Document
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.
-1
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
percent chord for NACA 63-, 64-, and 65-series
and h'om 2 to 15 percent chord for NACA 63A-,
Basic thickness forms of the NACA 63-, 6_-, 65-
64A-, and 65A-series airfoil sections. In addition,
series and NACA 63A-, 6_A-, 65A-series airfoil
a simplified procedure is presented for obtaining
sections are tabulated for thicknesses of 2, 3,/_, and 5
the pressure dish'ibutions about airfoil sections of
percent chord. Also presented for these thin airfoil
intermediate thicknesses.
sections are theoretical values (_ pressures a_d velocity
ratios required to obtain theoretical airfoil pressure
SYMBOLS
distributions. In. a&lition, for each family of air-
c chord of airfoil
foil sections, cross plots are presented fl'om which
t maximum thickness of airfoil
ordinates and pressure distributions can: be easily
Iz_ free-stream velocity
obtained for airfoil sections of thicknesses inter-
V local velocity at any poin! on airfoil surface
mediate to those presented in this report, in NACA
AV increment of local velocity
Report 824 (from 6 to 21 perce_t chord for the NACA
AI_ increment of local vdot'ity caused t)y
6-series), and in NACA Report 903 (fl'om 6 to 15
additional type of load distribution
perce_tt chord for the NACA 6A-series).
x distance along chord h'om leading edge
y distance perpendi('ular to chord
INTRODUCTION
DISCUSSION
In order to minimize the wave drag of super-
sonic aircraft, the wings and tail surfaces are
The basic thickness forms for the NACA 63-,
designed with the use of airfoil sections thinner
64-, 65-series and NACA 63A-, 64A-, 65A-series
than 6 percent chord. Ordinates for only a few
airfoil sections with thicknesses of 2, 3, 4, and
of these thin airfoils are published and these are
5 percent chord arc presented in tim tables'of
not conveniently located in a single report. This
figures 1 to 24. For tho 6A-series airfoil setqions,
report will supplement the information presented
where a trailing-edge radius is specific(l, an ordinate
in references 1 and 2 and provide the ortlim_tes of
is presented for the 100-percent-c]|ord station
additional airfoil sections useful in design of
to serve as a guide in fairing the rear portion of
supersonic aircraft.
the airfoil. The theoretical methods of references
The information presented in this report in-
1 and 2 were used to derive the 2-percent-tlfick
ch|des tabulated ordinates for symmetrical NACA
airfoil sections of the NACA 63-, 64-, 65-series
6- and 6A-series airfoil sections with thicl,messes of
and the NACA 63A-, 64A-, 65A-series families,
2, 3, 4, and 5 percent chord and a simplified
respectively. Althot|glt not exactly corre(.t,
method of obtaining ordinates for any thickness
ordinates for thickness ratios intermediate to
intermediate to published values from 2 to 2l
those presented in references I and 2 and in the
Supersedes NACA Technical Note 4322 by Elizabeth V,_. Patterson and Albert L. Braslow, 1958.
TECHNICAL REPORT R--84--NATIONAL AERONAUTICS AND SPACE ADMIN'ISTRATION
(2) The distribution corresponding to the design
present report can be obtained for all practiced
load distribution of the mean line (AV/V_)
purposes by the following method which was
(3) The distribution corresponding to the addi-
used to obtain the ordinates for the 3-, 4-, and
tional load distribution associated with angle of
5-percent-thick airfoil sections tabulated herein.
attack (AI'./V_)
For each family of airfoils, the ratio obtained by
Values of the velocity-increment ratio _V/V_
dividing the ordinate y at each chordwise station
are presented in references 1 and 2 and wdues
by the maximum thickness t is plotted against
of the velocity ratio V/V_ and the velocity-
the airfoil ma_mum thickness in percent airfoil
increment ratio AI-/V_ are tabulated in figures
chord as presented in figures 25 to 30. From
1 to 24. For each family of airfoil sections,
these cross plots, the ratio y/t at each ehordwise
vMues of (V/V_) _ and AI_/V,_ for intermcdiate
station can be obtained at, the desired wdue of
thicknesses can be obtained from figures 33 to 44.
maximum thickness. V_dues of the ratio of the
In these figures, (I'/V_) 2 and AI_/V_ arc plotted
leading-edge radius to the maximum thickness
as a function of the maximum airfoil thickness
squared as a function of maximunl thickness t
t in percent chord for each chordwise station.
are presented for the NACA 6-series and 6A-series
Careful comparison of the ordinates and pressure
airfoil sections in figures 31 and 32, respectively.
ratios tabulated in references 1 and 2 with the
Addition of a cambered mean line to the basic
faired cross plots of figures 25 to 44 shows some
thickness form is accomplished with the use of
discrepancies. Although these discrepancies are
the mean-line data of references 1 and 2.
small enough to be disregarded for all practical
The theoretic_d pressure distributions, indicated
purposes, the values obtained from the faired
by (V/V+) _, for each of the symmetrical airfoil
cross plots are preferred for design considerations.
sections presented are also tabulated in figures 1
to 24. in order to obtain the theoretical pressure
LANCLEY l_ESEARCH CENTER,
distributions for these airfoil sections at angles
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION, of attack and/or with cambered mean lines, the LANCLEY FIELD, VA._ A_g_sl 25, 1958.
procedure described in reference 1 can be used.
REFERENCES
In this method of calculating the pressure dis-
tributions, the velocity distribution about an 1. Abbott, Ira II., Von Doenhoff, Albert E., and Stivcrs, Louis S., Jr.: Summary of Airfoil Data. NACA
airfoil section is considered to be composed of
Rcp. 824, 1945. (Formerly NACA WR L-560.)
the following three separate and independent
2. Loftin, Laurence K., Jr.: Theoretical and Experimental components : Data for a Number of NACA 6A-Series Airfoil
(l) The distribution corresponding to the
Sections. NACA Rep. 903, 1948. (Supersedes NACA TN 1368.)
velocity distribution over the basic thickness
form at, zero angle of attack (V/V=)
II
ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 3
1.2 ]•2 ......
.8
(v/v=) z
(v/v®)2
.4 i J 20 40 60 80 I()0 0 0 20 40 60 80 I00 x, percent c x, percent c z, Percentc Y, percent c AI',tI'_ .r, percent c y, l_'rccnt c (ITVo)t '7 T "¢_ AI'o/V_ (171"_)2 _171"_ O _----'-- _ I 0 0 14.1{'¢1 0 0 9.083 .5 .158 2. 262 1.028 1.014 .5 .243 .011 247 .75 •198
1. 740 1.032 1.016 1•o li
.75 _ .300 1. 042 • 021 77O 1.25 ._54 1. 353 1.037 1.018 1.25 .383 1. 054 _ : •027 377 2.5 •352 • 998 1.045 1.022 2.5 ,528 1. 065 : .032 995 5.0 .489 • 703 1.049 1.024 5.0 .732 I. 071 :. 035 7OO 7.5 .590 •558 1,050 1.025 7.5 .884 I. 074 :.O36 10 .671 •480 1.051 1.025 10 1. 006 1. 076 :. 037 15 .796 • 380 1.052 1.026 15 1. 193 1. 079 • 039 382 5_) .885 1. 053 1.026 • 320 20 1. 327 i. 081 • 040 321 2.5 .946 1. 054 1. 027 • 277 25 1,420 I. 083 •041 27,8 30 .983 1. 055 1. 027 • 245 30 1. 476 I. 084 .041 245 35 .999 • 218 1. 055 1. 027 35 l, 499 I. 082 • 040 218 40 .903 1,053 1.026 •195 40 I. 489 1. 080 .039 195 45 .965 1. 050 1. 025 • 175 45 1. 445 1. 074 • 036 175 50 .916 1.045 1.022 • 158 50 1.37l 1.068 • 033 158 55 .850 1.039 1.019 • 143 55 1.27l I. 058 • 029 142 60 .769 1.033 1.016 .128 60 1.149 1.049 .024 127 I .115 65 .676 1.0_5 1.012 65 1. OO8 1.037 .018 114 ] • 102 70 .573 I. 018 1. 009 70 .853 1.02.5 ,012 75 .463 1.009 1.004 • 090 75 .688 1.012 006 .077 80 .350 .999 .999 80 .520 • 998 ,999 • 065 85 .239 • 989 .994 85 .354 .0_3 ,991 90 .136 • 050 .979 .989 90 .201 .968 ,984 049 95 .051 • 035 .969 • 984 95 .074 • 954 977 034 100 0 0 • 958 .979 IOO 0 • 939 ,969 ( L.E. radius: 0,045percent c L.E. radius: 0.072percent c FmuR_I. NACA63 002 basic thickness form.
FIGURE 2. NACA 63 003 I)'_sic thickness form.
4 TECHNICAL REPORT R-84--h_ATI01_AL AERONAUTICS AND SPACE ADMINISTRATION 1,2-- .8 1 -- i i .8 - t i - :
{v/v_)2
.4 <_---_-- --- I i
II I
__i--. I 60 80 i00 I00 0 20 40 0 20 40 60 80 x, percent c x, percent ¢ I y, percent c (171"_? 17V_ Al'dl'_ x, percent c x, percent c y, percent e (l'(I'¢o)2 : T_rl"_ 2_1"0/I",_.
