t_al/*0 18-'4,4-.e0 .2 .4 ._ .8 /.0 z2 /.4/._/2

Lift coeffYcien/, c,o

•028

.024

.022

,020

#.o/8

_ .014

.004

.002

0.005e ahead oft

03e above ]_ _J_ -L

AirfoH:N.A.C.A.21 Test:V.D.T.83 7 _/2t_ Date: 5- 7-32, R.N. :(effective} 8,130,000

Corz-ec_ed to /nf_Hife aspe. cff folio /.816--.44-z o .z .4 .¢ ._ zo zz /.4/._Lift coefficient, C,o

FIGURE 82.--N. A, C. A. 21 airfoil.


52

,48

44

_o

es_

24_

/z ._.

4b

-4 _

-- .Ole above -8

Da_e:8-15"32, R.N.:(effecfive)8,/30,O00 -12Correc£ed to/nfiiTife aspect ratio

O .2 .4 .G .8 ZO L2 L4 LG L8 '/6

_a 4up', , ,',-

L251 /.8 _.3Z.51 2.5_ S65.01 3.5_t 147=..'. 4.3_1 41:::: 4,9)1 _4-" " 5.7_1 $6

201 6.2 _1 _3

_ , 6.4 #6401 5.9_1 _0

50 [ 5.0 _ I 92

91

?6

u IIIIHII I

-:cllllll I.2o _o so 8o /ooPercen# oF chord

! 2.4 ._8

I _.2 .#4

.3 _1' <re i 20 .40

,.,. /oo,o i r

0 L.E._od.:O.949 I _ i1.8 . .36Slope of rod/us _ l I

_ thro_qh end of ' _ I =. _ _chord. 0./448 " Q _ I I _ o .o_

Illlll i _i' " I -z8._ 01 i ] i i i /, U I/'4_ 28_

o.,_ ,,,.,I I I I I IL/Z' e- / I'_ '1,o_" _._"

_,,,,<.eOI I I I I III ( : u u

"_,.,o8ol I t I I Iii J ,. / _Li/Z__'_ I I I I 1 I I ' 9_,. ,.o . c_._ 8_/oo I I I I I I / "/ _', 4 o_,_ o I I I I ! I_' ," , ' "_

.,_ I I I III Y .,/c, \ o ,_.,.£ "P I I I III/I ./" "__ "....

o"_ _ I I I g! IA/FFoiI'N.A.CA 23 R.N,.'_030,O00

"_4'r__" !1 I/I I5/ze:d"x30" Vel.(ff/sec.):69.7-2] I_ [ [Press.(sthd.atm.):21,/,Dafe.'/-4-33 '

8 - I Where tested:'LMA.L.,_est. _.D.7_,9,I0

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

Angle of'oHack, o_ (dec].)

.OZG 52

.024

.022 44

.004

FIGURE 84.--N. A. C. A. 23 airfoil.


.022

_4 .48

_2 .44 _.018

._o•"G.016,

/.8 .36 _.014

1.s .32 8

: .20_0

.16 u

:./2_

.04

0 0

.006

.0O4

.002

0

8 -.2

Dole:1-5-33, R./¢.'(effective) 8,/00,000Correcled to infinite folio

-4 -.2 0 .2 .4 .G .8 ZO Z2 Z4 /.G Z8LiftcoefF[cien_qo

FmURE 85.--N. A. C. A. 24 airfoil.

45

44

FIGURE 88.--N, A. C. A. 25 airfoil.

