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TECHNICAL REPORT R-84

ORDINATES AND THEORETICAL PRESSURE-DISTRIBUTION

DATA FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS

WITH THICKNESSES FROM 2 TO 21 AND FROM 2

TO 15 PERCENT CHORD, RESPECTIVELY

By ELIZABETH W. PATTERSON and ALBERT L. BRASLOW

Langley Research Center

Langley Field, Va.

https://ntrs.nasa.gov/search.jsp?R=19980223594 2018-08-21T00:04:47+00:00Z

TECHNICAL REPORT R-84

ORDINATES AND THEORETICAL PRESSURE-DISTRIBUTION DATA FOR NACA

6- AND 6A-SERIES AIRFOIL SECTIONS WITH THICKNESSES FROM 2 TO 21

AND FROM 2 TO 15 PERCENT CHORD, RESPECTIVELY 1

By ELIZABETII W. T)ATTERSON " and ALBERT L. BRASLOW

SUMMARY

Basic thickness forms of the NACA 63-, 6_-, 65-

series and NACA 63A-, 6_A-, 65A-series airfoil

sections are tabulated for thicknesses of 2, 3,/_, and 5

percent chord. Also presented for these thin airfoil

sections are theoretical values (_ pressures a_d velocity

ratios required to obtain theoretical airfoil pressure

distributions. In. a&lition, for each family of air-foil sections, cross plots are presented fl'om which

ordinates and pressure distributions can: be easily

obtained for airfoil sections of thicknesses inter-

mediate to those presented in this report, in NACA

Report 824 (from 6 to 21 perce_t chord for the NACA

6-series), and in NACA Report 903 (fl'om 6 to 15perce_tt chord for the NACA 6A-series).

INTRODUCTION

In order to minimize the wave drag of super-sonic aircraft, the wings and tail surfaces are

designed with the use of airfoil sections thinner

than 6 percent chord. Ordinates for only a fewof these thin airfoils are published and these are

not conveniently located in a single report. This

report will supplement the information presented

in references 1 and 2 and provide the ortlim_tes of

additional airfoil sections useful in design ofsupersonic aircraft.

The information presented in this report in-

ch|des tabulated ordinates for symmetrical NACA

6- and 6A-series airfoil sections with thicl,messes of

2, 3, 4, and 5 percent chord and a simplified

method of obtaining ordinates for any thickness

intermediate to published values from 2 to 2l

Supersedes NACA Technical Note 4322 by Elizabeth V,_. Patterson and

percent chord for NACA 63-, 64-, and 65-series

and h'om 2 to 15 percent chord for NACA 63A-,

64A-, and 65A-series airfoil sections. In addition,

a simplified procedure is presented for obtainingthe pressure dish'ibutions about airfoil sections ofintermediate thicknesses.

SYMBOLS

c chord of airfoil

t maximum thickness of airfoil

Iz_ free-stream velocity

V local velocity at any poin! on airfoil surface

AV increment of local velocity

AI_ increment of local vdot'ity caused t)y

additional type of load distribution

x distance along chord h'om leading edgey distance perpendi('ular to chord

DISCUSSION

The basic thickness forms for the NACA 63-,64-, 65-series and NACA 63A-, 64A-, 65A-series

airfoil sections with thicknesses of 2, 3, 4, and5 percent chord arc presented in tim tables'of

figures 1 to 24. For tho 6A-series airfoil setqions,

where a trailing-edge radius is specific(l, an ordinateis presented for the 100-percent-c]|ord station

to serve as a guide in fairing the rear portion ofthe airfoil. The theoretical methods of references

1 and 2 were used to derive the 2-percent-tlfick

airfoil sections of the NACA 63-, 64-, 65-series

and the NACA 63A-, 64A-, 65A-series families,respectively. Althot|glt not exactly corre(.t,ordinates for thickness ratios intermediate to

those presented in references I and 2 and in the

Albert L. Braslow, 1958.

TECHNICAL REPORT R--84--NATIONAL AERONAUTICS AND SPACE ADMIN'ISTRATION

present report can be obtained for all practiced

purposes by the following method which wasused to obtain the ordinates for the 3-, 4-, and

5-percent-thick airfoil sections tabulated herein.

For each family of airfoils, the ratio obtained by

dividing the ordinate y at each chordwise station

by the maximum thickness t is plotted againstthe airfoil ma_mum thickness in percent airfoil

chord as presented in figures 25 to 30. From

these cross plots, the ratio y/t at each ehordwisestation can be obtained at, the desired wdue of

maximum thickness. V_dues of the ratio of the

leading-edge radius to the maximum thickness

squared as a function of maximunl thickness t

are presented for the NACA 6-series and 6A-seriesairfoil sections in figures 31 and 32, respectively.Addition of a cambered mean line to the basic

thickness form is accomplished with the use ofthe mean-line data of references 1 and 2.

The theoretic_d pressure distributions, indicated

by (V/V+) _, for each of the symmetrical airfoilsections presented are also tabulated in figures 1to 24. in order to obtain the theoretical pressuredistributions for these airfoil sections at angles

of attack and/or with cambered mean lines, the

procedure described in reference 1 can be used.In this method of calculating the pressure dis-

tributions, the velocity distribution about anairfoil section is considered to be composed of

the following three separate and independent

components :

(l) The distribution corresponding to the

velocity distribution over the basic thicknessform at, zero angle of attack (V/V=)

(2) The distribution corresponding to the designload distribution of the mean line (AV/V_)

(3) The distribution corresponding to the addi-tional load distribution associated with angle of

attack (AI'./V_)Values of the velocity-increment ratio _V/V_

are presented in references 1 and 2 and wdues

of the velocity ratio V/V_ and the velocity-increment ratio AI-/V_ are tabulated in figures

1 to 24. For each family of airfoil sections,

vMues of (V/V_) _ and AI_/V,_ for intermcdiate

thicknesses can be obtained from figures 33 to 44.

In these figures, (I'/V_) 2 and AI_/V_ arc plottedas a function of the maximum airfoil thickness

t in percent chord for each chordwise station.

Careful comparison of the ordinates and pressureratios tabulated in references 1 and 2 with the

faired cross plots of figures 25 to 44 shows some

discrepancies. Although these discrepancies are

small enough to be disregarded for all practical

purposes, the values obtained from the faired

cross plots are preferred for design considerations.

LANCLEY l_ESEARCH CENTER,

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION,

LANCLEY FIELD, VA._ A_g_sl 25, 1958.

REFERENCES

1. Abbott, Ira II., Von Doenhoff, Albert E., and Stivcrs,

Louis S., Jr.: Summary of Airfoil Data. NACA

Rcp. 824, 1945. (Formerly NACA WR L-560.)

2. Loftin, Laurence K., Jr.: Theoretical and Experimental

Data for a Number of NACA 6A-Series Airfoil

Sections. NACA Rep. 903, 1948. (Supersedes

NACA TN 1368.)

II

ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 3

(v/v=)z

1.2

.8

.4

(v/v®)2

i20 40 60 80 I()0

x, percent c

]•2 ......

J0 0 20 40 60 80 I00

x, percent c

AI',tI'_

14.1{'¢12. 2621. 7401. 353

• 998• 703•558•480•380•320• 277• 245• 218•195• 175• 158• 143.128.115• 102

•090.077•065• 050• 035

0

z, Percentc Y, percent c

0 0.5 .158.75 •198

1.25 ._542.5 •3525.0 .4897.5 .590

10 .67115 .7965_) .8852.5 .94630 .98335 .99940 .90345 .96550 .91655 .85060 .76965 .67670 .57375 .46380 .35085 .23990 .13695 .051

100 0

(171"_)2 _171"_

0 01.028 1.0141.032 1.0161.037 1.0181.045 1.0221.049 1.0241,050 1.0251.051 1.0251.052 1.0261. 053 1.0261. 054 1. 0271. 055 1. 027

1. 055 1. 0271,053 1.0261. 050 1. 0251.045 1.0221.039 1.0191.033 1.0161.0_5 1.012I. 018 1. 0091.009 1.004

.999 .999• 989 .994.979 .989.969 •984• 958 .979

L.E. radius: 0,045percent c

FmuR_I. NACA63 002 basic thickness form.

.r, percent c

0.5 .243.75 _ .300

1.25 .3832.5 ,5285.0 .7327.5 .884

10 1. 00615 1. 19320 1. 32725 1,42030 1. 47635 l, 49940 I. 48945 1. 44550 1.37l55 1.27l60 1.14965 1. OO870 .85375 .68880 .52085 .35490 .20195 .074

IOO 0

y, l_'rccnt c (ITVo)t

O _----'-- _ I

1•o li1. 0421. 054 _ :1. 065 :I. 071I. 0741. 0761. 079i. 081I. 083I. 084I. 0821. 0801. 0741.068I. 0581.0491.0371.02.51.012

•998.0_3.968•954•939

'7 T"¢_

.011•021•027.032

:. 035:.O36:. 037• 039• 040•041.041• 040.039• 036• 033• 029.024.018,012006

,999,991,984977

,969

AI'o/V_

9.08324777O3779957OO55948138232127,8245218195175158142127 I

114 ]

076064049034

(

L.E. radius: 0.072percent c

FIGURE 2. NACA 63 003 I)'_sic thickness form.

4 TECHNICAL REPORT R-84--h_ATI01_AL AERONAUTICS AND SPACE ADMINISTRATION

.8 - t i - :

0 20 40 60 80

x, percent ¢

I00

x, percent c y, percent e

0 0.5 .330• 75 .404

t. 25 .5132. 5 ,7055, O .9767. 5 1,178

]0 I. 34115 1. 59020 1,77025 1. 8943O t. 96935 2. 00040 1.98445 1.924

1. 82455 1. 6896() 1. 52565 1. 33670 1.129

75 ,91080 .68685 ,40690 .20395 .096

IOO 0

(l'(I'¢o)2 : T_rl"_

01. 0101. 0491. 0681. 0821. 0911. 0971. 1001,1061.1091.1121.114I. Ill1.1081. 1001.09l1. 0781.0651.049I. 0331,015

.997• 978• 958• 939• 921

2_1"0/I",_.

0 6,7111,005 2. 2121.02t 1. 7891. 033 1.3951.044) .991

1.045 .6061. 047 .5601,049 .482I.052 .3831. 053 .3211. 055 .278I. 055 .2451,054 .2181,053 .1951. 049 .1751. 045 .158]. 038 ,1421.032 .127L024 .1131. 016 .1001. 007 .087• 998 .075•989 .063•979 .048•969 ,033•060 0

L.E. radius: 0.12_ percent e

FIGURE 3.- NACA 63 004 t,a_ic thickness form.

1,2--

.8 1-- i i

{v/v_)2

.4 <_---_-- ---

I

i

__i--. I

0 20 40

II I60 80 i00

x, percent c

x, percent c

0.5• 75

1.252.55.07.5

10152O25303540455O556O65707580859O95

100

I y, percent c

I0

.417

.600• f)42• 881

1,220

i 1. 472i 1. 676

1. 9882, 2132. 3082. 4622. 5002.47g2. 4012, 2742. 1041, S971. 6611. 4011.128

• 849• 576.324

• 1180

(171"_?