I
0 5. 353 0 0 0 0 0 6,711 0 0 .417 • 994 • 997 2. 169 .5 .5 .330 1. 010 1,005 2. 212 1,052 1. 026 1,799 • 75 .600 • 75 .404 1. 049 1.02t 1. 789 1,077 1. 038 1. 403 1.25 • f)42 t. 25 .513 1. 068 1. 033 1.395 1. 098 1. 048 • 987 2.5 • 881 2. 5 ,705 1. 082 1.044) .991 1. 111 1,054 • 694 5.0 1,220 5, O .976 1. 091 1.120 1.058 • 561 7.5 7. 5 1,178 1. 097 1. 047 .560 i 1. 472 1.124 1. 060 • 483 1.045 .606 10 ]0 I. 341 1. 100 1,049 .482 i 1. 676 15 1. 988 1. 133 1. 064 • 383 I. 052 .383 15 1. 590 1,106 • 322 2O 2, 213 1,137 I. 066 1. 053 .321 20 1,770 1.109 • 279 25 2. 308 L 141 1. 068 1. 055 .278 25 1. 894 1.112 • 245 30 2. 462 1,143 I. 069 I. 055 .245 3O t. 969 1.114 • 218 35 2. 500 1. 141 1. 068 1,054 .218 35 2. 000 I. Ill • 195 40 2.47g 1. 136 1. 066 1,053 .195 40 1.984 1.108 • 175 45 2. 401 l.l_ 1.061 1. 049 .175 45 1.924 1. 100 • 158 5O 2, 274 1.114 1. 055 1. 045 .158 1. 824 1.09l 1. 047 • 141 55 2. 104 1,097 1. 078 ]. 038 ,142 55 1. 689 1.080 1. 039 • 126 6O 1, S97 1.065 1.032 .127 6() 1. 525 1. 061 1.030 • 112 65 1. 661 1.049 L024 .113 65 1. 336 1. 040 1.020 •099 70 1. 401 70 1.129 I. 033 1. 016 .100 1.018 1. OO9 •086 75 1.128 1,015 1. 007 .087 75 ,910 • 995 • 997 • 074 80 • 849 .997 • 998 .075 80 .686 • 972 • 986 .061 85 • 576 • 978 • 989 .063 85 ,406 .324 • 947 • 973 • 047 9O • 958 •979 .048 90 .203 • 924 • 96L • 032 95 • 118 • 939 •969 ,033 95 .096 • 902 • 960 0 100 0 • 921 •060 0 IOO 0 L.E. radius: 0.200 percent c L.E. radius: 0.12_ percent e FIGURE 4,--NACA 63 005 basic thickness form.
FIGURE 3.- NACA 63 004 t,a_ic thickness form.
ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 5 1.2 1.2 .8 ---- • 8 --
¢v/_) z ( v/v¢o )2
I00 0 80 I00 0 20 4O 60 80 20 4O 6O x, percenl C x. percent ¢ z, percent e y, percent c (I'/1"=, T ., Vof 1 _¢ (TTV_: 17V_ a VolV, x. percent c y, percent c o o 0 14.451 9. 750 0 "L 0 " } ,5 .149 .028 1. 021 2. 210 1.014 2. 223 .5 ,, .2,35 .75 .188 1,033 1. 860 .75 .288 1. 051 I. 025 I. 860 1.25 ,246 1,042 1. 465 1.058 I. 029 i. 465 1.25. .372 2. 5 .344 1.0_-5 • 998 1. 063 1. 031 • 995 2. 5 : .515 5.0 .480 I, 048 • 697 5.0 .712 1. 066 [. 032 • 696 7. 5 .575 I. 049 • 562 1. 068 [. 033 • 561 IO ,6.54 I, 049 17.0 5 "' .973"856 • 478 1. 070 [. 03,1 • 478 15 .775 I. 050 • 380 15 1.156 1. 072 L, 035 • 381 20 .863 1. 051 • 320 _1 1.291 1. 075 I. 037 • 320 25 .928 1. 051 .277 _ 1.389 1. 077 I. 038 • 278 1. 052 .245 30 1.455 1. 079 [. 039 • 245 30 ,::i .971 35 •995 1. 053 • 218 35 1.49I I. OgO i. 039 • 218 40 .999 1.054 • 196 40 1.499 I. 081 L, 040 • 197 45 .976 1.052 • 178 45 1.463 1. 078 [. 038 • 178 50 .93l 1.048 • 158 50 1.395 1. 071 l, 035 • 158 55 .867 1. 042 • 142 55 1,298 1. 063 [.031 • 142 60 .790 1.036 • 128 60 1.180 1. 053 i. 026 • 128 65 .699 1.02_ . I15 65 1.043 1. 041 1.020 • I14 70 ?597 1. 020 • 102 70 .889 1. 030 t. O15 • I01 75 .487 1. Ol I .089 L 007 • 088 75 .724 1.015 80 .372 1.002 .078 1.002 [. 001 • 076 80 .553 85 .258 • 992 .065 • 987 • 093 .063 85 .382 90 .150 • 983 • 052 • 972 • 986 .0_ 90 .221 95 .058 • 970 • 953 • 976 95 .084 0' 035 100 0 O" 034 ,955 • 935 • 907 100 0 L.E. radius: 0,028 percent e 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 12, 1.2
t
.8 .8
J J !
(v/_F
(v/v®lz
.4 .4
i f !
q .....
20 40 6'0 BO IO0
4O 6O 8O I00
2O x, percent c x, percent C x, percent c y, percent c V/Vco AVofI'_ z, percent c y, percent h l'j I "a, c (viva): t7r_,
--7--V-
0 0 O 7. 070 5.5_ . 029 0.5 0.]O8 • 5 ,322 1,014 2. 225 1. 021 1. 010 2. 213 .75 .391 •060 1.030 1. _4 •75 .494 1. 063 1.03l 1,817 1.25 .,500 • 070 6. 034 1. 456 1.25 .627 1. 079 1. 039 1. 440 2.5 .£_5 •079 •039 • 992 2.5 .854 1. 094 1. 046 .987 5, 0 ,943 •084 • 041 • 695 5.0 1. 173 1. 106 1. 049 • 593 7.5 I, 134 • 088 .043 • 561 7.5 1,412 1. 107 1. 052 • 560 10 1. 290 .091 • 045 .478 lO I. 608 1.112 1.055 • 479 15 1,536 • 097 •047 15 I. 916 1. 121 1. 059 • 383 2_) 1,717 • 101 • 049 20 2. 143 1. 127 6. 062 • 321 2;_ 1. 849 • 104 • 051 Z5 2. 310 1. 132 1.064 • 279 30 1. 938 • 107 • 052 • 245 30 2. 421 1. 136 1. 066 • 245 35 1. 987 • 109 .053 • 218 • 219 35 2, 483 1. 138 1,067 40 1. 997 • 112 •055 • 197 40 2. 496 1. 141 1.068 • 198 45 1.9,50 • 104 .051 45 2. 435 1. 632 6. 064 • i77 50 6.857 • 095 •046 50 2. 316 1.119 1.058 • 158 55 1+ 726 .083 • 041 55 2. 152 1,104 6. 051 .142 60 I. ,567 • 069 .034 60 1. 950 1. 086 1. 042 • 127 65 6. 352 .054 .027 • 114 65 1. 717 1. 067 1. 033 • 113 70 1. 177 .039 .019 • 100 70 1. 460 1.047 1.023 • 099 75 .957 .OlO .087 75 1. 186 1.023 1.011 • 086 80 .729 ,075 80 .9O2 1.001 1,001 • 074 85 .503 • 062 85 .621 • 975 .987 • 061 9{) .290 • 059 90 .357 • 949 .974 • 048 95 . llO 937 95 .134 • 922 .960 0" 033 O' 032 I(D 0 .915 ] 957 100 0 • 895 .946 L.E. radius: 0.160 percent c L.E. radius: 0.173 Ix, rcent c FI(.;_-RE 7.-- NACA 64 004 basic thickness form.
FI(_URE8.--NACA 64 005 basic thickness form•
II
ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- A_N'D 6A-SERIES AIRFOIL SECTIONS 7 1.2 -- [ L !
_B .8 ' t I
A
, k
{v/v=)2 - t
(v/v=) 2
l .4 _ m
I
i
t
0 20
40 60 80 I00 o 20 4o _o so K)o
percent c x, percent c 2". percent c y, percent c I'/I'=)_ ITV, z, percent e g, percent c ,)_ IVI'= V°IV= 0 0 0 O D 9. 080 0 J 15. 947 .5 .139 1. 017 • 5 .220 I. O_ 1. 016 2. 210 I. 008 2. 220 .7,5 .165 1. 025 • 75 .2C_4 1, 021 1. 793 I. 012 1. 780 [ 1.04 i. 25 .211 l, 030 1.25 .334 1.04 i. 024 1. 406 I. 015 1. 401 2. 5 .307 1, 03,5 [. 617 2.5 •469 1. 025 987 .994 1. O_ 5.0 .430 I. 037 1.018 •692 5.0 .640 1. O_ 1,027 693 7. 5 .522 I. 038 [. 019 •563 7,5 .788 1. O_ 1. 028 562 lO .600 1. 040 [. 0'20 •478 l0 .9O5 1. O( 1. 030 478 15 .724 I. 042 l. 021 • 381 15 l. 091 1. O_ 1. 032 381 20 .818 1. 045 I. 022 • 321 20 1. 233 1. O_ L 033 321 25 .890 1. 047 [. 023 • 277 25 1, 341 1.07 1. 035 278 30 .943 I. 049 [. 024 • 245 30 l, 420 1, 07 1. 036 245 35 .979 1. 050 [. 025 • 218 35 1. 472 I• 07 1. 037 218 40 .997 1. 052 [. 026 • 196 40 1. 498 1.07 1. 039 196 45 .997 1. 054 [. 027 • 177 45 1. 495 I. 08 1. 040 177 50 .974 1. 053 [. 026 • 159 50 1. 458 1.08 1. 039 55 .926 1. 048 L 024 • 144 55 1. 383 I. 07 1. 035 60 .856 1.042 [. 021 • 130 60 1. 276 I, O_ 1.031 1. 025 ll6 65 .768 1. 035 l. O17 • 116 65 1.144 I, 05 70 .668 70 .,°Dt 1.03 I. 019 I02 1. 027 L 013
N
75 .556 1. 017 75 .822 1.02 1. 012 089 [. 008 80 .435 1.007 [. 003 1078 80 .641 1.00 I. (]04 076 85 .308 •.(}95 85 .453 • 99 • 996 064 • 066 90 .183 • 983 90 .269 • 97 • 986 •050 • 052 95 .072 •,_7 95 ,105 • 94 • 974 O34 O' 035 100 0 •948 • 974 100 0 • 92 • 962 O L.E. radius: 0.027 percent e L.E. radius: 0.061 percent c FIGURE 9.--NACA 65-002 basic thickness form. FIGURE 10.--NACA 65 003 basic thickness form.