Test: V.D 7:.1/46 -/ZDote: 7"2-34, R./¢ .'(effeci/'ve) _,lO0,O00

;tied to infinite folio0 .2 .4 .6 .8 ZO Z2 Z4 ZG Z816

Lift coeffFcient, qo


;ta.l'4,'rL'w_1 _' 0 -- --

?.5 -3.43i _IL,5.0 -_.TZ. _,,__-5.511 .7.5 i:7; -6.091 0 20 40 GO 80 /00

9', -6.751 Percent oF chord I

ZO r66: -7.021 "_,,,_ ,,_',_

25 rC ,9. - 7.06 _ -T -F _ E/e ._+o30 I( ,91 -6.90 --_ -4-_o ,(.l, -6.311/// I I I I I I t i I5ol _.6_ -5.45!-T-F_C _2.2 .44

IZ3 601 _.6_ -4.391 _--L--LL 70 • 5; -3.25!ooi,:, -2o,444 _z.o .4o

_. . 901 .8, - .88_ -_ -L -L _ .95 2: - 37

",- oo] ," o" JA_ L _/ 8 .36

_3 slope of rod,_s i _ "_, _ ,,_ [ II I I _ ____ through end of __, _ _TT. nJv. / _, j_

_J chord.. O./45 i L7,970,000, _ " "

__77--F-F-_'.-F-3.590,000,_ I _ t l l

b-Tfl_-- _ _ , . , _. _.-

.0 b

o"_ ._. _ A_PFoiI.' N.A.C.A. 26 R.N•: 3,020,O00 I" __ _ _U___S/ze:E"x30" Ve/.(ff./sec.):70.6 __ 2

-- _ _ Press.(sfnd.atm.).'_QEDofe: 7-3-34t -o- ] I/i i lWheretesfed:Z.M.A.L, TeM:V.D.T.//4_

-o Corre¢/ed_oC_2_e/-_.//._eec/_-."T__- 4 0 48 /2 IS 20" 24 28

An_I/e oFol/ac/£ oz (deg.)

E2

48

.02E 44

•o2o 40

_;.o/_ a__

:_ .o/s 324

82d _

, 20

.OO6 /2_t.

.004 8_

•002 4b

0 O_

h,_ -.I -4_ "

8 -.z -_

-.3 Test:V.O.T.I/47 -12"Date: 7"3-34, R.N..'(effech've) 7,970,000

Corrected /o /nF/Hi/e aspect Fo//o T8/6-'-4.4-2 0 .2 .4 .6' .8 LO L2 .L4 L6

L/F/ coeff/c/eni; C,o

FI6URE 87.--N. A. C. A. 26 airfoil.

,o, j-" 0 20 40 60 80 0

Percenl o f chord

A/;-Foi/: NA.CA. 27 R.N.: 3,010,O00S/ze:S"x30" VeL (ft./sec.): 70.3.Pr ess.($f;_d, c#m.).'_0. 7,Oafe :_-30-34Where tested: L._A.L._esf : V.DT.//45

;ffec/ " -.4

-__-4 0 4 8 12 IG 20 24 28

An(lie of olfock, O_ ('deq,)

2.4 .48

2.2 .44

2.0 .40

/.8 .36

1.6 .32

/.4_.28_

2._ 24 _• uJ " ._

._j ,u

!- .s"_./2_

.4 .08

.2 .04

0 0

•02G 52

.024 48

.022

•020

_.o/8

:_.o/G

U

.OOG

•004

.002

-.3Da/e:G-30-34.R.N..'(effecf/ve)7,940,000Corrected to/nEnite.4

-'_-.4-.2 0 .2 .4 .6 .8 ZO L2 L4 Z6 L8

Lift coeff/cien_,go.

/6

FIGURE _.--_T. A.. C. ,&. 27 airfoil.