0• 994

1,0521,0771. 0981. 1111.1201.1241. 1331,137L 1411,1431. 1411. 136l.l_1.1141,0971.0801. 0611. 0401.018

• 995• 972• 947• 924• 902

L.E. radius: 0.200 percent c

17V_

0• 997

1. 0261. 0381. 0481,0541.0581. 0601. 064I. 0661. 068I. 0691. 0681. 0661.0611. 0551. 0471. 0391.0301.0201. OO9

• 997• 986• 973• 96L• 960

Al'dl'_

5. 3532. 1691,7991. 403

• 987• 694• 561• 483• 383• 322• 279• 245• 218• 195• 175• 158• 141• 126• 112•099•086• 074.061• 047• 032

0

FIGURE 4,--NACA 63 005 basic thickness form.


¢v/_) z

1.2

.8 ----

20 4O 6O

x, percenl C

0 80 I00

z, percent e y, percent c

o o,5 .149

.75 .188

1.25 ,246

2. 5 .344

5.0 .480

7. 5 .575

IO ,6.54

15 .775

20 .863

25 .928

30 ,::i .97135 •995

40 .999

45 .976

50 .93l

55 .867

60 .790

65 .69970 ?597

75 .487

80 .372

85 .258

90 .150

95 .058

100 0

(I'/1"=,

0

1. 0211,033

1,042

1.0_-5

I, 048

I. 049

I, 049

I. 050

1. 051

1. 051

1. 052

1. 053

1.054

1.052

1.048

1. 042

1.036

1.02_

1. 0201. Ol I

1.002

• 992

• 983

• 970

,955

T ., Vof 1 _¢

14.451

2. 210

1. 860

1. 465• 998

• 697

• 562

• 478• 380

• 320

.277

.245

• 218

• 196

• 178

• 158

• 142

• 128

. I15

• 102

.089

.078

.065

• 052

0' 035

L.E. radius: 0,028 percent e

(v/v¢o)2

1.2

• 8 --

0 20 4O 60 80

x. percent ¢

I00

x. percent c y, percent c

7

0 "L 0 "

.5 ,, .2,35

.75 .288

1.25. .372

2. 5 : .5155.0 .712

17.0 5 "' .973"856

15 1.156

_1 1.291

_ 1.389

30 1.455

35 1.49I

40 1.499

45 1.463

50 1.395

55 1,298

60 1.180

65 1.043

70 .889

75 .724

80 .553

85 .382

90 .221

95 .084

100 0

(TTV_:

.028

1. 051

1.058

1. 063

1. 066

1. 068

1. 070

1. 072

1. 075

1. 077

1. 079

I. OgO

I. 081

1. 078

1. 071

1. 063

1. 053

1. 041

1. 030

1.0151.002

• 987

• 972

• 953

• 935

17V_

}1.014

I. 025

I. 029

1. 031

[. 032

[. 033

[. 03,1

L, 035

I. 037

I. 038

[. 039

i. 039

L, 040

[. 038

l, 035

[.031

i. 026

1.020

t. O15L 007

[. 001

• 093

• 986

• 976

• 907

a VolV,

9. 750

2. 223

I. 860

i. 465

• 995

• 696

• 561

• 478

• 381

• 320

• 278

• 245

• 218

• 197

• 178

• 158

• 142

• 128

• I14

•I01•088

•076

.063

.0_

O" 034

I,.E. radius: 0.062 percent e

FIGURE ,5. NACA 64 002 basic thickness form. FIGURE 6.--NACA 64 003 basic thickness form•

6 TECHNICAL REPORT R-84--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

1.2

.8

(v/v®lz

.4

t

2O 4O 6O

x, percent c

8O I00

x, percent c y, percent c

0 0• 5 ,322.75 .391

1.25 .,5002.5 .£_55, 0 ,9437.5 I, 134

10 1. 29015 1,5362_) 1,7172;_ 1. 849

30 1. 93835 1. 98740 1. 99745 1.9,5050 6.85755 1+ 72660 I. ,56765 6. 35270 1. 17775 .95780 .72985 .5039{) .29095 . llO

I(D 0

. 029

•060• 070•079•084•088.091• 097• 101• 104• 107• 109• 112• 104•095.083•069.054.039

937.915

V/Vco

O1,0141.0306. 034

•039•041.043•045•047•049•051•052.053•055.051•046•041.034.027.019.OlO

] 957

AVofI'_

7. 0702. 2251. _41. 456• 992• 695• 561.478

• 245• 218• 197

• 114• 100.087,075• 062• 059

0" 033


FI(.;_-RE7.-- NACA 64 004 basic thickness form.

12,

.8

(v/_F

.4

J J !

i f !

q .....20 40 6'0 BO IO0

x, percent C

z, percent c y, percent

0.5 0.]O8

•75 .4941.25 .6272.5 .8545.0 1. 1737.5 1,412

lO I. 60815 I. 91620 2. 143Z5 2. 31030 2. 421

35 2, 48340 2. 49645 2. 43550 2. 31655 2. 15260 1. 95065 1. 71770 1. 46075 1. 18680 .9O285 .62190 .35795 .134

100 0

c (viva): t7r_,--7--V-1. 021 1. 0101. 063 1.03l1. 079 1. 0391. 094 1. 0461. 106 1. 0491. 107 1. 0521.112 1.0551. 121 1. 0591. 127 6. 0621. 132 1.0641. 136 1. 066

1. 138 1,0671. 141 1.0681. 632 6. 0641.119 1.0581,104 6. 0511. 086 1. 0421. 067 1. 0331.047 1.0231.023 1.0111.001 1,001

• 975 .987• 949 .974• 922 .960• 895 .946

h l'j I "a,

5.5_2. 2131,8171. 440

.987• 593• 560• 479• 383• 321• 279• 245• 219• 198• i77• 158.142• 127• 113• 099• 086• 074• 061• 048

O' 032

L.E. radius: 0.173 Ix, rcent c

FI(_URE8.--NACA 64 005 basic thickness form•

II

ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- A_N'D 6A-SERIES AIRFOIL SECTIONS 7

{v/v=)2

1.2 --

[ L !

_B A, kl

.4 _

I

i0 20

(v/v=)2

40 60

percent c

m

t80 I00

2". percent c y, percent c

0 0.5 .139.7,5 .165

i. 25 .2112. 5 .3075.0 .4307. 5 .522

lO .60015 .72420 .81825 .89030 .94335 .97940 .99745 .99750 .97455 .92660 .85665 .76870 .66875 .55680 .43585 .30890 .18395 .072

100 0

I'/I'=)_

01. 0171. 025l, 0301, 03,5I. 037I. 0381. 040I. 0421. 0451. 047I. 0491. 0501. 0521. 0541. 0531. 0481.0421. 0351. 0271. 0171.007

•.(}95•983•,_7•948

ITV,

JI. 008I. 012I. 015[. 6171.018[. 019[. 0'20l. 021I. 022[. 023[. 024[. 025[. 026[. 027[. 026L 024[. 021l. O17L 013[. 008[. 003

• 974

15. 9472. 2201. 7801. 401

.994•692•563•478• 381• 321• 277• 245• 218• 196• 177• 159• 144• 130• 116

N1078

• 066• 052

O' 035

L.E. radius: 0.027 percent e

FIGURE 9.--NACA 65-002 basic thickness form.

.8 ' tI

- t

o 20 4o _o so K)ox,percent c

z, percent e g, percent c

0 O• 5 .220• 75 .2C_4

1.25 .3342.5 •4695.0 .6407,5 .788

l0 .9O515 l. 09120 1. 23325 1, 34130 l, 42035 1. 47240 1. 49845 1. 49550 1. 45855 1. 38360 1. 27665 1.14470 .,°Dt75 .82280 .64185 .45390 .26995 ,105

100 0

I. O_

[ 1.041.041. O_1. O_1. O_1. O(1. O_1. O_1.071, 07I• 071.07I. 081.08I. 07I, O_I, 051.031.021.00

• 99• 97• 94• 92

,)_ IVI'=

D1. 0161, 021i. 0241. 0251,0271. 0281. 0301. 032L 0331. 0351. 0361. 0371. 0391. 0401. 0391. 0351.0311. 025I. 0191. 012I. (]04

• 996• 986• 974• 962

V°IV=

9. 0802. 2101. 7931. 406

987693562478381321278245218196177159144130ll6I02089076064

•050O34

O


FIGURE 10.--NACA 65 003 basic thickness form.

569066--61----2

S TECHNICAL REPORT R-84--NATIONAL AERONAUTICS AND SPACE ADMLN'ISTRATION

1.2

.8

(v/v_} 2

.4t

i ! i_' 2'0 40 60 80 I00

x, percenl C

z, percent c y, percent c

0 0• 5 .307

• 75 .370

I. 25 .465

2.5 . _32

5.0 .870

7. 5 1,055

10 1. 212

15 1. 460

20 I. 650

25 1. 79330 1. 897

35 1. 965

40 1. 998

45 1, 991

50 1, 940

55 1, 838

60 1. 693

65 1.5] 5

70 1,309

75 l. 083

$0 .842

85 .593

90 .35 [

95 .136

I00 9

0 O1. 046 1,023

1, 054 1. 027r l, 059 " 1.029

1,064 1. 0321. 071 1. 035

1. 078 1,037

1.081 1.0401. 089 I. 044

1. 093 1. 045

1. 097 I. 047

1. 100 I. 049

I. 103 I. 050

1.106 1. 052

1,109 1. 053

1,108 1,053

I, 097 1. 047

1. 083 i. 041

I. 068 i. 033

1. 051 1. 025

1.031 1,0t51.011 1.005

•989 .994

.964 ,982

.933 .966

.9O2 .950

7.180

2, 188

1. 8001. 407

• 978

• 695

• 561

• 478

• 381

• 321

.279

• 246

.219

• 196

• 17,q

• lfW}

• 144

.129

• 115

• 101

• 088• 075

• 063

•049

• 033

0


FIGVRE ] 1 .--NACA 65 004 basic thickness form.

cv/%)2

f

8I- _

I-

L--.4 I,E_

o 20

J _

w

40 60 80 I00

x, percent c


0 0

.5 .394

.75 .475

1.2_ .5942. 5 .795

5.0 1. 090

7. 5 1. 322

10 1.518

15 1.828

20 2.066

25 2.245

30 2.375

35 2.459

40 2.498

45 2. 487

50 2, 420

55 2.2,90

60 2.106

65 1.881

70 1.62375 1,339

80 1.038

85 .729

90 •430

95 .165

100 0

0 0 5. 720

1.051 1.025 2.152

l. Or_ 1.030 I.,_0

1064 t 1.032 [ 1.402

1.074 1,_3_ .973

1.087 1. 013 .695

1,094 1.046 [ .5601,100 1,049 t .478

1.111 1.054 .381

1.118 1.057 .321t.123 1. OEO .279

1.127 1,062 .246

1. I31 1.063 .219

1.134 1.065 .197

].137 1.066 .178

1. 136 1.066 .160

1.120 1.0.58 .144

1. 103 t.0_0 .129

1. 084 1.041 .114

1.062 1.031 .100

1.038 1.019 .087

1,012 I.O00 .074

.985 .992 .062

.954 .977 ,048

• 917 .95_ .033

.880 ,938 0


FIC, URE 12.--NACA 65-005 basic thickness form.

1

ORDINATES AND PRESSURE DISTRIBUTIONS FOR N'ACA 6- A:ND 6A-SERIES AIRFOIL SECTIORTS 9

1,2

.8

(v/v_?