569066--61----2 S TECHNICAL REPORT R-84--NATIONAL AERONAUTICS AND SPACE ADMLN'ISTRATION 1.2 f .8 8I- _
J _
I-
cv/%)2
(v/v_} 2 t L-- w .4 .4 I,E_ i ! i
_
' 2'0 40 60 80 I00 40 60 80 I00 o 20 x, percenl C x, percent c z, percent c y, percent c z, percent c y, percent c 0 0 0 0 5. 720 0 O 7.180 0 0 1. 046 1,023 .5 .394 1.051 1.025 2.152 • 5 .307 2, 188 .75 .475 l. Or_ 1.030 I.,_0 • 75 .370 1. 800 1, 054 1. 027 1. 407 1.2_ .594 1064 t 1.032 [ 1.402 I. 25 .465 r l, 059 " 1.029 2. 5 .795 • 978 1.074 1,_3_ .973 2.5 . _32 1,064 1. 032 5.0 1. 090 1. 071 1. 035 • 695 1.087 1. 013 .695 5.0 .870 7. 5 1. 322 1. 078 1,037 • 561 1,094 1.046 [ .560 7. 5 1,055 10 1.518 1,100 1,049 t .478 1.081 1.040 • 478 10 1. 212 15 1.828 1.111 1.054 .381 1. 089 I. 044 • 381 15 1. 460 20 2.066 1.118 1.057 .321 1. 093 1. 045 • 321 20 I. 650 t.123 1. OEO .279 25 2.245 1. 097 I. 047 .279 25 1. 793 1.127 1,062 .246 30 2.375 30 1. 897 1. 100 I. 049 • 246 1. I31 1.063 .219 35 2.459 35 1. 965 I. 103 I. 050 .219 1.134 1.065 .197 40 2.498 40 1. 998 1.106 1. 052 • 196 ].137 1.066 .178 45 2. 487 45 1, 991 1,109 1. 053 • 17,q 1. 136 1.066 .160 50 2, 420 50 1, 940 1,108 1,053 • lfW} 1.120 1.0.58 .144 55 2.2,90 55 1, 838 I, 097 1. 047 • 144 1. 103 t.0_0 .129 60 2.106 60 1. 693 1. 083 i. 041 .129 1. 084 1.041 .114 65 1.881 65 1.5] 5 I. 068 i. 033 • 115 1.062 1.031 .100 70 1.623 70 1,309 1. 051 1. 025 • 101 75 1,339 1.038 1.019 .087 75 l. 083 1.031 1,0t5 • 088 80 1.038 1,012 I.O00 .074 1.011 1.005 • 075 $0 .842 85 .729 .985 .992 .062 • 989 .994 • 063 85 .593 90 •430 .954 .977 ,048 .964 ,982 •049 90 .35 [ 95 .165 • 917 .95_ .033 .933 .966 • 033 95 .136 100 0 .880 ,938 0 .9O2 .950 0 I00 9 L.E. radius: 0.170 percent c L.E. radius: 0.109 percent c FIC, URE 12.--NACA 65-005 basic thickness form.
FIGVRE ] 1 .--NACA 65 004 basic thickness form.
ORDINATES AND PRESSURE DISTRIBUTIONS FOR N'ACA 6- A:ND 6A-SERIES AIRFOIL SECTIORTS 9 1,2 .8 i
(v/v_?
1•2•8 --'---- -- - .4 f_
0 20 40 60 80 I00 40 60- 80 -_o
0 2O percenl c _percenf c (V/V¢o x,I_rCellt c y, percent c z, percent c g, percent c V/I'._ I "o: l "c O7I%)' t 0 0 0 0 0 0 0 I. 320 I. 018 • 5 .159 .5 .242 • 993 • 990 ,_,198
1:o17 12 830
1.034 .75 •196 • 75 .295 1.048 I. 024 • 828 1,25 .251 1. 041 1. 020 1. 450 I. 25 ,377 1.057 1,028 .435 2.5 .3,50 1. 044 1. 022 ,995 2, 5 .524 1,064 I. 032 • 990 5. O ,486 1.048 1. 024 .697 5.0 .727 1,070 1. 034 • 697 7.5 .587 1. 049 I. 024 .558 7. 5 .878 ].072 1. 035 • 500 1O . C_8 I. 050 1. 025 ,481 10 .999 1.075 1. 037 • 4S2 1,051 15 .790 1. 025 .381 15 1.183 1,078 1. 038 • 382 1. 052 1. 026 .319 20 , _77 • 20 1.315 ]. 080 I. 039 • 319 I. 052 1. 026 .277 25 .938 25 1. 408 1•082 l 1. 040 • 277 1. 053 1. 026 .243 30 .977 30 I. 467 1.084 1.04l • 243 I. 053 1. 026 .217 35 •996 35 1. 495 1.082 1. 040 .217 I. 052 I. 026 .196 40 .995 49 1. 493 1.079 1. 039 • 195 1. 048 I. 024 .176 45 .974 45 1. 461 1.074 1,036 .175 1. 045 1,022 .158 50 .936 50 1. 400 1.068 l. 033 .158 1. 040 I. 020 .142 55 .880 55 1,316 1.061 l. 030 • 142 I. 035 1. 017 .128 60 .808 60 1.2O9 1.051 l. 025 .127 65 .724 I, 029 I. 014 .115 65 1. 083 1.041 1,020 .114 1. 022 70 .630 I. 01l .102 70 .940 i. 030 1,015 .101 1.014 1,007 .090 75 .528 75 .788 1. 020 1,010 .089 1. 007 80 .424 1,003 ,078 80 .633 1.0O8 1. 004 .076 .998 85 .319 • 999 .065 85 .476 .995 • 997 •064 •988 • 994 .052 90 .214 90 .319 •982 • 99I •051 95 .109 95 .163 .967 .983 .034 O' 976 0' 988 0" 035 100 .005 100 .007 0 0 L.E. radius: 0.030 percent c L.E. radius: 0•067 percent c T.E. radius: 0.005 percent c T.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
i E v- Y 1
! i i i
[ 1 / i ! , .8 _
{v/%) z
(v/vj 2
.4 0 20 40 60 8O I00 O_ 20 40 60 80 I00 x, percen_ c percen_ c 17V_ A1"jV,_ I'./I% z, percent c y, percent z, pertx.nt ¢ y, percent c (I7t 5. 420 6. 770 0 0 0 0 o O. 970 3 983 •5 •412 • 940 2. 131 2.170 • 5 .326 •75 ,496 1. 063 1. 031 1. 786
li 1. 029 L 812
• 75 .396 1.25 .628 1. 039 I. 400 1. 1. 035 1. 418 1. 080 1,25 .503 2. 5 .871 1.048 • 980 1. 1. 040 •985 1. 098 2. 5 .698 5.0 1.207 I• 055 • 695
1. 1,045 •696 I 1.113
5.0 .967 7.5 1,456 1.118 1.057 • 562 I. 1,046 • 561 7.5 1. 167 10 1,658 1. 124 1. OiD • 484 1. 1. 049 .484 10 1. 328 15 1.968 1.132 1,064 • 382 1. 1. 051 15 1. 576 20 2.191 1.137 1. 066 • 320 1. 1. 053 20 i. 753 1.oo8 • 278 :277 25 2.348 1.140 1. 1,054 25 i. 878 • 244 30 2.450 1.142 I. 070 1. 1.055 • 244 30 1. 958 • 217 .217 35 2,496 1.140 I, 068 35 I. 995 1. 1.054 • 194 • 194 40 2.488 1.132 1.064 40 1.991 I. 1.052 1.060 • 174 • 175 45 2.430 1. 123 45 1,946 1. 1. 048 1.114 1. 055 • 157 1. 044 .158 50 2.327 50 1. 864 1.
I. I00 1. 049 • 140 • 141 55 2,183 55 i. 75(1 l. 1. 039 1. 084 1. 041 • 126 • 126 60 2.(_)3 60 I. 607 1. 1. 033 1,067 I. 033 •112 1. 027 • ll3 65 1.792 65 1,439 1.
1. 048 1. 024 .099 1. 1. 020 • 100 70 1. 555 70 1.249 I. 031 1. 015 • 086 L 1. 013 .088 75 1.302 75 I. 046 80 1.045 1.010 1. 005 .074 L 1. 004 .075 80 .840 85 .786 • 989 • 062 •996 85 .632 • 048 90 .528 •970 •988 9_ .424 95 .270 95 .217 O' 948 O1974 O' 033 0" 979 lid .012 O' lid .009 L.E. radius: 0.185 percent c L.E. radius: 0.118 percent c T.E. radius: 0.013 percent c T,E. radius: 0.010 percvnt c FIGURE 16. NACA 63A005b'tsic thickness form.
FIGURE ] 5,---NACA 63A004 basic thickness form.
ORDINATES ANDPRESSURE DISTRIBUTIONS FORNACA6- AND6A-SERIES AIRFOIL SECTIONS l l
1.2
(v/vcJ 2
(v/v_?
I
: Li
5¸ A
i I
____ '
I
2O 4O 60 80 I00 0 2O 40 60 80 I00 x, percent ¢ x, percent c x, percent c y, percent c (Iq %)_ '7V¢_ AI'o/Vm z, percent c y, percent c
• _v./v___
0 0 0 0 14. 738 0 0 0 ) • 5 .153 1 020 1. 010 2. 240 .5 .235 1.030 [ 1,015 • 75 .191 1 033 I. 016 1, 850 • 75 ,289 1.040 [ [. 023 1.25 .245 1 040 1. 020 1. 470 l. 25 .309 1. 467 1,055 I [, 027 2.5 .34[ I 043 1,021 ,992 2. 5 .5t0 1.062 [ [.031 990 5. 0 .473 1 045 I, 022 .698 5,0 .706 1.064 ] 1.032 697 7.5 .57L 1 046 I. 023 .558 7.5 .851 1.066 ] L 032 560 10 .650 1 047 I. 023 .481 10 ,969 1.008 1.033 48t 15 .769 1 048 I. 024 .381 15 L 148 1.071 / 1.035 381 20 .856 1.024 .319 20 1. 282 1. 073 k 030 32O , 049 25 .021 050 1.025 .277 25 1. 380 I. 075 [. 037 278 j 30 .967 1.025 .244 30 1,449 I. 078 :. 038
I:o51 244 I
35 .993 052 1.026 .218
35 I. 489 1.079 .030 218 I 40 I. 000 1,025 .194 40 1. 500 1.080 :. O39
(052
45 .987 o51 I, 025 .176
45 1. 478 1. 078 .038 176 [
50 .950 i: 047 I, 023 .159
50 1.42I I. 070 .034 55 .895 1. 021 .143 55 1.337 I. 062 ,031 142 , 042 60 ,825 036 I. 018 .129 60 1,232 1. 054 .027 65 .744 1. 014 , 116 65 1.110 1. 044 .022 128 j 115
l: 020
70 ,652 023 1. 011 .102 70 .97l I. 034 .017 IOl 1 75 .5,50 1.008 .09O 75 .818 1.023 l. Oll
I: ox6
80 .442 1.004 .078 80 .657 1.010 1.005
N
85 .332 • 999 .065 85 .494 • 997 .998 •054 90 .223 989 • 994 .0,52 90 .331 • 982 .091 .051 95 . ll3 978 • 989 .034 95 .169 .967 .983 )34 100 .004 0 } 0 100 .007 0 ( L.E. radius: 0.028 percent c i,.E. radius: 0.062 percent c T,E. radius: 0.005 percent c T,E. radius: 0.008 percent e FIGURE 17.--NACA 64A002 basic thickness form• FmvRE 18.--NACA 64A003 basic thickness form.