0

Z

O0

e o;--1

d

o 80

0

÷

,t

I I]11 II _

ooooooo I'l'l'l'l" I'1"1"1"1"1" 1"1'1"1"1"1"1" I'1"1"1"1"1"1"1' I'l'l'J'l'l" I'l'l'l'l't'l" I'l'l'l'l'l'l'l" I'1'I'1"1"I" l'l'l'l'l'l'l'l' °°°°°°1" "°1"

_°_IIIII IIIIII 1111111 IIIIIIII IIIIII IIIIitl II)11111 IIIIII )!111111 ''

_." .......... MMMMM_ ..................... MMMMMMM MMMMMMMM MMMMMM MMM_MMMN "M_MM_M_M_

_._ _ o

<_0_

•_ _ oooooo _oooo _o _o_ oooooooo oooooo ooooooo oooooooo oooooo ooo_oooo ooo_o_

o

_'ili!il iiill i!!i!i iiii!il ii!iiiil iiili! i!i!iil ili!!'!! i!ii!i !!iiiii! i!'iiii!i_

,-s

_g

.t_:l

_0"_ _

4 __°=

48 REPORT NO. 628----NATIONAL ADVISORY COMMITTEE FOIL AERONAUTICS

r/)

rJ2

o_

o_

O

I.

, , , . , , ,

rD

,_ _= _ ¢4 ',_ ',_ ' ¢4_ ',_ ' _5 ',¢4 ]¢_¢4 ,.4 ',¢g_ ' o6.-Z I_ ', ¢.i ',_¢4o6 _,.4 _,-_ ' ,.4 ',_ 1,.4 ' ,,_4 ]egege_

- _ i i i i i i" i ! i i ', i i i

ea_ _ .....i_ i= i _ i_ i _ i_ i_ _ ',"_ ' '_ ','_ ',".4 ,,"'_'_ _ ,,"_',"_ ,,;_',"_ _ ;_._

_ _ _-_ ,,_ _ ',_ ©_ i_ _© i_: _ '_

-i' ii i ..... ii ..... i, .... i....

I ',

j _ "1" "1" " I'1" "1' " 1' "1" "l'l" ( "1"1" ' i'i" "1' " l" "1"1 "¢_ °1" "1" ' I" "1" "1" " I'1" " I'1"1' I"

iii°°i°i°i i" °i i i°i i i i i i i°°i°_- _<_ ', • : • ', • • ', • ', • ', • : • • • : • • ', • • _ • ', • : • "<_ ¢_ " ', " I • ', • ', ' I " • ', ....

_._ _ .................................................

..._ ,._ I¢4 ',.,_ ', _ I¢4 ', _ I_ ._"_ • ._ ',_6_.' I ,--;,_ ',-; ', ,d I,_o o_ I_ ', ei ',_ I_ ', ...d,._ ',,.__ _ I ',i ',1 ', I I ',1 ', i ',1 :T [ [ ',1 I ', I I ',1 ', I II I l II ', I :[ ', I ', I I ', I I I [

[ .

r..) , -I I

zr_=_ z. zzzzzz zii[i iliii[ zz',zz izz ii zzzzi iiili ii!i}! zzzzzz

',_= I_- ', I ', , '. ',": ', ', I ', ', ', ......................

ig"_"-;.' 11-1.4.' '._i_}! i_ii_ "i""i """": """"" ":'""" "" "":",_" ',_ ',_> : ',_" ',_" NN_I_ , ,_ ,_ _ , ', ', , _ ', _ ', I " : " " " " i _ ' " " ', ',.-: : ', I'," ','_ ',= _ ',= ',= , _ i _. ' '.._ ', ', ', _ ', ' ', ', ', _ ', ', ', ', ', ', ', I ', ', ', ',_- ' ' ' ',

_r_ ', ,,w. _ ..... ,, .......... : ...... = , , , ,',_I._ _ _ I _ :_" _._ _& ...................... ..._ ,

OT7

o,9,

g

g

"IXhlhI/l£ x.r.IShlX(I-X"IaVI_IVA XH,I, h_I (IX,.L_X,.L S'IIOzI_IIV _0 SDI,L_I_X,LDV_IVH0

Documents

search.jsp?R=19930090937 2020-06 … › archive › nasa › casi.ntrs.nasa.gov › ...REPORT NO. 628--NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS ao, the section lift-curve slope