.4

0 20 40 60 80 I00

percenl c

(V/V¢o

0I. 0181.0341. 0411. 0441.0481. 049I. 0501,0511. 052I. 0521. 053I. 053I. 0521. 0481. 0451. 040I. 035I, 0291. 0221.0141. 007

.998•988

O' 976

1:o17 128301. 020 1. 4501. 022 ,9951. 024 .697I. 024 .5581. 025 ,4811. 025 .3811. 026 .3191. 026 .2771. 026 .2431. 026 .217I. 026 .196I. 024 .1761,022 .158I. 020 .1421. 017 .128I. 014 .115I. 01l .1021,007 .090

1,003 ,078• 999 .065• 994 .052

0' 988 0" 035

x,I_rCellt c y, percent c

0 0•5 .159.75 •196

1,25 .2512.5 .3,505. O ,4867.5 .587

1O .C_815 .79020 , _7725 .93830 .97735 •99640 .99545 .97450 .93655 .88060 .80865 .72470 .63075 .52880 .42485 .31990 .21495 .109

100 .005

L.E. radius: 0.030 percent cT.E. radius: 0.005 percent c

1•2•8 --'------ -

11

0 2O 40 60- 80

_percenf c

i

f_

-_o

z, percent c g, percent c

0 0.5 .242• 75 .295

I. 25 ,3772, 5 .5245.0 .7277. 5 .878

10 .99915 1.183

• 20 1.31525 1. 40830 I. 46735 1. 49549 1. 49345 1. 46150 1. 40055 1,31660 1.2O965 1. 08370 .94075 .78880 .63385 .47690 .31995 .163

100 .007

O7I%)'

t0

• 9931.0481.0571,0641,070].0721.0751,078]. 0801•082 l1.0841.0821.0791.0741.0681.0611.0511.041i. 0301. 0201.0O8

.995•982.967

0

V/I'._

0• 990

I. 0241,028I. 0321. 0341. 0351. 0371. 038I. 0391. 0401.04l1. 0401. 0391,036l. 033l. 030l. 0251,0201,0151,0101. 004

• 997• 99I.983

0

I "o: l "c

I. 320,_,198• 828.435• 990• 697• 500• 4S2• 382• 319• 277• 243

.217• 195.175.158• 142.127.114.101.089.076•064•051.034

0

L.E. radius: 0•067 percent cT.E. radius: 0,008 percent c

FmVRE 13. -NACA 63A002 basic thickness form. FIGURE 14,--NACA 63A003 basic thickness form,

10 TECHNICAL REPORT R-84--NATIONAL AERO-N'AUTICS AND SPACE ADMINISTRATION

.8 _

(v/vj2

O_ 20 40 60 80 I00

percen_ c

z, pertx.nt ¢ y, percent

0 0• 5 .326• 75 .396

1,25 .5032. 5 .6985.0 .9677.5 1. 167

10 1. 32815 1. 57620 i. 75325 i.87830 1. 95835 I. 99540 1.99145 1,94650 1. 86455 i. 75(160 I. 60765 1,43970 1.24975 I. 04680 .84085 .6329_ .42495 .217

lid .009

c (I7t

o

li1.1.1.I.1.1.1.1.1.1.I.1.1.l.1.1.1.LL

O'

3 983

1. 0291. 0351. 0401,0451,0461. 0491. 0511. 0531,0541.0551.0541.0521. 0481. 0441. 0391. 0331. 0271. 0201. 0131. 004

•996•988

0"979

I'./I%

6. 7702.170L 8121. 418•985•696•561.484

:277

• 244.217• 194• 175.158• 141• 126• ll3• 100.088.075

L.E. radius: 0.118 percent cT,E. radius: 0.010 percvnt c

FIGURE ] 5,---NACA 63A004 basic thickness form.

{v/%)z

.4

0

i E v- Y 1

! i i i

[ 1 / i ! ,

20 40 60 8O I00

x, percen_ c

z, percent c y, percent

0 0•5 •412•75 ,496

1.25 .6282. 5 .8715.0 1.2077.5 1,456

10 1,65815 1.96820 2.19125 2.34830 2.45035 2,49640 2.48845 2.43050 2.32755 2,18360 2.(_)365 1.79270 1. 55575 1.30280 1.04585 .78690 .52895 .270

lid .012

• 9401. 0631. 0801. 098

I 1.1131.1181. 1241.1321.1371.1401.1421.1401.1321. 1231.114I. I001. 0841,0671. 048I. 0311.010

• 989•970

O' 948

17V_

O. 970

1. 0311. 0391.048I• 0551.0571. OiD1,0641. 0661.oo8

I. 070I, 0681.0641.0601. 0551. 0491. 041I. 0331. 0241. 0151. 005

O1974

A1"jV,_

5. 4202. 1311. 786I. 400

• 980• 695• 562• 484• 382• 320• 278• 244• 217• 194• 174• 157• 140• 126•112.099• 086.074• 062• 048

O' 033


FIGURE 16. NACA 63A005b'tsic thickness form.

ORDINATESANDPRESSUREDISTRIBUTIONSFORNACA6- AND6A-SERIESAIRFOILSECTIONS l l

(v/vcJ2

1.2

8

4

: Li2O

5̧ A

4O 60

x, percent ¢

i II

80 I00


0 0• 5 .153• 75 .191

1.25 .2452.5 .34[5. 0 .4737.5 .57L

10 .65015 .76920 .85625 .02130 .96735 .99340 I. 00045 .98750 .95055 .89560 ,82565 .74470 ,652

75 .5,5080 .44285 .33290 .22395 . ll3

100 .004

(Iq %)_

01 0201 0331 040I 0431 0451 0461 0471 048

, 049050

I:o51052(052o51i:047

, 042036

l:020023

I:ox6N

989978

0

'7V¢_ AI'o/Vm

0 14. 7381. 010 2. 240I. 016 1, 8501. 020 1. 4701,021 ,992I, 022 .698I. 023 .558I. 023 .481I. 024 .3811.024 .3191.025 .2771.025 .2441.026 .2181,025 .194I, 025 .176I, 023 .1591. 021 .143I. 018 .1291. 014 , 1161. 011 .1021.008 .09O1.004 .078• 999 .065• 994 .0,52• 989 .034

} 0

L.E. radius: 0.028 percent cT,E. radius: 0.005 percent c

FIGURE 17.--NACA 64A002 basic thickness form•

(v/v_? I

____ '

0 2O 40 60 80 I00

x, percent c


0 0.5 .235• 75 ,289

l. 25 .3092. 5 .5t05,0 .7067.5 .851

10 ,96915 L 14820 1. 28225 1. 38030 1,44935 I. 48940 1. 50045 1. 47850 1.42I55 1.33760 1,23265 1.11070 .97l75 .81880 .65785 .49490 .33195 .169

100 .007

0 )1.030 [ 1,015

1.040 [ [. 0231,055 I [, 0271.062 [ [.0311.064 ] 1.0321.066 ] L 0321.008 1.0331.071 / 1.0351. 073 k 030I. 075 [. 037I. 078 :. 0381.079 .0301.080 :. O391. 078 .038I. 070 .034I. 062 ,0311. 054 .0271. 044 .022I. 034 .0171.023 l. Oll1.010 1.005

• 997 .998• 982 .091.967 .983

0 (

•_v./v___

1. 46799069756048t38132O278 j244 I218 I

176 [159142

128 j115

IOl 1

•054.051

)340

i,.E. radius: 0.062 percent cT,E. radius: 0.008 percent e

FmvRE 18.--NACA 64A003 basic thickness form.

12 TECHNIICAL REPORT R-$4--N'ATIONAL AER02fAUTICS AND SPACE ADMINISTRATION

(v/v_)2

.8_ - - I - 1 ii i

-+ +..... ÷ - ._+______i

I

0 2'0 40 " 6'0

x, perceni c

x, percent c

0.5• 75

1.252.55.07.5

I01520253O354045

y, percent c (VIV¢o) 2 1

0 I 1.035

! rose lt 1.o66 I

• _79 ! ].o7o I! 1.082/ 1.o86 I

l 1.os_ [! 1.o94 I/ 1.o9s i/ !.1Ol I| 1.104 ]- 1. 106 '

86 |---_---5o

AI'JV_ !"/V=

)1.0t7I. 026I. 032I. 039I. 0401. 0421. 0441.0461.0481.049I. 051i. 052

5500657O758O859O95

I00

.318• 388• 492

• 9371. 1291. 2861.52fi1. 7081.8391.9311.9852.0O01. 9671.89O1.77g1. 6371. 4721.286I. 082• 868• 652• 438.223• 009

1. 108 1.0331. 105 1.0511.094 I 1.046

1.083 [ 1.0411.071 I 1.0351.059 [ 1,0291.045 [ 1.0221.030 i 1.0151.013 ] 1.006

• 995 .997• 976 I .988

0' 058 t 0" 979

I

2. 1991. 845t. 459

• 985.696• _2• 481.381• 320• 27£.245•219• 196.17fi.158• 142• 12g• 114• 100• 088•076•063•050•033

0

L.E. radius: 0.110 percent eT.E. radius: 0.010 percent c

FmtmF. 19.--NACA 64A004 basic thickness form.

(v/v#_

tt__1

0 210 40

x, percenl c


I0 0

• 5 .402• 75 .487

I, 25 .6102. 5 .8485. 0 1. 1677. 5 1.406

10 1. 60215 1. 90420 2. 13125 2, 29730 2. 41335 2. 48140 2. 50045 2. 4.5650 2. 35855 2. 216

50 2. 03865 1,83170 1. 59775 1. 34380 1.07785 .81190 ,54405 ,278

100 , Ol I

i

0 01. 032 I. 0161,053 I. 0261. 074 1. 0361. 093 1. 0451. I00 1. 049I. 106 I, 0521.111 I.OM1.117 1.0571. 123 1. 0601.127 1,0621.131 1.0f;31,133 1,0641.13,6 1.06,51, 131 1,0631.118 1.057

1. 104 1.05l1.089 1. 0441.073 1. 0361. 055 1.0271.036 1.0181.015 1.007

• 994 .997• 970 .985• 946 .973

0 0

5. 5702.1561. 8311,445

• 982• 695•563• 4£1• 381• 321• 278• 245• 219.197 ,• 176.1,58• 141• 127.113•099•087• 075• 062• 048• 032

0

L.E. radius: 0.173 percent eT.E. radius: 0.0125 percent c

FIGURE 20.--NACA 64A005 b'_sic thickness form.

ORDINATESAN:D PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 13

(v/v_)a .........

.4 . "" -1

..... ....

i I.20 40 60 80 I00

x, percent c


0 0.5 .]40.75 .168

1.25 .2142.5 .3125. 0 .4367. 5 ,527

10 .£_315 .72420 .81825 ,89030 .94435 ,98040 .99945 .99950 .0_055 .93860 .87665 .79970 .70775 .C_380 .48985 .36890 .24795 .120

1OO .004

_(v/v=)

o1. 0171. 0271. 0321.0351. 0381.039

1.04O1. 0421. O441. 0461. 048I. 0501.05tI. 0521. 0511. 0471.0411. 0351. 0281. 0211.0131. 003

• 991• 977

0

.®3111.013 I1.0101. 0171.0101.0191. 0201.0211.022

1.0231.024I. 0251. 0251. 0261.025I. 023I. 0201.0171.0141.0101.0061.001

• 995.988

0

dV,

• 145.220•810.400•980•602• 563•479•380•320• 277• 245.218.196• 178• 160• 144• 129• 116• 103•090•078•065•051•034


12 !

(v/v®) 2

.8 .......