12 TECHNIICAL REPORT R-$4--N'ATIONAL AER02fAUTICS AND SPACE ADMINISTRATION
.8_ - - I - 1 i i i -+ + ..... ÷ - ._+______
(v/v_)2 (v/v# _
i
I
tt
__1
86 |---_---5o 0 210 40
0 2'0 40 " 6'0 x, perceni c x, percenl c i AI'JV_ !
x, percent c "/V= z, percent c y, percent c y, percent c (VIV¢o) 2 1
I
) 5. 570 0 0 0 0 0 0 I 1.035 .5 1.0t7 .318 2. 199 • 5 .402 1. 032 I. 016 2.156 • 75 I. 026 • 388 1. 845 • 75 .487 1,053 I. 026 1. 831
! rose l
1.25 I. 032 • 492 t. 459 I, 25 .610 1. 074 1. 036 1,445 t 1.o66 I 2.5 I. 039 • 985 2. 5 .848 1. 093 1. 045 • 982 • _79 ! ].o7o I .696 5.0 I. 040 • 937 5. 0 1. 167 1. I00 1. 049 • 695 ! 1.082 1. 129 • _2 7.5 / 1.o86 I 1. 042 7. 5 1.406 I. 106 I, 052 •563 1. 286 • 481 I0 1. 044 10 1. 602 1.111 I.OM • 4£1 l 1.os_ [ .381 15 1.046 1.52fi 15 1. 904 1.117 1.057 • 381 ! 1.o94 I 1.048 • 320 20 1. 708 20 2. 131 1. 123 1. 060 • 321 / 1.o9s i 1.049 1.839 • 27£ 25 25 2, 297 1.127 1,062 • 278 / !.1Ol I I. 051 1.931 .245 3O | 1.104 ] 30 2. 413 1.131 1.0f;3 • 245 35 - 1. 106 ' i. 052 1.985 •219 • 219 35 2. 481 1,133 1,064 40 2.0O0 • 196 1.13,6 1.06,5 .197 , 1. 108 1.033 40 2. 500 45 1. 967 1. 105 1.051 .17fi 45 2. 4.56 1, 131 1,063 • 176 1.89O 1.094 I 1.046 .158 50 2. 358 1.118 1.057 .1,58 55 1.77g • 142 55 2. 216 • 141 1.083 [ 1.041 1. 104 1.05l 00 1. 637 • 12g • 127 1.071 I 1.035 50 2. 038 1.089 1. 044 65 1. 472 • 114 65 1,831 .113 1.059 [ 1,029 1.073 1. 036 7O 1.286 • 100 70 1. 597 1. 055 1.027 •099 1.045 [ 1.022 75 I. 082 • 088 75 1. 343 1.036 1.018 • 087 1.030 i 1.015 8O • 868 •076 80 1.077 1.015 1.007 • 075 1.013 ] 1.006 85 • 652 • 995 .997 • 063 85 .811 • 994 .997 • 062 • 976 I .988 9O • 438 • 050 90 ,544 • 970 .985 • 048 95 .223 •033 05 ,278 • 946 .973 • 032 0' 058 t 0" 979 I00 • 009 0 100 , Ol I 0 0 0
I
L.E. radius: 0.110 percent e L.E. radius: 0.173 percent e T.E. radius: 0.010 percent c T.E. radius: 0.0125 percent c FmtmF. 19.--NACA 64A004 basic thickness form. FIGURE 20.--NACA 64A005 b'_sic thickness form.
ORDINATES AN:D PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 13
12 !
.8 .......
(v/v®) 2
(v/v_)a .........
.4 . "" -1 .4 .t_-=-; --]-_ ::=---- ....
..... ....
i I. i .... I
20 40 60 80 I00 o' zo 40 6o so too
x, percent c x, percent c x, percent c y, percent c dV, _(v/v=) z, percent c y, percent c (17V,,_)_ TTIr_ aI'dl"_ 0 0 o • 145 0 0 0 0 I0. 081
.®311
.5 .]40 1. 017 .220 • 5 .223 1. O30 I. 016 2. 220 .75 .168 1. 027 •810 .75 .269 1.043 1.021 I. 812 1.013 I 1.25 .214 1. 032 1.010 .400 1.25 .342 1. 046 1.023 I. 395 2.5 .312 1.035 1. 017 •980 2. 5 .479 1.049 1.024 • 978 5. 0 .436 1. 038 1.010 •602 5.0 .656 1. 055 1.027 • 691 7. 5 ,527 1.039 1.019 • 563 7. 5 .793 1. 058 1.029 • 563 10 .£_3 1.04O 1. 020 •479 10 .908 1. O60 1.030 • 480 15 .724 1. 042 1.021 • 380 15 1.091 1.0C:4 1.032 • 381 20 .818 1. O44 1.022 • 320 20 1.231 1. 068 1.033 • 321 25 ,890 1. 046 • 277 1.023 25 1.339 1.071 1.035 • 2,'7 30 .944 1. 048 1.024 • 245 30 1.418 1. 073 1.036 • 245 35 ,980 I. 050 I. 025 .218 35 1.471 1. 070 1.037 .218 40 .999 1.05t 1. 025 .196 40 1. 498 1. 078 1.038 • 197 45 .999 I. 052 1. 026 • 178 45 1.498 1. 079 1.039 • 178 50 .0_0 1. 051 1.025 • 160 50 1.467 1. 076 1.037 • 160 55 .938 1. 047 I. 023 • 144 55 1.404 1. 070 1.034 • 144 60 .876 1.041 I. 020 • 129 60 1.310 1.062 1.031 • 129 65 .799 1. 035 1.017 • 116 65 1.193 1. 053 1.026 .115 70 .707 1. 028 1.014 • 103 70 1. 056 1.042 1.021 • 102 75 .C_3 1. 021 1.010 •090 75 .901 1. 032 1.016 .090 80 .489 1.013 1.006 •078 80 .729 1.018 I. 009 • 078 85 .368 1. 003 1.001 •065 85 .550 1. 003 1,001 • 064 90 .247 • 991 • 995 •051 90 •369 • 988 .994 • 050 95 .120 • 977 .988 •034 95 .188 • 968 .984 • 034 1OO .004 0 0 I00 .007 0 0 0 L.E. radius: 0.026 percent c L.E. radius: 0.058 percent c T.E. radius: 0.0045 percent c T.E. radius: 0.007 percent c FIGURE 21. NACA 65A002 basic thickness form. FIGURE 22.--NACA 65A003 basic thickness form.
14 TECHNICAL REPORT R-84--NATIONAL AEHONAUTICS AND SPACE ADMINISTRATION ].2 -- ..... i _4 .8
[
(v/v_)2 { v/v_ ) 2
' I
I i
0 20 40 60 80 t00 20 40 60 BO I00 x, Dercen? c x, percent c
[
y, percent c I(V/V¢_)_ i 1 x, percent c x, percent c y, percent c (_71'%): fl',_ -__A'I"[I'® i 0 0 i 0 0 0 0 0 7. 337 .5 .385 ' I. 041 ,5 .304 1.038 I. 019 2. 210 • 75 • 467 1. 050 .025 .75 .368 1.0,50 1,025 1.805 I. 25 .595 .030 1. 060 1.25 .469 l. 055 1. 027 1.389 2.5 ._15 .035 1. 072 2. 5 . B47 1,061 I. 030 .974 5.0 1.09t .043 1,087 5.0 ,875 I. 07I I. 035 .690 7. 5 I. 326 .046 1. 094 7.5 1. 059 1.076 1. 037 .563 10 I, 519 1. 099 •048 . 4_0 10 1. 213 1. O80 1.039 .480 15 1. 820 1. 109 . 053 . 382 15 1. 459 1,087 1. 043 .381 20 2. 059 1, 11,5 .0,56 .323 20 1.64,5 1. 001 1.045 .322 25 2. 237 ]. 120 . 058 . 278 25 1.7R8 I. 095 1. fit6 .277 30 1. 892 30 2. 367 1. 123 ,060 .246 1. 098 1. 048 .245 35 1. 962 35 2. 453 1. 127 .062 ,218 I. 101 1. 049 .218 40 1. 997 40 2. 496 L 130 . Of'_ .198 1. 104 1.05l .198 45 2. 494 45 1.996 1.05l .178 1. 132 .064 .178 1. 105 50 l. 9:)4 1. 101 L 049 .161 2. 440 1.128 .062 .161 55 1. S68 1. 092 I, 045 .144 55 2. 331 I. 116 ,056 . 144 00 2,173 rio 1,743 1. 081 1. 040 .128 1,102 050 ,128 65 1. 976 1. 088 043 . 113 65 t. 586 1,070 1.034 .114 70 1, 746 1. 069 034 . 100 70 1, 402 1.056 1. 028 .101 75 1. ,197 1.05O 025 .088 75 1. 195 1. 041 1,020 .089 80 1, 203 1. 028 014 .076 80 .067 1,023 1. Ol 1 .077 85 ,907 85 .729 I. 003 L 001 .063 1. 003 001 .002 90 . riO0 • 978 989 .048 90 .490 • _1_3 • 991 .040 95 .310 • 947 973 .034 !
95 .250 • 958 • 979 .034 100 . O11 0 _ 0 100 .009 0 0 0 L.E. radius: 0,150 percent c L.E. radius: 0.102 i)ereent c T,E. radius: 0.0125 percent c T.E. radius: 0.010 percent c FICI'aE 23.--NACA 65A004 basic t'hickness" form. 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
_,o+- iiiil ...... F%! Li .476 wm:_ ....
_tP_ _:::_:!_ _ >_::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 ,494 _ _ I ig'_'-ili _,1 490 ,502 .,,.
! !! ! _ i!_iiiiii_,i_i_,_!ii_i_ iiiiiiiiiiiiiiii- _ !•i!{i}i, t_ _ ___iiiii!Li_ ili_ _'
,498 --_ _".......
E _ .496 :,, :_"T _]! !!i!_!!i: !;:: ' ' :ii: :::1 : o ,492 all::::i:: _iii- _-, .... i ::;M> .488 _ ....... _:: "6
_i _ ill!
!Iiii! :: ti
i:_il!!l i_ili_i!!