.4 .t_-=-; --]-_ ::=---- ....

i .... I

o' zo 40 6o so toox, percent c


0 0• 5 .223.75 .269

1.25 .3422. 5 .4795.0 .6567. 5 .793

10 .90815 1.09120 1.23125 1.33930 1.41835 1.47140 1. 49845 1.49850 1.46755 1.40460 1.31065 1.19370 1. 05675 .90180 .72985 .55090 •36995 .188

I00 .007


(17V,,_)_ TTIr_ aI'dl"_

01. O301.0431. 0461.0491. 0551. 0581. O601.0C:41. 0681.0711. 0731. 0701. 0781. 0791. 0761. 0701.0621. 0531.0421. 0321.0181. 003

• 988• 968

0

0I. 0161.0211.0231.0241.0271.0291.0301.0321.0331.0351.0361.0371.0381.0391.0371.0341.0311.0261.0211.016I. 0091,001

.994

.9840

I0. 0812. 220I. 812I. 395

• 978• 691• 563• 480• 381• 321• 2,'7• 245.218• 197• 178• 160• 144• 129.115• 102.090• 078• 064• 050• 034

0

FIGURE21. NACA 65A002 basic thickness form. FIGURE 22.--NACA 65A003 basic thickness form.

14 TECHNICAL REPORT R-84--NATIONAL AEHONAUTICS AND SPACE ADMINISTRATION

(v/v_)2

].2 --

.8

..... i _4

[

20 40 60 BO I00x, Dercen? c


0 0,5 .304.75 .368

1.25 .4692. 5 .B475.0 ,8757.5 1. 059

10 1. 21315 1. 45920 1.64,525 1.7R830 1. 89235 1. 96240 1. 99745 1.99650 l. 9:)455 1. S68rio 1,74365 t. 58670 1, 40275 1. 19580 .06785 .72990 .49095 .250

100 .009

(_71'%):

01.0381.0,50l. 0551,061I. 07I1.0761. O801,0871. 001I.0951. 098I. 1011. 1041. 1051. 1011. 0921. 0811,0701.0561. 0411,023I. 003

• _1_3• 958

0

0 7. 337I. 019 2. 2101,025 1.8051. 027 1.389I. 030 .974I. 035 .6901. 037 .5631.039 .4801. 043 .3811.045 .3221. fit6 .2771. 048 .2451. 049 .2181.05l .1981.05l .178L 049 .161I, 045 .1441. 040 .1281.034 .1141. 028 .1011,020 .0891. Ol 1 .077L 001 .063

• 991 .040• 979 .034

0 0

L.E. radius: 0.102 i)ereent cT.E. radius: 0.010 percent c

FICI'aE 23.--NACA 65A004 basic t'hickness" form.

{v/v_)2

' II i

0 20 40 60 80 t00

x, percent c

[x, percent c

0 0.5 .385• 75

I. 25 .5952.5 ._155.0 1.09t7. 5 I. 326

10 I, 51915 1. 82020 2. 05925 2. 23730 2. 36735 2. 45340 2. 49645 2. 494

2. 44055 2. 33100 2,17365 1. 97670 1, 74675 1. ,19780 1, 20385 ,90790 . riO095 .310

100 . O11

y, percent c I(V/V¢_)_ i 1

• 467 1. 050

fl',_ -__A'I"[I'®

.025

.030

.035

.043

.046

ii 0' I.041

1. 0601. 0721,0871. 0941. 099 •048 . 4_01. 109 . 053 . 3821, 11,5 .0,56 .323]. 120 . 058 . 2781. 123 ,060 .2461. 127 .062 ,218L 130 . Of'_ .1981. 132 .064 .1781.128 .062 .161I. 116 ,056 . 1441,102 050 ,1281. 088 043 . 1131. 069 034 . 1001.05O 025 .0881. 028 014 .076

1. 003 001 .002• 978 989 .048• 947 973 .034 !

0 _ 0

L.E. radius: 0,150 percent cT,E. radius: 0.0125 percent c

FIe:URn 24.-- NACA 65A005 basic thickness form.

ORDINATES AND PRESSTJRE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 15

.t74

569066- 61--3

16 TECtINICAL REPORT R--84--NATIONAL AERONAUTICS AND SPACE ADMLNISTRATION

.476

I ig'_'-ili

,494 _ _

_,1 490

,502 .,,.

,498 --_ _".......E_ .496 :,,

o ,492 all::::i::

_-,

.488 _ ....... _::"6

o .480 i

!Iiii!::ti

_il_li[!!!i!.47__ i2_-

,440 _ ....

wm:_ ....

_:::_:!_ _

_,o+-

_tP_

.... i

:::1 :

_iii-

::;M>

i:_il!!li_ili_i!!

iiiitii!_'_'iiiil,_,......

iiiiiiii:iiiiiiiil

4

iiiil

...... F%! Li

>_::i_41it_l;l:_ii;ii

ii4i___ _ i :i:.ii:.ii!ii! i_i::ii:i::,ilii i_i :I (IT!! !llillill iii_i:: i,_i:ii_!i]i:i [!)iil i ii[:;F K!: E?h?i:! :! !;_ i:!i !i;!i}i:! E!:i_ill !ii

! !! ! _ i!_iiiiii_,i_i_,_!ii_i_iiiiiiiiiiiiiiii-_ !•i! {i}i, t_ _ ___iiiii!Li_ ili__'

:_"T _]! !!i!_!!i: !;:: ' ' :ii:

_i

i_511:._

:,=

_ ill!

T;iF;;i

__ iiill

_i,iiil.........

i:iii_!!........

i .....

LKI̧

6 8 I0 12 14 I6 18 20Maximum thickness, f, percent c

(b) x= 15 to 45 percent c.

22

FIGURE 25.--Continued.

ORDINATES AND PRESS'URE DISTRIBUTIONS FOR NACA 6- AXD 6A-SERIES AIRFOIL SECTIONS 17

=-a¢u

E

Eo

E

O

_O

"6rr-

.386_ I 1: _:: _ _

.:582 _ i- 'qi'7,'_

_ :: i 4:.378 _ - --

,374 •..:. .,'! .,.!.... t ::_:: F -i-

:: I :1: :E :t i

.366 _ i__--

<. ! i;l:i.362-_-+-

.424 "- _

9_58

.354 @ _;. i ........... l:J:

.416 -- --_-] _

I

L::R: I ]

.408 _ ......

fff ....i.... _.............404 # _ ' :_ :JJ].:_L_

.460 _ I { , _---=

.400.456 _ L.__

.396 _ I ...... ,'::_I

t ::::

.452 _ .... _[ : t

:z: :1t21: _

.444 _ _Ei _"!;iiii[i4-:

?i:!

.436_ 2 4

(e) _:= 50 to 60 pereen_ c.

FIGVRt.I 25.--C0ntinued.

1S TECHNICALREPORTR St--NATIONALAER0_AUTICSANDSPACEADMINISTRATION

.232

.228

.224

.220

,216

.290

.212

.286

.208

.282

_,1"- .204

d •278

.200".9

.274

E .196r_E .270

2.540

._ .266-o8 .536

"6.£ .262

.332

.258

.321

.254

.250

.320

.316

,312

.308

•3040 4 6 12

:qliii ii;ii! iill _!:I:

_; i12!Iiii!_!i

• . iiiii

NN:;):i]

........... i:;i::_iltill

2iA___ ...........itii

j-

£I:i ili:1 i."

t lq _I:T:i 4:t:

i!iir::i

::!p

J ;t [, :: tI:_I

" ?11_i

'. !i!!1 £_:_i2£i;

:j :p:

i!l..........illill.......

8 I0

Moximum thickness, l, percent c

(d) x=65 to 75 percent c.

1_ l a IZI_.E 25.-- Continued.

2O 22


.026

.022

.068

.018

.064

.060

.056

.120

.052

.116

d

.o .108

.E

E

E5 .104E.90

JooE

,i T6a

"6 .09159

_. ,172

.168

.164

.160

.156

.152

,148

•144 0 6 8 I0 12 14

Maximum thicknesst t, percent c

(e) x=80 to 95 percent c.

FIGURE 25.--Concluded.

16 18 2O 22

20 TECItNICAL I_EPORT R--S/--NATIONAL AEROL'NrA'UTICS AND SPACE ADMINISTRATION

• i_ i!il i: +1_i i_-_ !_ Zi=. :i,_ _i }_: .:: _:: ::::ti_i ::.i:'_5_ _::

292 I I ...... _ ....'_" ......."I :'_

_!_!i_ i-i ..........

++++ ::iiiiiiii_+i+++++++++++++m+"; - _o i

Maximum thickness, I, percent c

i=i

22

(a) x=0.5 to 10 percent c.

Ft(;t+ItE 26.--Variation of rat io of ordinate to maximum thickness with airfoil

maximum thickness for the NACA 64-series airfoil scctions.

ORDINATESANDPRESSUREDISTRIBUTIONSFORNACA6- AND6A-SERIESAIRFOILSECTIONS 21

ii':Xi ! ii:_i

_- _ i:ii iiii ilt_ lfiilJi][ _ " ' <-+' il_

4=

460

"3800 2 4

}777i{_:7i7 ti7774_l:f77LTTTfT_77_fii _Tit;ifi_iitl] _t_i _T_

7!i'ii!!iiiii_!ii}iii}iii!i_i!!iiii!!!!!ii!7ti!ii}ill77iiiii6 8 I0 12 14

Maximum thlckness, #, percent c

....... iliI]f7|i![7!_77:::_;;t_;;;;;,:::;;_

IG 18 20

771:

]!ii

22

(b) x= 15 to 45 percenl c.

FIGURE 26,--C0n! inuod.

22 TECHNICAL REPORT R-84--NATI01_AL AERON-AUTICS AND SPACE ADMINISTRATION

.392

•588

:584

580

.576

.412

.468

.408

.464

.460

.456

.452

,448

.4440

ii!!i!

if! iL

%

iiiilii_iill

_F

2i

±

iii'iliii_i

iiii_i

22!1;!

:i_i:i

d-:{

!1:

2t4

Maximum thickness, t, percent c

(c) x = 50 to 60 pcrcent c.

FIGURE 26.--Contimmd.

18 22

ORDINATESANDPRESSUREDISTRIBUTIONSFORNACA6- AND6A-SERIESAIRFOILSECTION'S 23

.244

.240

.232

268

.264

• 536

.552

.324

•320

.3160 6 8 I0 12 14


(d) x--65 to 75 percent c.

FIGURE 26.--Contiaued.

16

569066--61--4

24 TEC]:INICAL REPORT R-S4--2N_ATI0--N'AL AERONAUTICS AND SPACE ADM'INISTRATION

22

2

ORDI:NATES AiN'D PRESS'URE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 25

$

E

"5

o

[

"B.9

.z2o_ ......................... !_; _ __i! I;;_

.120 HfiiH!

.I 16

.ii2 i;i:

,°_ii•t04 ....

.096 iiii

.092

.088

F_

•084 _f

.080 _

.080 _L-'_

.o76 ;_

,072 _

.068 ....

::!!; _ ii _ ii :ii_!_! i_ per( er :'h

I_ H[_iii t_!!H_HiU;i [ii',:i;J;:;;;i,;?,: i_ i

i!Iiii__[!_i_:':':li'_',!iii

ii"27

iiiiiiiii_ii:$ii,_i;,ii!i[:iiiiIiiiii!!IiiilIii!