T;iF;;i iiiitii!_'_'iiiil, _, ......
i_511:._
_il _li[!!!i!
o .480 i :,=
.47__ i2_-
_i,iiil .........
iiiiiiii: i __ iiill
iiiiiiil
i:iii_!! ........
,440 _ ....
i .....
LKI ¸ 4 6 8 I0 12 14 I6 18 20 Maximum thickness, f, percent c (b) x= 15 to 45 percent c.
FIGURE 25.--Continued.
ORDINATES AND PRESS'URE DISTRIBUTIONS FOR NACA 6- AXD 6A-SERIES AIRFOIL SECTIONS 17
.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 _ 5 8
=-
a¢ u .354 @ _ ;. i ........... l:J: E .416 -- --_-] _ I E L::R: I ] o
E
O .408 _ ......
_O "6 fff ....i.... _ ............
rr- .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 TECHNICAL REPORT R St--NATIONAL AER0_AUTICS ANDSPACE ADMINISTRATION
.232 .228 :qliii ii;ii! iill _!:I: .224 _; i12!Iiii!_!i • . iiiii .220
NN:;): i]
,216 .290 .212
........... i:;i:: _iltill
.286 .208 .282 2 iA___ ...........itii _,1"- .204 d •278 .200 ".9
j-
.274 E .196 £I:i ili:1 i."
r_ E .270 .540 ._ .266 -o 8 .536 "6 t lq _I:T: .£ .262 i 4:t:
.332
i!iir::i .258 .321 .254 ::!p .250 J ;t [, :: tI:_I .320
" ?11_i
.316 '. !i!!1 £_:_i 2£i; ,312 :j :p: .308 i!l ..........
illill.......
• 3040 4 6 12 8 I0 2O 22 Moximum thickness, l, percent c (d) x=65 to 75 percent c.
1_ l a IZI_.E 25.-- Continued.
ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 0A-SERIES AIRFOIL SECTIONS 19
.026 .022 .068 .018 .064 .060 .056 .120 .052 .116 d .o .108 .E E E 5 .104
E
.90 Joo E ,i T6 a "6 .0915 _. ,172 .168 .164 .160 .156 .152 ,148 •144 0 6 8 I0 12 14 16 18 2O 22 Maximum thicknesst t, percent c (e) x=80 to 95 percent c.
FIGURE 25.--Concluded.
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_ _::
++++ ::iii iiii i_+i+ ++++ +++ +++++m+ "; - _o i
292 I I ...... _ ....'_" ......."I :'_ _!_!i_ i-i ..........
i=i
Maximum thickness, I, percent c (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.
ORDINATES ANDPRESSURE DISTRIBUTIONS FORNACA 6- AND6A-SERIES AIRFOIL SECTIONS 21
ii':Xi ! ii:_i
_- _ i:ii iiii ilt_ lfiilJi][ _ " ' <-+' il_ 4= 771: ]!ii ....... iliI]f7|i![7!_77:: :_;;t_;;; ;;,:::;;_ }777i{_:7 i7 ti777 4_ l:f77LTTTfT_7 7_fii _Tit;ifi_iitl] _t_i _T_
7!i' ii!!iiiii_ !ii} iii} iii!i_i!! iiii!! !!!i i!7ti!ii }ill 77ii iii
"3800 2 4 6 8 I0 12 14 IG 18 20 22 Maximum thlckness, #, percent c (b) x= 15 to 45 percenl c.
FIGURE 26,--C0n! inuod.
22 TECHNICAL REPORT R-84--NATI01_AL AERON-AUTICS AND SPACE ADMINISTRATION
ii!!i!
.392 •588 :584 if! iL .576
%
iiiili
i_iill _F i
±
iii'il iii_i iiii_i .412 .468 .408 22!1;!
.464
:i_i:i
.460 .456 d-: { .452 ,448 !1: t4 18 .4440 Maximum thickness, t, percent c (c) x = 50 to 60 pcrcent c.
FIGURE 26.--Contimmd.
ORDINATES ANDPRESSURE DISTRIBUTIONS FORNACA 6- AND6A-SERIES AIRFOIL SECTION'S 23
.244 .240 .232 .264 • 536 .552 .324 • 320 .3160 6 8 I0 12 14 16 Maximum thickness, t, percent c (d) x--65 to 75 percent c.
FIGURE 26.--Contiaued.
569066--61--4
24 TEC]:INICAL REPORT R-S4--2N_ATI0--N'AL AERONAUTICS AND SPACE ADM'INISTRATION
ORDI:NATES AiN'D PRESS'URE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 25
.z2o_ ......................... !_; _ _ _i! I;;_
:: !!; _ ii _ ii :ii_!_! i_ per( er :'h I_ H[_ iii t_!!H_Hi U;i [ii',:i;J;:;;;i,;?,: i_ i
Iiii_ _[!_i_:':':li'_ ',!iii
ii"27
i!
.120 Hfi
iiiti_i_Liliiii!ii:.i i',;i
iH! ,iiii,iiil,;_ .I 16
$
::-_:2 i:: iL2 _ L
.ii2 i;i: ::_i:::: !!i:_ :4:-_i{ t:L _!
: i F F _'Y
iiiiiiiii_ ii:$ii ,_ i;, ii!i[: iiiiIiiii i!!I iiilIii!
:?i_::i ii::iii ilil if_ t_ii:_
E ..[::i: :_i; ii_ hrf I_+i :::$:1;!
Eilili_ i_ _!ii_il iiiiiii [!ill[ill ;_ii2; ;Elf/: ;;; !iH_ i:>J fill "5 [[ [[[[:: .... :::_:; .......... ::_::::,:,:
,°_ii
;i:q[:i ii!i _ f i_i[iil H! !ili
o iii,iii i!iiliil ilii!i !i:
":'"_: [i[!liiii iii_i_i ................ :iiii[__ i_i _i-"_ _._i lili Iill !i!i
•t04 ....
[
.096 iiii "B _ii iiii !!!i ]P. I_: f:=[i [iiilf::ilii!i =.:/J !b--+-i.',i' .9
l_::i _ ':!!!i _:.!1!i_ iiil
.092
..... _ .... !!iili!!!I!_:_liiiil!i iiiili]:.ii
'i ....
.088 F_
_ _ i[ii ilJl?ii iiili_!t ii!I ii_,') ii)_i )i'.ii _ili
_. i_$ii)
•084 _f
,:::::-' !iiiii!tiiii;iii_!iH ""_"_._
Hii iiii iii fill i_:-_-, i'.[] i5 _ii.i[iiIiiiii_l[[Ii[![ !ii',i
....!.... F:Jiiiiiiili
iiiliiil-i ilIii_ili
.080 _ .080 _L-'_ mm::
.o76 ;_
!if_ii[i!!?f_!] ;4;_i@i;::l_
E![i_H
_ii?:: iii]iiiii!i! ii[i!fl i_l
:q;i!_iT!!!ii:i!ilii!i!iil
,_T_ iliil :.[_[ !!t ,072 _ :hii_[i iiJiif
i i !:ifiil
.068 ....
2 4 6 8 I0 12 14 16 18 20 22 Moximum thickness, l, percent c (a) • =0.5 to 5.0 percent c.
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_ TECIINICAL REPORT R-$4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
500 _' '1........_: ...... _i_ .... _ ,-_ ""_ " " - _'i_ ,, .496 __/_!__'.. __iii Ii _ __'._!t _ _'_!,_._!_ .492 .488
=e
E £ .416 ....... {....... _::_:: Ti ii!21i!_if _ i .E "6 .9 *6 368 ...................... :.:: ......... _ ....i.......
!iiiiiiiii_!i_!' _,_iiiilili _iii,_i!!i
16 18 20 22 Maximum thickness, t, perceni' c (b) x= 7.5 to 40 percent c.
IF:_GtTI_E 27.--Cont.inued.
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 .492 o 16 2O 2S TECHNICAL REPORT H--84--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • .336 .332 .328 .324
tiiii_
.320 .316 .312 :#!!
x,l- .30B _ h o .304 E .381 it ,300 ,384 © .296 .380 "6 .£ .376 IX: .372 .368 ::_ i?i} * .364 .36O N i::i .35E .352 20 22 6 8 I0 12 14 .3480 Moximum thickness, l, percent c (d) x = 65 to 70 percen_ c.
FIGURE 27.--Continued.
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 fi_ii fi!!i
i!i!i
ili+ .240 !!i!
• 2360 6 8 I0 12 14 16 18 20 22 Moximum thickness, t, percenl c (e) x= 75 to 80 percent c.
FIGURE 27.--Cont inued.
30 TECHNICAL REPORT R-S4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
.038 ,,032 .028 iii__ ......
L2
.024 .092
!!!ii_
.O88
_iii!
.084
' _I ::ij
.080
9oi_
E;E _!E .076
==
-5 --i_] S iii _:: = .072 E _i i iii _,
ii!ii!l
o .068 E o .I 56 "_ .152 "6 .£ |ii: :F: !iiii!:: .
_: .148 !f!;!_i!
•
_lt_ lii;;t ;; %, .144
ft!i tli?
,140 _ii: li .136 ff!f t_= .i32 :j £ lii:t: _11 ? i
5_
.128 .124 f!!
.I 2C 12 14 8 I0 16 Maximum thickness, f, percent c (0 x=85 to 95 percent c.
F1GVnE 27.--Concluded.
ORDINATES AND PRES'S"URE DISTRIBUTIONS FOR :N'ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 31
f 4 7 6 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 _ii
Z : 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
32 TECHNICAL REPORT R-84--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
.... _41_:; _#
::i
_pi _ _' 55
i_iiii
I
i:_ _I_ iiiii __.i_
_ !i,_i_i ,_
.424 468 h;
_l;mm miiii::i_ i !_
_'_ _.iiNiiiii_ _ _ _i_i _' _i ¸_ hi: [:._] 't"! "_ + -_r t: : _ _ m
il_ _ !i_t_
g .456 E
o _ ii__
2- 4ao _
ii _ ¸__ ! i ! _ lie _I i !i_!
_7
,[i_!_._;j!:i ;_L'ii!E:i{ .496 ili_!
llEi_ilii q T' il
.492 _ ii
_ii! _ '_:_'_':'_i_ :_ ! _ _'_:_
48E 2 4 6 8 I0 12 14 16 Meximum thickness, t. percent c (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_
"I _ii!
_ill ii.i;::.].:: •508 _'_"_ _
_i iii
iii !::41:_:!::_
,304 i , 3oo_;F;; .564 t_m_!l _'1"-
!!!