Eilili_i_ _!ii_iliiiiiii[!ill[ill;_ii2;;Elf/: ;;;[[ [[[[:: .... :::_:; .......... ::_::::,:,:

":'"_:[i[!liiiiiii_i_i................

::-_:2 i:: iL2 _ L::_i::::!!i:_ :4:-_i{t:L _!: i F F _'Y

:?i_::iii::iii ilil if_t_ii:_..[::i: :_i; ii_ hrfI_+i

;i:q[:iii!i_ f i_i[iilH!!ili:iiii[__i_i_i-"__._ililiIill!i!i

iiiti_i_Liliiii!ii:.ii',;i

:::$:1;!!iH_ i:>J fill

iii,iiii!iiliililii!i !i:

,iiii,iiil,;_

....._....!!iili!!!I!_:_liiiil!iiiiili]:.ii'i ....

,:::::-'!iiiii!tiiii;iii_!iH""_"_._

_ii iiii !!!i

....!.... F:Jiiiiiiiliiiiliiil-i ilIii_ili

]P. I_: f:=[i[iiilf::ilii!i =.:/J!b--+-i.',i'

l_::i_ ':!!!i _:.!1!i_iiil

_ _ i[iiilJl?iiiiili_!tii!Iii_,') ii)_i)i'.ii_iliHiiiiiiiii filli_:-_-,i'.[]i5 _ii.i[iiIiiiii_l[[Ii[![!ii',i

_.i_$ii)

!if_ii[i!!?f_!];4;_i@i;::l_:q;i!_iT!!!ii:i!ilii!i!iil

2 4 6

(a)

_ii?:: iii]iiiii!i!ii[i!fl i_l,_T_ iliil:.[_[!!t

:hii_[i

8 I0 12 14


• =0.5 to 5.0 percent c.

i i !:ifiil16 18

mm::

E![i_H

iiJiif

20 22

F_GurtY 27.--Variation of ratio of or(linatc to maximum thickness with airfoil maximum

thick ne_ for t he NACA 65-series airfoil sect ions.

2_ TECIINICALREPORT R-$4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

=eE3

£

.E

"6.9*6

500 _' '1........_: ...... _i_ .... _ ,-_ ""_ " " - _'i_,,

.496 __/_!__'.. __iii Ii ___'._!t __'_!,_._!_

.492

.488

.416 ....... {....... _::_:: Ti ii!21i!_if _ i

368 ...................... :.:: ......... _ ....i.......

!iiiiiiiii_!i_!' _,_iiiilili _iii,_i!!i

Maximum thickness, t, perceni' c

(b) x= 7.5 to 40 percent c.

IF:_GtTI_E 27.--Cont.inued.

16 18 20 22

ORDINATES AND PRESS'URE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 27

.428

.424

.42O

.408

.404

.444

.488

.440

.484

.48O

.476

• 500

.472

.496

.492o 16 2O 22

2S TECHNICAL REPORT H--84--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION •

.336

.332

.328

.324

.320

.316

.312

x,l- .30B

o .304

E .381

,300

,384

© .296

.380

"6.£

IX:

2

:#!!

.376

.372

.368 ::_

.364

.36O N

.35E

.352

.3480

tiiii_

_ h

it

i?i} *

i::i

6 8 I0 12 14


(d) x = 65 to 70 percen_ c.


18 20 22

I

ORDINATES AND PRESST_'RE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTION'S 29

• 220

.216

.212

.208

.204

.200

.196

_1_.192

.280

u_E .188

E .276

_ .184

o ;272

.180

_5 .2"68

"5.o_

_. .264

.256

.252

.240

• 2360 6 8 I0 12 14

Moximum thickness, t, percenl c

(e) x= 75 to 80 percent c.

FIGURE 27.--Cont inued.

16 18

fi_iifi!!i

i!i!i

ili+

!!i!

20 22

30 TECHNICAL REPORT R-S4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

.038

,,032

.028

.024

.092

.O88

.084

.080

.076==-5

= .072E

o .068E

o .I 56

"_ .152

"6.£

_: .148

.144

,140

.136

.i32

.128

.124

.I2C

L2

!!!ii_

E;E_!E

!f!;!_i!

ft!itli?

ff!ft_=

5_

iii__ ......

|ii:

%,

_ii: li

9oi_

:j £ lii:t:

12 14

:F: !iiii!:: .

•_lt_ lii;;t;;

_11 ? i

8 I0

f!!

16

Maximum thickness, f, percent c

(0 x=85 to 95 percent c.

F1GVnE 27.--Concluded.

' _I ::ij

--i_] S iii _::

_iiiii_,ii!ii!l

_iii!

1

ORDINATES AND PRES'S"URE DISTRIBUTIONS FOR :N'ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 31

f476

iiii_ percent C

,472

.468

.442 _i_;_iii_i i_; !_ i_:i::ii!:-!i _ ' _0_=?_ ] :::i _ :_ i: _

.4.38 :"

"4°° n;:-_l-- .... t :t_ I _I:lI _ I liilil i _iiZ : 2I]:Z i!;i:: i:7:1::2: iiiiii!!!!ii-iii; _]

.592'396 :7 : ;]: ;;;; ::] !i; L. :i_._::!!!! _' ......... !!

334 _2121"%,dJ : :_ :liiilili_iii :;_ iO

o .294..... ....................................................,.......,:,............_ : _ 71 TI_ :!_ !',! ,! i fir :m : ._ _ :_!_ :: : I!i _!............: ;:::t_::t;::1i:?;:_1 ;: :

_ .290

E

.244 . : !!i_;.ii:.ill iii!i!_iiil }; _!!i_®

_ .240

'_ .I 78 ;i_i__i_ i ii i _i!i_ii!iEi il Lii iiv:ii _iil !iil! ElI )i_iii_ iii!i_ ! 2 i!iili

.170

................ ;............. : iii!'iii ; i_!!

•1221 _iq:i tii!!lii;_tmililr

,,Io0_

O80

.o%.-_,-_-_:'::; ..............;: ':, '_,6=.̀........,_,..............,:_'-[_,_Maximum thickness, 2, percentc

(a) x=O.5 to 25 percent c.

Fmt'R_: 28.--Variation of ratio of ordi_mte to maximum thickness with airfoil

maximum thickness for the NACA 63A-series airfoil sections.

569066--61----5


440

436

432

428

.424

468

I i:__I_iiiii__.i_

_i_i _' _i ¸_

il_ _ !i_t_

hi:[:._]

m

g .456E

o _ ii__2- 4ao _

::i

i_iiii

_ !i,_i_i,_

.... _41_:;_#

_pi __' 55

h;

_l;mmmiiii::i_i !__'_ _.iiNiiiii_ _ _

't"! "_ + -_r t: : _ _

ii _ ¸__ ! i ! _ lie _I i !i_!_7,[i_!_._;j!:i ;_L'ii!E:i{

_ii! _ '_:_'_':'_i_ :_ ! _ _'_:_

2 4 6 8 I0 12 14 16Meximum thickness, t. percent c

.496 ili_!llEi_ilii

qT' il

.492 _ ii

48E

(b) x = 30 to 55 percent c.

"FIGURE 28.--Continued.

±--

ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SEC'_IONS 33

.316

.512_

•508 _'_"__

,304

3oo_;F;;

.564 t_m_!l

_'1"-

!!!

:; :: :E _E ......-- .356 ......

E i_Mi i:i

.352 ......._+.

"_ :: :: :Tii:

.9 .348 _-_?_s

.344 m:r_;,

.408 .......

=?!!ii !

.404 _ !:'[ 11

40( ..,

t

.39 i

.39 _

,5880r:::F:_

_ill ii.i;::.].::

iii !::41:_:!::_

"I_ii!

i ,

_i iii

!i!_Iiiii!i_i_iiii___

iiiiil_iil!_;j%;

!i::ifill::i_l ,i_*

_tii; i!i....;iii _ ;i

iii :-i_[i._

lii:

ii;t

_iiltfltl;i!t!!

1!!!i_!: _ !,

ii,li,! i!ii,_.E.iiii

iEI

";:ill! .....

ii i!i_ii!i

Iili !i_

i!!!iii!il iiIfil;_'il

2 4 6 8 I0 12 14

Moximum thickness, ;, percent c

(c) x=60 to 70 percent c.


i_ _. _..........

16


oo4_i_I,_,,,= •

0 . iiF !:_ii!i_:_i_ _:_i-*_...........pe rx_tc _,;.;,

I00

.104 _

.162

158

.154c

.c

E 150._E

214Eo

•210

o

"6 .206,9

.202

.198

.268;

•264

•260

,256

.252

,24E

i__'""_"__'_'_'_'__!_'_I_"_'"_!i

iii!il ......

!I iii __ i :Yit- t

2 4

::: ::: iiii!!: ....

! ;: ]i

x: 1

:::! t+

6 8

_iiiill

H?EH

!!!1!:5

C

i!:i

I0

75

12


iiii,_iliiiiii ,

ii!: ]!!!

iiii:'N

15i!i ?:i_

lliiii_i

!!12214 16

(d) x=75 t,o 100 percent, c.

F_cv_ 28.--Concluded.

ORDINATESANDPRES'SIYlqEDISTRIBUTIONSFORI_AC&6- AND 6A-SEI_IES AIRFOIL SECTIONS 35

.',q.50 _i!=:liiiit_Iii':;'=............"_"_:_:=""J_perce'n?cx -H!!_i : " ÷;_ i I _]

• 426 V/:_ff:_|:ii'ii{::

__4 _i_!!iiiiI_!ii__i!l_i:_!Pifiiii_$ ii4ii!ii !ii !i!ii i}ii ::i:.:"ii i!il j!;i i_!!i;[i_:iiiii)iiii_iii_iil; ilii ii_ _i ;1i::_i[I_

.380

...._iii iil ii?ii::i;iil iii _!i ii! ilY:!i :ii_ii:.iili i]_i!i]]!iii!! i i_i!::

322 ....... "; ........ : ...... ._.,_ .......

.3,

:_ "_. !!!!2!! ,!!_ !!!! it!! if!! !i ........ IF! .... !!!

•" i!ili!il!ili ii!!i!!i!i!i_! i!il!!iii,li'iii; ilil_.280-_ iff!i;;i'_"_'-:.._i.iii!ti!::ii_,ii _i .....................

.234 ....... . ........ .iti i......... iifill 1! '": _::;':_i'_ ..... =:: :t: q::_:. _::r

o 74 ..................... t...........

....i!ii iiii_iiiii.ii!::: iiii_250_ :_:; _i, _ _ i_ '.I 'TO ::_: :: ": '::: ::" "" :F:!!_, ;= =;:., : : _ : I: _:t=_:,: :_::,.:

24 r ,

J20 i _ .................. | ..............

098 .,-_ ............ _ -

':"':_!i!,ii!": _:.iii.75 iiii,'_ , ,,_......._'_i:r': ii:_.;...........094 ' '.............................

084 ................................ i ........

" FH!!::ili:! if ,:_iiiiii!_F:_!i i! iiil !5 i!!i i:i !_iii!_! ! :: :]:


(a) z= 0.5 to 20 percent c.

Flcuas 29.--Variation of ratio of ordinate to maximum thickness with airfoil

maximum thickness for the NACA 64A-series airfoil section_,

36 TECHN'rCAL REPORT R-84--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

=i.444 _i_

.440 i!i! !i!

-_ _i_

......_'_'_*__"I !I.... :: " iii

==.,..ii,ii_i ...........

"= '="_}i===ii='_'_....=

_1 .486 i ".+-

_,=. ";:-='! _'!!"__'""""HI ii i_,I 1i i

4,4'_=:,i_lill_IiililiI!IilI_,,,,,_ililii I =

' =°='"= ! I!I!li "_! i R!II iiii i _'='''_.o==,,._,i IIiI_i _iiiii i! _ i

Maximum lhickne_s, f, percent ¢

(b) x= 25 to 55 percent, c

Flora); 29.--Continued,

i I1

=®5

14 16

ORDINATESANDPRESSURE DISTRIBUTIONS FOR _ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 37

.326

!!p!3181 :=t

.3,4N_iI'!_,,_

:x _: t r:

i;JI_iii_ii.3o6 _ _7

.372 ..

.364 _''_ !::::]

,,., .36o i Jiii iii;

.352

.416 _;; i_ii:i _

7_.408

.404 _::

b _t::: _.4oo FI _t

0 2

!i;@

t?i!H

tt}dfffl'dVi

P:ib:

}@ii:-iiiF?

iii::Ji_i_

:tmH

11:1:11:h

::_ttlii.

_7

-':4:=:;1:

..£.!4

.,+ .....

N_

_ _ _ ltl.....

:"__!i!"_i: :i.kri:

it!i!_ili!,i,;,;i_

......iillylLI_

ili::i • .ii!iii lib:!

!l!l_

_!i}!7 i1:4:_11

t!!!!i!!!

! d"

u_p ::!i i_i ....!_I '

i _:Vt:r:1;;:1:,

ti!i{l 1:::¢:

I_11_ #---:!-

t_+,-t.-¢*,ffit:

}_ h.dilf[

g _t::1

@! ' i'ii!ti4_4s

;ii _!iilili !i!i

i7i!i! _ _!i

• !iliti_i

5'! ......

4 6 0

Ill _li !lf_i_t_il

• . 71_77FI-

lii_!i!i_!ii!iill_,-.... ii!l

i fi!Ff:_ i

I0 I_

Maximum thickness, #, percent c


Flccn_ 20.--Continued.

!_ _

!::':!'_I!_!ii!!_

I'T

__t_i..L. i1114

3S TECHNICAL REPORT R-84_NATIOXAL AERONAUTICS AND SPACE ADMINISTRATION

.168

.164

.160

.152

.224

.276

.272

,26B

.264

.26q

.25t6 8 io .... 12

Moximum thickness, f, percent ¢


Fmrm,: 29. Continued.

14 16

ORDINATESANDPRESSUREDISTRIBUTIONSFOR_N'ACA6- AND6A-SERTESAIRFOILSECTIONS 39

_*-+-+,++*t_+ ..,* ,**. [:::' iI:+ 1" : :7:: "'EZ :'_' ' C _'*

.060 ,"-L'_...............

i .052__ :::;_:::: :__. :::: ::::

0

eJ

o__. k-X!FFTtl_t!iit i7._i7::!

EX............... _ii-_+_-:-22_+..,_-"__.,--+:._--...... :7!;G- #- 4;.:-_

El".! ................ i}ii 7!!!

..............iZ!7-ii7

::T:: .:+:: :::L:

: (e) :::::l::::t::::l

.I00(_:: 2

_ff----+--._ :.:.L::_ _ :_:: :::: ....

:::: ::: :::::!f_!i:::::::::::::::::::::::::::: :::: ::;:

,L! !!i': ......... ii!i__ --.:

::::::::::::::::::::::::::::: ;;

iiii_ = _=:=:

i!;i _7{]_ a_m----:;!;7;I;!_ii_i#i_.... ji

7:.77 -- . - _:_i!_777iti:Xl-V.::lili_Tit7777-;-;g-D-.g-i-k-k-;:gJ_ _+ .... :-,:'" ;.Lg _ .... _T-- LX.+$

4 6 8

Moximum thickness,

_,.+

;.:: *,:::

....... +

:::: E!i_

i!?? :7_)

............-ii":'717111£7-''<'

-::: L:!Liiiiiiiiitiiii . . :_iii

IO 12 14 16

l, percent c

(e) x: =90 _,o ]00 percent, c.

F[GC_RE 29.- Conclu(t.e(t,

569066 61 .... 6

40 TECIINICALREPORTR-S4--NATIOXALAERONAUTICSANDSPACEADMINISTRATION

. _08 _;:t!::_t-;ti!;

30oU t!T_:

.286L.:!:!:L'_.::

,262 .........

.2aoL:II:_I:J!

"_64I_i.L

.120

.116 ( 'l'-'i:_

E : i i_1 llii

Et t : t

o .,, 2 i_ii}};i

J08

oB .104rr'

• • Li!_i!i

;-: - Tti;:: i:._ ;:_ iili_ ;;]! _-

• " "'-" ::ii:"-m .... :F , I

:it:: :ii:{t t_ _ t: ....,,::,-_.......

.096 =-i ": t{_]i ::_J_i}J::J:L iii_; ;I; ;i;i !_: :;i;:::

_0 9 2

..... :L]iiii. _ _i. _-+ ::i: :i -

.084 .........::_": _" _ :;....

.076 _:_ ' : @_:::::: _ :L

.068(_: :_;'ii'iii i !: i2 4 6 8 I0 12 14 16Maximum thickness, f, percent c

(a) z::0.5 tu 10 p_'rccnt c.

FmtT_E 30.--Varialion of ralio of ordina(c (o maximum thickness with airfoil

maximum thickm'_., fur the NACA 65A-_eries airfoil sections.

ORDINATESANDPRESSUREDISTRIBUTIONSFOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 41

500 I "_-• _: ii_:i_ ..... _ _;{iiii ill! _ii iiil iliI iil !i:!ii iii i:,i ii::i:,! ::: :,i ii! il iil ii!iii_:iiii ii!i !i

.-5O2

.498 ill !!i _iiii_ _ i_!iii ,,,

° liii li 488 ii ill

o _= ,........ '........ :!iit:!,i

446450............. ? _i ;_i -,-.._]

• _i _iiiiiiiiii!t'.i !i ii!i:::.ii::i ! i:.i::: _ " i ' :.iiii'.i

,_ " :,iiii;il ::: illi_!ili_!

368 .; ..... _ ............. t::: ; ............. i E _ i _ .....

.364

Maximum lhickness, / percent c

(b) x-]5 to 50 l)erce_t c.

F]G_L'RE 30.--Co_timmd.

42 TECTtN'ICAL REPORT R--S4--NATIONAL AERONAUTICS AND SPACE kD_fINISTRATION

.356 _ !i

.348 i

.336

iili_it .......

:ti................I"_!

X, ' "

.400 _...... _)

:]I '!:_,1--.396_t i

j _l i! .!o .392 _ i_" .ii

.384

.44o _

°

.424

i!

_ '_- 't

--!--- Fii::

...._ _ i..... !!]

i_|::::!i;Vii]i] :!i :.!

: _] !ii

iii!i::_,111 ::_

!!!!!!t!: _

il;tii::il-Vii?iIi:/._dl:I : :

, ::l::l t

..... _ iiti:] I f ::

<: _:t t: ::1:/1 ....

r:;_

!i!

.472

.468

.464

.46C

L :: i :"

g_

t::;h:

2 4 6 8 I0 12

Maximum thickness, /, percent c

14 16

(c) x= 55 to 70 percent, c.

F_c;uas 30. Continued.

1

ORDI_-ATES AND PRESSURE DISTRVBUT[ONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 43

t_ _ .....

_ ....................---*-__- _f_: F:+:_!:::!::: !_ r-_,, t[i_[_il!',_i !'"_............

zoo ::i!: I

:I

.z_z!i!

.... t ....

ill q

.284(_= ::: ;:iil _ i':ili<2

--_ 1:N :!i i:/_ii::il i[ !:/.::_:

--- !2Li2i:i!iJ_i]

_ i;tiiiiii ::i ili. i

•:_i:.<ii::2i !!'_:._=::iiii

iiil:_4 6 8

;:.:iLl_ I'.:L<I_m!i_ili_iiii_i';:1211

; , iiiiiii:iiiilm _ .... _i;:::

............... ili

I0 12 14Maximum thickness, t, percent c

(d) x= ?'.5 to 85 percent c.

FIGURE 30. Continued.

iiii

iii!

I6

44 TECH_'ICAL REPORT R-S4--NATIONAL AEI10NAUTICS AND SPACE ADMINI,_THATION

o

X,

.......... qttl _..,-,,......... --- _oo

..... t-:t_'_ _-. itHi}I ++l ..........

........... t t.,tt."t'" _A:I 2_JJ ,,.,.*,_

tltll!_tlttt_ :if t! d-l_ttll 11tflllttl

,4*' _-_1 t H tl

_+÷_,

.064

N'-

= .060

E

0

w

.05

n_

o

"6 .124O

g

,120

ii'

.116 u_t0 2

_}: _NJH**I_;:M1

4

.,.°, ++_*t_÷+

..... £1h+:rtt_t

"__ ,'IMIH'tl

..... H_I!H

,÷**_ ......

*+H

H__tlt

tM1

_÷÷t_

........ HH_ .......

1::1 ::::: _H;: llth+ll_i:

-_ ...... H;;: :.t.t$",_t ':_' r}

...........6 8 10

Ma×imum thickness, t, percem c

(e) x 90 to ]00 percent c.

]_(;_E 30. Conclu<h'd.

:t:i,e

H- tl trill tt t

*_ [1- HWt_, I 1 t

12

**++,

,+* H

*++*1

,+_,,

N4N

t ;111t !+t'

t_H

14

"2_J4

I

tTl_

RM

16

ORDI_'ATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 45

.012_!,_ _}_ _i_

.0o4 _! _:_._,:ii: i!ii

I_O --= ._

"o o"

_,o__ ,ooE,,=! i_:i_1:!i

0 _ _;

:m

:u: ;11

]ii i_ m: :ii:iI!iiii:_!

__:_i u,_ ::;!l:iliF:qiiiili_:

:::_M::::!ii_i:lii!_:'_ii!t:il!!_:1::::,::::_:!::_

:: series " _F :!::IT::: u::m:: :::: :::, if!! f _T

:t:::' :;J: i1: !!;: !:i ....

.008 u,, ,

.004 iiii

[i:il

2

• :i;ili_ii i![ _ _ 65-series

4 6 8 I0 12

FIOUIIL" 3l.--Variation of the

:::t::::t::: I i::j::;:|::: i:.: :

-+--M_; :2:_ ........ ::4

14 16 18 20 22Mcximum thickness, l, percent c

ralio of leading-edge radius io ma.ximm'n, thickness squared fro" the NACA 63-, 64-, and65-sories airfoil seetlons.

_6 TECttNICALREPORTR--S4--NATIONALAERONAUTICSAND SPACE ADMINIgTRATION

.008

.004

_ !liiIilll _,

'.Li i:H ,_ i

_:t:l I HHZFHIHI:iili ii_iiH_, "LN44"_u'N'_!J"

llil .................