_iiltfl tl;i!t!!
lii:
ii i!i_ii!i
:; :: :
!i! _I iiii!i _i_iiii_ __
E _
-- .356 ......
E ...... 1!!!i_! : _ !,
!i::i fill ::i_l ,i_*
E i_Mi i:i ii,li,! i!ii,_.E.iiii .352 .......
_+.
iEI Iili !i_ "_ :: :: : Tii: _ti i; i!i....
";:ill! .....
.9 .348 _-_?_
iiiiil _iil!_;j%; ;iii _ ;i
s
i!!!iii!il ii
Ifil;_' il
iii :-i_ [i._
ii;t .344 m:r_;, .408 .......
=?!!ii !
.404 _ !:' [ 11 40( .., t .39 i i_ _. _ ..........
.39 _ ,5880r:::F:_ 2 4 6 8 I0 12 14 16 Moximum thickness, ;, percent c (c) x=60 to 70 percent c.
FIGURE 28.--Continued.
34 TECHNICAL REPORT R-84--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
= • oo4_i_ I,_,,, _:_i_ _:_i-*_ ........... pe rx_tc _,;.;, 0 . iiF !:_ii!i I00 .104 _ .162
i__'""_"_ _'_'_'_'_ _!_'_I_"_'"_!i
.154
c .c E 150 ._E E o •210 o "6 .206 ,9 .202 .198 .268; iiii,_ili iiiii , iii!il ...... _iiiill ii!: ]!!!
• 264 ::: ::: iiii!!: ....
iiii:'N H?EH •260 !!!1!:5 ! ;: ]i ,256 C 75 15i!i ?:i_ _ i :Yit- t .252 x: 1 lliiii_i :::! t
!I iii _
+ i!:i
!!122
,24E I0 12 14 16 6 8 2 4 Maximum thickness, t, percent c (d) x=75 t,o 100 percent, c.
F_cv_ 28.--Concluded.
ORDINATES ANDPRES'SIYlqE DISTRIBUTIONS FORI_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?i i::i;iil iii _!i ii! ilY: !i :i i_ii:.i ili 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 !!ii i,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!_! ! :: :]: Maximum thickness, t, percent c (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 !I
=i
.444 _i_ .... :: " iii .440 i!i! !i!
-_ _i_
==.,..ii, ii_ i ...........
"= '="_}i == =ii ='_'_ .... =
_1 .486 i ".+-
_,=. ";:-='! _'! !"_ _'""""HI ii i_,I 1i i
4,4 '_= :,i_lill_Iiilil iI!IilI_,,,,,_ ililii I =
i I1
°='" = ! I!I!l i "_ ! i R!I I iiii i _' ='''_
' =
.o==,,._, i IIiI_i _iiiii i! _ i
=®
14 16 Maximum lhickne_s, f, percent ¢ (b) x= 25 to 55 percent, c Flora); 29.--Continued,
ORDINATES AND PRESSURE DISTRIBUTIONS FOR _ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 37
.326 ylLI_
...... iill
_ _ _ ltl.....
!i;@ ili::i • .
ii!iii lib:!
t?i!H
!!p!
3181 :=t !l!l_ _!i}!7 i1:4:_11 tt}dfff
.3,4N _iI'!_,,_
l'dVi :"_ _!i!"_i: :i.kri: :x _: t r:
i;JI_ii i_ii
it!i!_ili!,i,;,;i_
P:ib:
.3o6 _ _7
.372 ..
t!!!!i !!!
i _:Vt:r :1;;:1:,
}
ti!i{l 1:::¢:
@ii I_11 _ #---:!-
! d" t_+,-t.-
:-iiiF?
¢*,ffit:
;ii
}_ h.dilf[ .364 _''_ !::::]
g _
_!ii lili !i!i
t::1 ,,., .36o i Jiii iii; iii::Ji_i_ !_ _
@
u_p ::!i i
! ' i'ii!ti4 _4s
_i .... !_I '
.352 :tmH .416 _;; i_ii:i _
i7 i!i! _ _!i
lii_ !i!i_!i i!i
!::':!' _I!_! ii!!_
ill _,- .... ii!l 11:1:11:h Ill _li !lf_i_t_il
• !iliti_i
::_ttlii.
_7 5'! ......
7_ .408 -':4:=:;1: .404 _:: i fi!Ff:_ i
b _
I'T t::: _
.4oo FI _t
• . 71_77FI- ..£.!4 .,+ .....
N_
__t_
i..L. i11 0 2 4 6 0 I0 I_ Maximum thickness, #, percent c (c) x=60 to 70 percent c.
Flccn_ 20.--Continued.
3S TECHNICAL REPORT R-84_NATIOXAL AERONAUTICS AND SPACE ADMINISTRATION
.168 .164 .160 .152 .224 .276 .272 ,26B .264 .26q .25t 6 8 io .... 12 14 16 Moximum thickness, f, percent ¢ (d) x=75 to 85 percent c.
Fmrm,: 29. Continued.
ORDINATES ANDPRESSURE DISTRIBUTIONS FOR_N'ACA 6- AND6A-SERTES AIRFOIL SECTIONS 39
_*-+-+,++*t_+ ..,* ,**. [:::' iI:+ 1" : :7:: "'EZ :'_' ' C _'* .060 ,"-L'_ ...............
_,.+
_ff----+--
._ :.:.L:: _ _ :_:: :::: ....
;.:: *,::: :::: ::: :::::!f_!i:::::::::::::::::::::::: :::: :::: ::;: ::::::::::::::::::::::::::::: ;; ....... +
:::: E!i_
i .052__ :::;_:::: :__. :::: ::::
,L! !!i': ......... ii!i
__ --.: eJ o_ iiii _ = _=: =:
_. k-X!FFTtl_t!iit i7._i7::!
EX ............... _ii-
i!;i _7{]_ a_m----: ;!;7; I;!_ii_i#i_ .... ji
_+_-:-22_+.. ,_-"__.,--+:. _--.. .... :7!; i!?? :7_)
G- #- 4;.:-_
El".! ................ i}ii 7!!! 7:.77 -- . - _:_i!_777iti:Xl-V.::lili_Tit7777 -;-;g-D-.g-i-k-k-;:gJ_ _+ .... :-,:'" ;.Lg _ .... _T-- LX.+$
.............. iZ!7-ii7 .... ........ -ii":'7171 11£7 - ''<'
::T:: .:+:: :::L:
-::: L:!L
: (e) :::::l::::t::::l
iiiiiiiiitiiii . . :_iii
.I00(_: : 2 4 6 8 IO 12 14 16 Moximum thickness, l, percent c (e) x: = 90 _,o ]00 percent, c.
F[GC_RE 29.- Conclu(t.e(t,
40 TECIINICAL REPORT R-S4--NATIOXAL AERONAUTICS ANDSPACE ADMINISTRATION
. _08 _;:t!::_t-;t i!; 30oU t!T_ : .286L.:!:!:L '_.:: ,262 .........
.2aoL:II:_I:J!
• • Li!_i!i
"_64I_i.L
.120 .116 ( 'l'-'i:_ E : i i_1 llii E t t : t
o .,, 2 i_ii}};i
;-: - Tti;:: i:._ ;: _ iili_ ;;]! _- J08 • " "'-" ::ii:"-m .... :F , I
o
:it:: :ii:{t t_ _ t: .... ,,::,-_ .......
B .104 rr' .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 !: i 2 4 6 8 I0 12 14 16 Maximum 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.
ORDINATES ANDPRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 41
500 I "_- • _: ii_: i_ ..... _ _;{iiii ill! _ii iiil iliI iil !i:!i i iii i:,i ii::i:,! ::: :,i ii! il iil ii!iii_:i iii ii!i !i .-5O2 .498 ill !!i _iiii_ _ i_!iii ,,,
° liii li
488 ii ill
o _= ,........ '........ :!iit:!,i • _i _iiiiiiiiii!t'.i !i ii!i:::.ii::i ! i:.i::: _ " i ' :.iiii'.i
,_ " :,iii i;il ::: ill i_!ili_!
446450 ............. ? _i ;_i -,-.._] 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.
TECTtN'ICAL REPORT R--S4--NATIONAL AERONAUTICS AND SPACE kD_fINISTRATION
:ti ................ I"_ !
.356 _ !i .348 i iili_it .......
X, ' " .336 .400 _ ...... _) i_|::::!i ;Vii]i] :!i :.!
r:;_ :]I '!: , ::l::l t
_,1-- .396_t i : _] !ii
j _l i! .!
i!
o .392 _ i_" .ii !i!
_ '_- 't
iii!i ::_ ,111 ::_
--!--- Fii:: .384
.44o _
..... _ iiti:] I f ::
°
.... _ _ i
!!!!!!t !: _
..... !!]
<: _:t t: ::1:/1 ....
il;tii::il-V ii
?iIi:/._dl :I : : .424 .472 L :: i :" .468 g_ .464 t::;h: .46C 14 16 4 6 8 I0 12 Maximum thickness, /, percent c (c) x= 55 to 70 percent, c.
F_c;uas 30. Continued.
ORDI_-ATES AND PRESSURE DISTRVBUT[ONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 43
t_ _ .....
_ .......... ..........---*-_ _- _f_: F:+:_ !:::!::: !_ r-_,, t[i_[_i l!',_i !'"_ ............
zoo ::i!: I
iiii --_ 1:N :!i i:/_ii::il i[ !:/.::_: :I
;:.:iLl _ I'.:L<I _m !i_ili_iiii_ i';:1211
; , iiiiiii:i
--- !2Li2i: i! iJ_i] iii!
iiilm _ .... _i;:::
.z_z!i!
.... t .... _ i;tiiiiii ::i ili. i
............... ili
• :_i:.<i i::2 i !!'_:._=:: iiii
ill q
iiil :_
.284(_= ::: ;:iil _ i':ili< 2 4 6 8 I0 12 14 I6 Maximum thickness, t, percent c (d) x= ?'.5 to 85 percent c.
FIGURE 30. Continued.
44 TECH_'ICAL REPORT R-S4--NATIONAL AEI10NAUTICS AND SPACE ADMINI,_THATION
X,
.......... qttl _..,-,,......... --- _oo
..... t-:t_'_ _-. itHi}I ++l .......... ,4*' _-_1 t H tl
........... t t.,tt."t'" _A:I 2_JJ ,,.,.*,_ _+÷_, tltll!_tlttt_ :if t! d-l_ttll 11tflllttl
o
.064 "2 _ J4 "__ ,'IMIH'tl :t:i ,e .,.°, ++_*t_÷+ **++,
N'-
_}: _NJH**I_;:M1 ,+* H
..... H_I!H
= .060 *++*1 E ..... £1h+:rtt_t ,+_,,
ii'
,÷**_ ......