:!!! ......,,:._..._,. ....,,,_.._ .............. ililli+ th]:]_]:r{l_i!!t_

:!:::,';:l[: _: :t it ,. . ,P_,_jT__ -',h'-T

ql q+}:i:_ i::_ ,{i_:::: +_";+H_*IHtHI:III_,}._J:!P.I_h+ .-i{!l i :h

_-_-_-,+,_-._,_,I,,_+::_ .... _',:_

.O08

_g

m

g _ .004

+, !it: , : ,:ttl 4 t :11 4 _ : , : : +,

....m1 _I_tFllu:*_ , t....... :.... t ....

hi_.{H:I

i!i} t!::]

tit: I:_;I

,+HL; '_-

+q+Hgl

008 _: :;_, _"_"_"'_: : " "_I ::i; _;L+ :;; : _ _1 "; t_t !'i'T_

;::;.... i::: : + '_t_J[i::Jl: ..............

....}!i!:}!!!..............::;: iHi_i..............

_I,,:::, ::_:}: :'.Q :I:_lI*i..............

0 2 4 6 8

i',', _:_,l_qJ!ilit:,:_I.

,.I;|:,_ _ ........... i .......ti:, t:: ...... J: ,t ........iF, :I,, _; 1!i +i _" i;i

IO 12 14


IH* *H+;

!!!i ,':.+++:,,,+ +....HH ++++.

_._ _i-_+++.t _++.I_+.+-;;+;.

I::11

.+_

HI_ HIH

tt![ :iI+_[

I}}}il: !

FxavaE 32--Variation of ihe ratio of leading-edge radius 1o maximum thickness squared for tlm NACA 63A-, 64A-, and

65A-series airfoil sections.

ORDINATESANDPRESSUREDISTRIBUTIONSFORNACA6- AND 6A-SERIES AIRFOIL SECTIONS ;47'

I.I i , --

,9 .....

i

IoB -- --

cJ ,7 --

I

• i i

J0 2 4 6 B I0 12 14 16 18 20 22

Moximum thickness,f, percent c

(_} x=0.5 percent c.

F[O_TRE 33.--VarlatioH of static-pressure coefficient with airfoil maximum thicknc_ for the NACA 63-series airfoil _cctiui_s.

48 TECI-1-N'ICAL REPORT R-84--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

t.28

1.24

1.20

1.16

1.12

L08

1.04

.76

.72

(b) x=0.75 to 5.0 percent c.

Fl C,rRF, 33.--Continucd.

20 22

ORDINATESANDPRESSUREDISTRIBUTIONS]:ORNACA6- AND6A-SERIESAIRFOILSECTIONS 49

1.76

1.72

1,68

1.64

1,60

1.56

1.52

_. 1.48

..8

_c_1.44

L40

_ 1.56

o

1,52

1.28

1.24

1.20

1.16

1.12

1.08

1.040

f i - i

!it I SI!:;I-J:tl °-

4 6 8 I0 - 12 14 16 18 20_ 22

Moximum thickness, t, percent c'

(c) x: 7.5 to 30 percent c.

FIGURE 33.--Contimmd.

50 TECHNICALREPORTR--84--NATIONALAERONAUTICSAi'_DSPACEAD:_INISTRATION

1.72

1.6B

1.64

1.60

1.56

1.5;'

1.48

¢,1

8 1.44

_ 1,40c

o 1.5619

IIJ

1.32CI.i

o

1.28

1.24

t.20

1.16

t. t2

1.08

1,04

1.00o

Li-

II

I4

I

I

!

-I,I

I

-p

I

I

V/

i//

/f

---- -- -t--.... k

.....

...... _

-I

-- i

i

I

-- +

I

_l

:II

-÷

i

-- +

I

6

!

2I 5_

-I t '

-- " -', - " i "

_]/ _///]

/4/,

I8 I0 12 t4 t6 18 20 2P

Maximum fhickness, l, percent ¢

(d) x=35 _o 70 percent, c.

F_ e;uaE 33.--Contbmed.

ORDI_*ATESANDPRESSUREDISTRIBUTIONSFORNACA6- AND6A-SERIESAIRFOIL SECTIONS 51


(c) x=75 to I00 percent c.


52 TECHNICALREPORT R-84_NATIONAL AERONAUTICS AND SPACE AD_IINISTRATIOk_T

{,I6 ....

1.12

1.08

1,04

1.00

ORDINATES AND PRESSURE DISTRIBUTI0_S FOR _ACA 6- A_D 6A-SERIES AIRFOIL SECTIOXS 53

1.72

1.68

1.64

1.60

1,56

1.52

1.48

(b) x: 5.0 to 40 percent c.


54 TECHNICALREPORTR--g4--NATIONALAERONAUTICSANDSPACEAD_II'N-ISTRATION

1.64

1.60

1.56

1.52

1.48

1.44

1,40

"" 1.36

g

o_ 132u

tD

°_ 1.28

0

1.z4

1.2o

1.16

1.12

i.o8

I.o4

t.ooo

// ......///

//T

+18B I0 12 14 16

Moximum thickness, f, percent c


i/

/ 1/_°

/I-

.... ]___

!60

1

65

_ _ 70

75

20 22

F]G_TRE 34.--Continued.

ORDINATESANDPRESSUREDISTRIBUTIONSFORNACA6- AND6A-SERIESAIRFOILSECTIONS 55

,o, _[

.96 _ J _

_ \_X8

: 88 \\ _

i .84

u .80

--.68

(d)

"640 2 4 6 8 I0 12 14

X,

16 18 20 22

Maximum thickness, t_ percent c

(d) x=80 to 100 pcrccnt c.

FIGURE 34.--Concludcd.

56 TECIt"NrICAL REPORT R--,gl--NATIONAL AERONAUTIC,% AND SPACE ADM'INISTRATION

(a) x=0.5 to 5.0 percent c.

FIrSt-RE 35.--Variation of static-pressure coefficient with airfoil maximum thickness for the

NACA 65-series airfoil sections.

ORDI-KATESAND PRESSURE DISTI_IBUTIONS T0R N'ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 57

....... 'erce°!-_i 401.64 I

It I/ I_

1.60 //_

-- .- I / /=o

.... A

,.20 _ S

,.,_ ,_7 / I

.... I ]

"'=- ,N_ _ I 1 |,__ -

t

1.08

1.04

(b)

-- - -L ......

4 6 8 I0 12 14 16 18 20 ;)2

Maximum lhickness, #, percent C

(b) x=7.5 to 45 percent c.

]TIGURE 35 --Co,ltinucd.

5S TECtl_'ICAL REPORT R-8,t--NATIONAL AERONAUTICS AND SPACE AD3IINISTRATION

1.64

1.60

1.56

1.52

1,48

1.44

1.40

N

_ 1.36

ig,

1.32

Q)

1.28t

U

O

_ 1.24

1.20

1.16

1.12

1.08

1.04

i .000

. L_L __X,

- percent C----

50 .......,. /

-/

..... -/ /

JF2 4 6 8 I0 12 t4 16 18 20


(c) x= 50 to 75 percent c.


22

l

ORDINATES AND PRESSURE DISTRIBUTI0_TS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTION'S 59

-.........

_ .84

_ .80

.76

,, _l_i......ii!- :-i---i _i L_i _ -1.68 ..... .........................

I I i t , !lj.6Oo-- I . , __ _2 4 6 8 I0 12 14 f6 18 20 22

Moximum thickness, f, percent c


]?[GUI{E 35.--Concluded.

60 TECITXICALREPORTR--84--R'ATIONALAERONA£TTICSANDSPACEADMINISTRATION

1.28--! I i °e,c_oto--

/l_ 2.5 __ .

--_ 1.25

\ :X\

__Ii ;_JL\T L Z_-_

-i__ _ Z¸

_N

I

I

I

I

I

• II

i

I. ---t

i

i

t

16"520 2 4 6 8 t0 _ 12 14


(a) x--0.5 to 5.0 percent c.

FIGURE 36.--Variation of static-pressure coefficient with airfoil


ORDINATESANDPRESSUREDISTRIBUTIOL-N'SFORNACA6- AND6A-SERIESAIRFOILSECTIONS 61

I6 I0


t l !II

12 14 16


FICVaE 36.--Continued.

(32 TECHNICALREPORTR-S4--NATIONALAERONAUTICSANDSPACEAD_fINISTI_ATION

+.24

= _LI6

-

_,112&I

m 1.08

1.44 +

) .40

t.36

i.:..52 .... f -- --

96 .... _ --

I9z __l .....

l

_l_+ .Cc)t i

840_2-- 4-

I.04

).00

_N __

I

]j__ ___

t .... I

t +

- //;

;///l

-- +

_J_ 1

+ --t

""--.4

i

I

--4 -- 4

14Maximum thickness, l, percent c

(c) x= 35 to 95 percent c.

FtacaE 36.--Concluded.

85

16


I. i6 --

1.08

1.04

1.00

\

Ii

Ii

1 J

\

\

.5 I

\\

...... -e.... io - (2Maximum thickness, t, percent ¢

(a) ¢=0.5 to 2.5 percent c.

FtGV_E 37.--Variation of static-pressure coefficient with airfoil maximum thickness

for the NACA 64A-series airfoil sections.

64 TECH.NICAL REPORT R-S4--NATIONAL AERONAUTICS AND SPACE AD_IINISTRATION

1.48

1.44

1.40

1.36

1.32

4--"1,28

ID

_ 1.24

_ L20

1.16

1.12

1.08

1.04

(b)

0 6 I0Moximum thickness, t, percent c

(b) x= 5.0 to 35 percent c.

FIC_TRE 37.--Continued.

I

1


1.48

1.44 --

1.40 --

1.36 --

1.32

1.28 --

1.24

,8 1.20 ---

"E

•_, 1.16 --

_ 1.12 ---

&._ t.08 --

1.04 --

1.00

.96 -

.88 J

:)1.84 0

!

//

/:-//

//

/

--t .... 1 L

i i

I I I2 4 6 8 I0

Moximum thickness, 1, percent c

(c) x =,i0 to 95 pcrceat c.

/

/

/

/

J

t

i

"- I

-_l 1_

l L _Yl2"

i r//r/o

_1- [_

I

I = I

-- ' I 85I

--._. ___

12 14 16

FIGVRE 37.--Concluded.

66 TECtINICAL REPORT R--$4--NATI0_N'AL AEHONAUTICS AND SPACE ADMINISTRATION

1.12

L08

1.04

LO0

t iIO

Maximum thickness,t, percent c

(a) x=0.5 to 2.5 percent c.

12 14 16

FZGVRE 38.--Variation of static-pressure coefficient, with airfoil maximum thickness for the NACA

65A-series airfoil sections.

!11

il

ORDI'N_ATES AND PRESSURE DISTRIBUTI0:NS FOR N'ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 67

1.44


Fm_nn 38.--Continued.

i '

--" 50.

// __ l

. . • _-------_, __ __

i

I

i

14 16

68 TECHNICALREPORTR--S4--NATIONALAERONAUTICSANDSPACEAD._IINISTRATION

1.40

1.36

1.52

t.28

1.24

1.04

1.00

I

'840 2

!

I

6O

65

i

• 70

i !

75

I

8O

9O i1

6 8 Io


(e) x=45 to 9,5 percent c°

t4

FIGurE 38.--Concluded.

ORDr_ATESANDPRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 69

.... 1.2

i ia, 6 8 I0 12 14 16 18 20 22


(a) x=0 percent c.

FIevR_: 39.--Variation of additional velocity-increment ratio with airfoil maximum

thickHcss for the NACA 63-series airfoil sections.

70 TECI-TNICAL REPORT R--84--5:ATIONAL AERONAUTICS AND SPACE ADR{INISTRATION

2.3 ----

2,2 ..... x__ .......\

'\ !

_.o........ \ _- i

1.9 ............ _ !