I w .05 n_ o N4N "6 .124 O *+H
g
........ HH_ .......
H- tl trill tt t t ;111 t !+t' 1::1 ::::: _H;: llth+ll_i:
,120 H_
*_ [1- HWt_, I 1 t _tlt t_H tM1 -_ ...... H;;: :.t.t$",_t ':_' r} tTl_ _÷÷ RM ...........
t_ .116 u_t 12 14 6 8 10 0 2 Ma×imum thickness, t, percem c (e) x 90 to ]00 percent c.
]_(;_E 30. Conclu<h'd.
ORDI_'ATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 45 .012_!,_ _}_ _i_ ]ii i_ m: :ii: iI!i iii:_!
:m :t:::' :;J: i1: !!;: !:i ....
.0o4 _! _:_
._, :ii: i!ii
I_O --= ._
__:_i u,_ ::;!l:iliF:q iiiili_: "o o" :u: ;11 ::: _M:::: !ii_ i:li i!_:'_ii! t:il !!_:1:::: ,::: :_:! ::_ :: series " _ F :!::IT::: u::m:: :::: :::, if!! f _T
_,o_ _ ,ooE ,,= ! i_:i_1:! i
0 _ _; .008 u,, ,
[i:il
:::t::::t::: I i::j::;:|::: i:.: : • :i;ili_ii i![ _ _ 65-series
.004 iiii -+--M_; :2:_ ........ ::4
4 6 8 I0 12 14 16 18 20 22 Mcximum thickness, l, percent c FIOUIIL" 3l.--Variation of the ralio of leading-edge radius io ma.ximm'n, thickness squared fro" the NACA 63-, 64-, and 65-sories airfoil seetlons.
_6 TECttNICAL REPORT R--S4--NATIONAL AERONAUTICS AND SPACE ADMINIgTRATION
.008
ql q+}:i:_ i::_ ,{i_:::: +_";+
_ !liiIilll _, H_*IHtHI:III_,}._J:!P.I_h+ .-i{!l i :h '.Li i:H ,_ i .004
:!!! ......,,:._..._,. .... ,,,_.._ .............. ililli+ th]:]_]:r{l_i!!t_ _-_-_-,+,_-._
,_,I,,_+::_ .... _',:_
_:t:l I HHZFHIHI: iili ii_iiH_, "LN44"_u'N'_!J" :!:::,';:l[: _: :t it ,. . ,P_,_jT__ -',h'-T llil .................
.O08
hi_ .{H:I
_g m
g _ .004
i!i} t!::] tit: I:_;I +, !it: , : , :ttl 4 t :11 4 _ : , : : +, ,+H L; '_-
....m1
_I_tFllu:*_ , t....... :.... t ....
+q+Hgl IH* *H+; 008 _: :;_, _"_"_"'_: : " "_I ::i; _;L+ :;; : _ _1 "; t_t !'i'T_ !!!i ,':.+++: ,,,+ +....
HH ++++.
_._ _i-_ +++. t _+ +.I_ ;::;.... i::: : + '_t_J[i::Jl : ..............
+.+- ;;+;.
I::11 i',', _:_,l_qJ!ilit:,:_I.
.... }!i!:}!!! .............. ::;: iHi_i ..............
.+_ HI_ HIH ,.I;|:,_ _ ........... i .......
ti:, t:: ...... J: ,t ........ tt![ :i I+_[
_I,, :::, ::_:}: :'.Q :I :_lI* i.............. iF, :I,, _; 1!i +i _" i;
I}}} il: !
i
0 2 4 6 8 IO 12 14 Moximum thickness, l, percent c FxavaE 32--Variation of ihe ratio of leading-edge radius 1o maximum thickness squared for tlm NACA 63A-, 64A-, and 65A-series airfoil sections.
ORDINATES ANDPRESSURE DISTRIBUTIONS FORNACA 6- AND 6A-SERIES AIRFOIL SECTIONS ;47'
I.I i , -- ,9 .....
i
I
oB -- -- cJ ,7 -- I • i i
J
0 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 20 22 (b) x=0.75 to 5.0 percent c.
Fl C, rRF, 33.--Continucd.
ORDINATES ANDPRESSURE DISTRIBUTIONS ]:ORNACA 6- AND6A-SERIES AIRFOIL SECTIONS 49
1.76 1.72
f i - i
1,68 1.64 1,60 1.56
1.52 !itI S
_. 1.48
..8
_c_1.44
I! :;I -J: tl °-
L40 _ 1.56 o 1,52 1.28 1.24 1.20 1.16 1.12 1.08 1.040 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 TECHNICAL REPORT R--84--NATIONAL AERONAUTICS Ai'_D SPACE AD:_INISTRATION
1.72
-I
---- -- -t--
,I .... k
1.6B I .....
-p
1.64
I
!
...... _ 1.60 I 1.56
L
1.5;' i- 1.48 I 5_
-I t '
¢,1 -I 8 1.44 -- " -', - " i " -- i _ 1,40 c I I o 1.56 IIJ i I 1.32 CI.
i -- + o I 1.28
_l
I
1.24
:I
I t.20 I _]/ _/ //] -÷ /4/, i 1.16 -- +
I
t. t2 I
1.08
!
V/ i// 1,04
/f
I
1.00 o 6 8 I0 12 t4 t6 18 20 2P Maximum fhickness, l, percent ¢ (d) x=35 _o 70 percent, c.
F_ e;uaE 33.--Contbmed.
ORDI_*ATES ANDPRESSURE DISTRIBUTIONS FOR NACA 6- AND6A-SERIES AIRFOIL SECTIONS 51
Maximum thickness, f, percent c (c) x=75 to I00 percent c.
FIGURE 33.--Concluded.
52 TECHNICAL REPORT 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.
FIGURE 34.--Continued.
54 TECHNICAL REPORT R--g4--NATIONAL AERONAUTICS ANDSPACE AD_II'N-ISTRATION
1.64 1.60 1.56
i/
1.52
/ 1/_°
1.48
/I-
1.44 1,40 "" 1.36 g .... ]___ o_ 132
u !60
tD °_ 1.28 // ......
1.z4
///
1.2o
1.16 //T
1.12 _ _ 70 i.o8 I.o4
+
t.oo 18 B I0 12 14 16 20 22 o Moximum thickness, f, percent c (c) x=45 to 75 percent c.
F]G_TRE 34.--Continued.
ORDINATES ANDPRESSURE DISTRIBUTIONS FORNACA 6- AND6A-SERIES AIRFOIL SECTIONS 55
,o, _[
X, .96 _ J _
_ \_
X8
: 88 \\ _
i .84 u .80
--
.68 (d) "640 2 4 6 8 I0 12 14 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-KATES AND PRESSURE DISTI_IBUTIONS T0R N'ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 57
1.64 I
....... 'erce°!-_ i 40
It I/ I_
1.60 //_
-- .- I / /=o
.... A
,.20 _ S
,.,_ ,_7 / I
.... I ]
"'=- ,N_ _ I 1 |,__ -
1.08 -- - -L ......
1.04
t
(b) 14 16 18 20 ;)2 4 6 8 I0 12 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
. L_L __
X, - percent C---- 1.60 50 ....... ,. / 1.56
-/
1.52 1,48
..... -/ /
1.44 1.40 N _ 1.36 ig, 1.32 Q) 1.28 t U O
_ 1.24
1.20 1.16 1.12 1.08 1.04
J
F
i .00 2 4 6 8 I0 12 t4 16 18 20 Moximum thickness, f, percent ¢ (c) x= 50 to 75 percent c.
FIGURE 35.--Continued.
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 (d) x=80 to 100 percent c.
]?[GUI{E 35.--Concluded.
60 TECITXICAL REPORT R--84--R'ATIONAL AERONA£TTICS ANDSPACE ADMINISTRATION
1.28
--! I i °e,c_oto- -
_N
I /l_ 2.5 __ .
I --_ 1.25 I I I • I I i
\ :X\
I . ---t i i
__Ii ;_JL\T L Z_-_
t
-i__ _ Z¸
"520 2 4 6 8 t0 _ 12 14 Maximum thickness, /, percent c (a) x--0.5 to 5.0 percent c.
FIGURE 36.--Variation of static-pressure coefficient with airfoil maximum thickness for the NACA 63A-series airfoil sections.
ORDINATES ANDPRESSURE DISTRIBUTIOL-N'S FORNACA 6- AND6A-SERIES AIRFOIL SECTIONS 61
t l !
I
I I
6 I0 12 14 16 Maximum thickness, f, percent c (b) x=7.5 to 30 percent c.
FICVaE 36.--Continued.
(32 TECHNICAL REPORT R-S4--NATIONAL AERONAUTICS ANDSPACE AD_fINISTI_ATION
_N __ 1.44 + I ) .40
]
j__ ___ t.36 t .... I i.:..52 .... f -- --
t +
+.24
- //;
= _LI6
-
;///l
_,112 & I m 1.08 I.04 -- +
_J_ 1
).00 + --t ""--.4 96 .... _ -- i I 9z __l .....
l
I --4 -- 4 _l_+ .
Cc)t i
840_2-- 4- 14 16 Maximum thickness, l, percent c (c) x= 35 to 95 percent c.
FtacaE 36.--Concluded.
ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 63
I. i6 -- 1.08 I i
1 J
1.04 \ 1.00 \ \ I i
\
\
.5 I
...... -e .... io - (2
Maximum 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 (b) 1.04 6 I0 Moximum thickness, t, percent c (b) x= 5.0 to 35 percent c.
FIC_TRE 37.--Continued.
I
ORDINATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 65 1.4 8 !
1.44 --
l L _Yl 2"
1.40 -- 1.36 --
i r//r/o
1.32 1.28 -- 1.24 ,8 1.20 ---
/
//
"E •_, 1.16 --
/
/
/
:-//
_ 1.12 --- /
//
&
J ._ t.08 -- t
_1- [_
1.04 -- I 1.00 i I = I .96 - "- I -- ' I 85 I
--._. ___
/ --t .... 1 L .88 J
-_l 1_
i i
:)1
I I I
.84 0 2 4 6 8 I0 12 14 16 Moximum thickness, 1, percent c (c) x =,i0 to 95 pcrceat c.
FIGVRE 37.--Concluded.