1.7 ........ -_

"_ 1.5 ................

1.3 ............. ]--! --I

! __i........... !

I,.2 ............. i-- --i

\

I

I

-i

l.O---- __._...._______._._.__

.9 ............

I

__ J

Ii

---J

!(b)

'SO---------2----4 6 B -- io 12Maximum thickness,f, percent

._ __ !

!

i

!

-- -- I

i

_ JI

- 1i

_ J

!

I

i

I14 16

(b) x=0.5 {o 2.5 percent c.

__ ]

.- l .

- -- percent c

\,,

! |

' : t.25

___L_ L_

18 20 2;_


ORDINATES,L\_D PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 71

.72

.68 _--"percent ¢

.64 _

._o .... j ..... _2-

.56

.52

-- .k

7.5: .... + .............

.48 -- --

_1_8 .44 ....

o_ .40

E

.56 ................

.32 --..... 20

.28 _ ---25

.24 .......

.20 l --

.16 ....

.12

.O8

.04 ......

ic, I I0 2 4 6

3OI ....

35

........ 40

5O

--- ___E

_ _ 60

-_ _---1-'-- ..... _---_- 65_

...... _ .... _ _ ___ _-70

85

_95_

8 I0 12 14 16 18 20 22Moximum thickness, t, percent c

(c) == 5.0 to 95 percent c.

FIGVRE 39.--Concluded.

72 TECI-I-NTrCAL REPORT R--$4--iN_ATIONAL AE_0_TAUTICS AND SPACE ADMINISTRATION

!!

iI

14.0

13.6 --

t3.2 --

12.8 --

I2.4 -

12.0 -

_6 11.6 --8

c

_ 11.2 -ID

b

_ 10.8 --- --

_ 10,4 ....

•_ I0.0 - - -

9.6-

9.2- ---

8.8-

8.4 ....

8.0-

7.6 ....

(o)7'20 2

-percert c .....

::]-?

\

L_R __/\ ,

........ _._

l ... = .............

A.

7,6

7.2

6.8

6_4

6.0

5.6

5.2

4.8

4.4

4.0

• 3.6

3.2

- 2.8

2.4

2.0

1.6

1.2

04 6 8 I0 12 14 16 18 20 22

Moximum thickness, 1, percent ¢

.4

(a) x=O percent c.

FZGCRE 40.--Variation of additional velocity-increment ratio with airfoil maximum

thickness for the NACA 64-series airfoil sections.

ORDINATES AI_D PRESSURE DISTRIBUTION'S ]70R R_ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 73

2.4

2.5

2.2

2.1

2,0 n

1.9 --

1.8

_1_"_ 1.7

E

f

\

\

\

1.5

1 ""--

31.2 1

I.I

1.0 _ _

L ___.

.8_ 2 4 6 8

...... __

I

t

i \ i x.-- _ percent c _--

-- _"--1 .75

_- .__) ..... _ _ _ _

ii 11I0 12 14 16 18 20 22

Maximum thickness, t, percent' C


FIfiURE 40.--Continued.

74 TECH'NrCAL REPORT R--S4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

.72

.68

.64

.6O

.56

.52

.48

_1%8 "44

o .40

Ew

._ .56J

"_ .32

'_ .2B

.24

.20

.16

.12

.08

.O4

J

i ' _ " _--percent c

Z5

.... ::x2_

....... i __

_,---_ .....I

t --h

-- ---_ _ 55

-- "---: -_-- 65

q_:_!_i___l it i _ _°2 4 6 8 I0 12 14 16 18 20 22


(e) x=5.0 to 95 percent c.


,I

ORDINATES AND PRESSURE DISTRIBUTION'S FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 75

16.0

8.8

15.6

15.2 8.0

14.1 7.6

ii iZ Z I i : :-i-i " : _-,,., ] _j_ ,2..... i JJJ :,4.° i . _ ' i /i

,3 i L_! _-_ 1-!_i _6.,

4.0

I0., !

I0.0 - 2.8

..... _L- -- jJ_.__ -_L_

1.28'40 2 4 6 8 I0 12 14 16 18 20 22

Maximum thickness, t percent ¢

(a) :_=0 percent c.

FIt3URE 4].--Variation of additional velocity-increment ratio with airfoil maximum

thickness for the NACA 65-series airfoil sections.

15.

o" 12._

12.4

E

' 12.0

11,6

g

_ ..2

76 TECI=INTCAL REPORT R--S4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

2.5 -- i

2.2.

2.1

2.0

1.9

1.8

<_1_'8,._.o"

1.6

._ 1.5 _

_ 1.4 _

1.3

1.2 -

I.I

_.0 - --..__

.9 .......

(b)

.8_ 2 4 6 8 IO

i-\i-

I

i ii-i

I

12

F:

L.

I

I

14 r6 _8 2o 2'z

Maximum Hfickness, L _ercent c


FIG_:RE 41.--Co_tinued.

ORDINATESANDPRESSUREDISTRIBUTr0NSFORNACA6- AND6A-SERIESAIRFOILSECTIONS 77

(c) x=5.0 to 95 percent c.

Ficvr_E 41.--Concluded

78 TECHNICALREPORTR--84--NATIONALAERONAUTICSAND SPACE ADMINISTRATION

,4.01 ,, LT_I, ,, I 1_9.2,4.° [-L L a Lat 88

__ __ L..... L--- _ [ --I I i I I

- " 7 ............

13,2-- : L_ L [ 8.o

,Z.B--- _: .... _ _--I 7.6/

7- I ,

12.4 ............. _7.2

12.0 ............ ,6.8

II.6 -- T ..... .4

_°I "..8 I

o" 11.2-- -- ' rcent c -- -- 6.0

e __ .o ........

10.8 ............ _ 5.6

_ 10.4 ............. _ 5.2

I0.0 -- -- -- 4.8

9.2 .... 4.0

B.B ....... 3.6

L

---- - _-- 3.28.4 -- _ -- /

/

8.o-- _- \ -- - 2.8

_ _ __ _ _1\_

-- - , ---_ 2.o

i 1.66"80 2 4 8 t0 I?_ 14 16

Moximum thickness. ,', _ercent c

(a) x = 0 percent e.

FIGURE 42.--Variation of additional velocity-increment ratio with airfoil

ma×imum t,hickness for the NACA 63A-series airfoil sections.

ORDI57ATESANDPRESSUREDISTRIBUTION'SI_'ORNACA6- AND6A-SERIESAIRFOILSECTIONS 79

2.5

2.2 -- _-

2.1 L

2JO- '--

1.9 - --

1.8

.d i.7 •

r>,

L4 --

1.3 --

1.2 ---

I.I ---

1.0 ----

[b) I

.9 J0 2


Fr_'cRz 42.--Continued.

_0 TECI-L-_TrCALREPORTR--$4mNATIONALAERONAUTICSAI_DSPACEAD_/fINISTRATION

.72

.68

.64

.60

.56

.52

.48

_°_8.44

e"

.40

"E

.56c

"_ .52

.28

< .24

.20

.O8

.04

r :L_

-- __] m

I........ i __

...... 4__ __

!

!

__J_-

_J

i

I !

I

II

..... 1

• __ 21Zi

. -- ___ J

I

Il

k

-- I

i

[c) ' I , /2 4 6 8

Moximum thickness,

X,

- percent C --

.... 5.0

.... L __

!

/

, !|

-4-- __ _ :oI

I ! :s.I

--- --_-t-- -- 35-

-- _-J--I ....... _.0-

_ _1__ I __ __' ; _ _5

I

-- _-- --_ -- _0

_ _ rO

..... )5

_b ,? ,4 ,6t,percent c

(c) x=5.0 to 95 percent c.

I_eURE 42.--Conchtdcd.

ORDINATESAI_TDPREISSUREDISTRIBUTIONSFORNACA6- AI_D6A-SERIESAIRFOILSECTIONS 81

d

E

E

co

14.8 -- --l_" T--

i 1--Ill

it_15,6 --

l&2 --

--_ l( i _

!! ! ]12,8 .....

II I

i2,0 .....

11.6-- ;_i i i

11.2 .....

10.8 -- _ '_-

-- _ i÷-

10.4 ......

I0.0 .....

9,6 ....

9.2 ....

- _, 2

8.8 -- --_ _'

8,4 .....

8.0 ....

--- ] J 1

i ....... _. - 2.0

_o) 17'20 2 4. 6 8 I0 (2_ f4 161"6

Moximum thickness,t, percent c

(a) x=0 percent c.

F_Gv_, 43.--Variation of additional vclocity-increme_t ratio with airfoil


82 TECHNICALREPORTR--8i--NATIONALAERONAUTICSANDSPACEADMINISTRATION

2,4 ..............

2.3 ..... :

.... !

2.2- - -"_--%

2.1 - --_ --_

2.0 ......

1.9 ..... :---

i 1.7 - --

_ - __

i>, 1.6 .....

_ 1.4 ...... _

1.3 ........J

• i-1.2 -

I.I .... J--

L r- I -_i I !--I

i I

! , !

X

./ i\!

-- ! .... t

. ! --- m

Jl ........ _-i

8 I0 12 14 16

(b)

.9_- ..... 2 4 6Moximum thickness, f, percent c

(b) z=0.5 to 2.5 percent c.

FzGunF, 43.--Contlm]ed.

ORDINATES AND PRESSURE DIS'TRIBUTION'S FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS

.72

X,

.68

83

.52:

4 6 8 I0 12Moximum thickness, f, percent c

(c) z=5.0 to 95 percent ¢.

FZGUaE 43.--Concluded.

14 16

84 TECI-L--'_ICALREPORTR--84--NATIONALAERONAUTICSA_*DSPACEADMI'NISTRATI0_,,T

16.4 .......... 9.6

16.0

15.6

15.2 --

14.8 --

i14.4 _

I

i-14.0 -- --

i

6 13.2 I

i 12.8

_ 12.4

_ 12.0

g

_ 11.6

11.2 --

10.8 --

10.4 --

I0.0 --

9.6 --

9.2 --

8.8 o )1

0 2 t0Maximum thickness, t, percent c"

(a) z---0 percent c.

FIGURE 44.--Variation of additional velocity-increment ratio with airfoil


ORDINATESAI%rDPRESSURED1STR'IBUTI01qSFORI_ACA6- AI_D6A-SERIESAIRFOILSECTIONS 85

2.4

2.3

2.2

2.1

2.0

1.9

,, 1.8

1.7oL

m1.6

-5o 1.5

c.9__ 1.4

1.3

1.2

I.I

1.0

.9

•8 o

.1

(b) x=0.5 to 2.5 perccnt c.


86 TECI-IN'rCALREPORTR--84--NATIONALAERONAUTICSANDSPACEADMINISTRATION

i

L. I ll percent CV i----I_---F--- __._ 5.0

.68 ..... _ :.,.__

,60

_ -_ : _!_.52 --

.48 I0

-- i

...... ......

_t_8.44

o"

.40

"E 15

.36 ......

J.... _-4:J_J__,LL

! !.pll J iF -i----tl / I ! _t I _°_

.04 ....... _ i90-

0 2 4 6 8 I0 12 14 16Maximum thickness, f, percent ¢

(c) z=5.0 to 95 percent c.

FIGU!_E 44.--Concluded.

V,S. ;OVERNMERT PRIKTIHG OFFICE:Igll

TECHNICAL REPORT R-84 - NASA · TECHNICAL REPORT R-84 ... mediate to those presented in this...

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