66 TECtINICAL REPORT R--$4--NATI0_N'AL AEHONAUTICS AND SPACE ADMINISTRATION
1.12 L08 1.04 LO0
t i
IO 12 14 16 Maximum thickness, t, percent c (a) x=0.5 to 2.5 percent c.
FZGVRE 38.--Variation of static-pressure coefficient, with airfoil maximum thickness for the NACA 65A-series airfoil sections.
!1
il
ORDI'N_ATES AND PRESSURE DISTRIBUTI0:NS FOR N'ACA 6- AND 6A-SERIES AIRFOIL SECTIONS 67
1.44
i '
--" 50.
/ / _ _ l . . • _-------_, __ __
i
I i 14 16 (b) x=5.0 to 40 percent c.
Fm_nn 38.--Continued.
68 TECHNICAL REPORT R--S4--NATIONAL AERONAUTICS ANDSPACE AD._IINISTRATION
1.40 1.36 !
1.52 6O t.28 1.24 i • 70 i !
I I 8O 1.04 1.00 9O i I '840 2 6 8 Io t4 Maximum thickness, f, percent c (e) x=45 to 9,5 percent c° FIGurE 38.--Concluded.
ORDr_ATES AND PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 69
.... 1.2
i i
a, 6 8 I0 12 14 16 18 20 22 Maximum thickness, /, percent c (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__ .......
._ __ !
\
!
i !
__ ] '\ !
_.o ........ \ _- i
1.9 ............ _ !
-- -- I i \ _ J
I
- 1
i 1.7 ........ -_ .- l .
I - -- percent c "_ 1.5 ................
I
-i
_ J \,,
!
1.3 ............. ]--! --I
! __i
........... !
I
I
,.2 ............. i-- --i I
! |
__ J I i ' : t.25 i l.O---- __._...._______._._.__ .9 ............ ---J
___L_ L_
!
(b)
I
14 16 18 20 2;_
'SO---------2---- 4 6 B -- io 12
Maximum thickness, f, percent (b) x=0.5 {o 2.5 percent c.
FIGURE 39.--Continued.
ORDINATES ,L\_D PRESSURE DISTRIBUTIONS FOR NACA 6- AND 6A-SERIES AIRFOIL SECTIONS 71
.72 .68 _--" percent ¢ .64 _
._o .... j ..... _2-
.56 -- .k 7.5 : .... + .............
.52 .48 -- -- _1_8 .44 ....
o_ .40 E .56 ................
.32 -- .28 _ --- 3O I ....
.24 .......
.20 l -- .16 ....
5O
--- ___E
.12 _ _ 60 -_ _---1-'-- ..... _---_- 65 _ .O8 ...... _ .... _ _ ___ _-70 .04 ......
_95_
ic, I I
0 2 4 6 8 I0 12 14 16 18 20 22 Moximum 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
7,6 !
!
7.2
i
I 6.8 14.0 6_4 13.6 -- 6.0 t3.2 -- 5.6 12.8 -- 5.2 I2.4 - 4.8 12.0 -
_
-percer t c ..... 4.4 6 11.6 --
::]-?
c 4.0 _ 11.2 - ID b _ 10.8 --- -- • 3.6 3.2 _ 10,4 ....
\ - 2.8 •_ I0.0 - - -
L_R __/
2.4 9.6- \ , 2.0 9.2- --- ........ _._ 1.6 8.8- 1.2 8.4 ....
8.0- l ... = .............
.4 A.
7.6 ....
(o)
7'20 2 4 6 8 I0 12 14 16 18 20 22 Moximum thickness, 1, percent ¢ (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
I
f 2.2
\
\
2.1 t 2,0 n 1.9 -- 1.8
_1 _
"_ 1.7
\
E 1.5 i \ i x.
-- _ percent c _--
1 ""--
-- _"--1 .75
1.2 1 I.I
_- .__
1.0 _ _ ) ..... _ _ _ _ L ___.
ii 11
.8_ 2 4 6 8 I0 12 14 16 18 20 22 Maximum thickness, t, percent' C (b) x=0.5 to 2.5 percent c.
FIfiURE 40.--Continued.
74 TECH'NrCAL REPORT R--S4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
.72 i ' _ " _--percent c .68 .64 .6O .56 Z5
.... ::x2_
.52 .48 J _1%8 "44 ....... i __ o .40 _,---_ .....
E w I ._ .56 J "_ .32
t --h
'_ .2B .24 .20 .16 -- ---_ _ 55 .12 -- "---: -_-- 65 .08 .O4
q_:_!_i___l it i _ _°
2 4 6 8 I0 12 14 16 18 20 22 Moximum thickness, f, percent ¢ (e) x=5.0 to 95 percent c.
FIGURE 40.--Concluded.
,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., 15.
o" 12._ 12.4 E ' 12.0 11,6 g
_ ..2
4.0 I0., !
I0.0 - 2.8
..... _L- -- j J_.__ -_L_
1.2 8'40 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.
76 TECI=INTCAL REPORT R--S4--NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 2.5 -- i 2.2.
F: 2.1 2.0 1.9 1.8
<_1 _'8, ._
.o"
1.6
i-\
._ 1.5 _
i-
_ 1.4 _ 1.3 1.2 -
I
I.I
i i
L.
i-i
I
_.0 - --..__ .9 .......
I
I
(b) 14 r6 _8 2o 2'z .8_ 2 4 6 8 IO 12 Maximum Hfickness, L _ercent c (b) x=0.5 to 2.5 percent c.
FIG_:RE 41.--Co_tinued.
ORDINATES ANDPRESSURE DISTRIBUTr0NS FORNACA 6- AND6A-SERIES AIRFOIL SECTIONS 77
(c) x=5.0 to 95 percent c.
Ficvr_E 41.--Concluded
78 TECHNICAL REPORT R--84--NATIONAL AERONAUTICS AND 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
/ I ,
7-
12.4 ............. _7.2 12.0 ............ ,6.8 II.6 -- T ..... .4 ..8 I
_°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 ---- - _-- 3.2 8.4 -- _ -- / /
8.o-- _- \ -- - 2.8
_ _ __ _ _1\_
-- - , ---_ 2.o
i 1.6 6"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.
ORDI57ATES ANDPRESSURE DISTRIBUTION'S I_'OR NACA 6- AND6A-SERIES AIRFOIL SECTIONS 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 J 0 2 (b) x=0.5 to 2.5 percent c.
Fr_'cRz 42.--Continued.
_0 TECI-L-_TrCAL REPORT R--$4mNATIONAL AERONAUTICS AI_D SPACE AD_/fINISTRATION
.72
r : X, L_ - percent C -- .... 5.0
.68
.... L __ -- __] m
.64
!
I ........ i __
.60 ...... 4__ __
.56 !
.52
I
!
I /
__J_-
.48
I
, !
l |
_°_8.44
e" .40
_J
"E k .56 i c I !
-- I
-4-- __ _ :o
"_ .52
• __ 21Z
I i . -- ___ J I ! :s.
.28
I
I
I < .24 i --- --_-t-- -- 35- .20 -- _-J--I ....... _.0- _ _1__ I __ __ ' ; _ _5 I -- _-- --_ -- _0 _ _ rO .O8 .04 ..... )5 [c) ' I ,
/
_b ,? ,4 ,6
2 4 6 8 Moximum thickness, t, percent c (c) x=5.0 to 95 percent c.
I_eURE 42.--Conchtdcd.
ORDINATES AI_TD PREISSURE DISTRIBUTIONS FORNACA 6- AI_D6A-SERIES AIRFOIL SECTIONS 81
14.8 -- --l_" T--
i 1
--Ill
15,6 --
it _
l&2 -- --_ l( i _ !! ! ] 12,8 .....
II I i2,0 .....
11.6-- ;_ d i i i E 11.2 .....
E 10.8 -- _ '_- -- _ i÷- 10.4 ......
c o I0.0 .....
9,6 ....
9.2 ....
- _, 2 8.8 -- --_ _' 8,4 .....
8.0 ....
i ....... _. - 2.0
--- ] J 1
_o) 1
7'20 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 maximum thickness for the NACA 64A-series airfoil sections.
82 TECHNICAL REPORT R--8 i--NATIONAL AERONAUTICS ANDSPACE ADMINISTRATION
2,4 ..............
L r- I -_
i I !--I
2.3 ..... : .... !
i I
2.2 - - -"_--
! , !
% X 2.1 - --_ --_
./ i \!
2.0 ......
1.9 ..... :--- -- ! .... t i 1.7 - -- _ - __ i >, 1.6 .....
_ 1.4 ...... _ . ! --- m 1.3 ........
J 1.2 -
• i-
I.I .... J--
Jl ........ _-i
(b) 8 I0 12 14 16
.9_- ..... 2 4 6
Moximum 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 .52: 4 6 8 I0 12 14 16 Moximum thickness, f, percent c (c) z=5.0 to 95 percent ¢.
FZGUaE 43.--Concluded.
84 TECI-L--'_ICAL REPORT R--84--NATIONAL AERONAUTICS A_*D SPACE ADMI'NISTRATI0_,,T
16.4 .......... 9.6 16.0 15.6 15.2 -- 14.8 -- i 14.4 _ 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 t0 Maximum thickness, t, percent c" (a) z---0 percent c.
FIGURE 44.--Variation of additional velocity-increment ratio with airfoil maximum thickness for the NACA 65A-series airfoil sections.
ORDINATES AI%rD PRESSURE D1STR'IBUTI01qS FOR I_ACA 6- AI_D6A-SERIES AIRFOIL SECTIONS 85
2.4
2.3
.1
2.2
2.1
2.0
1.9
,, 1.8 1.7 o L m 1.6 -5 o 1.5 c .9 __ 1.4 1.3 1.2 I.I 1.0 .9 •8 o (b) x=0.5 to 2.5 perccnt c.
FIGURE 44.--Continued.
86 TECI-IN'rCAL REPORT R--84--NATIONAL AERONAUTICS ANDSPACE ADMINISTRATION
i L. I ll percent C
V i----I_---F--- __._ 5.0
.68 ..... _ :.,.__ ,60
_ -_ : _!_
.52 -- .48 I0 _t_8.44 o" .40
-- i
"E 15 ...... ......
.36 ......
J .... _-4:J_J__,LL
!!.pll J i
F -i----tl / I ! _t I _°_
.04 ....... _ i90- 0 2 4 6 8 I0 12 14 16 Maximum thickness, f, percent ¢ (c) z=5.0 to 95 percent c.
FIGU!_E 44.--Concluded.
V,S. ;OVERNMERT PRIKTIHG OFFICE:Igll