Hammond, Alexander, D

Mcmullan, Barbara M

English

NASA Technical Reports Server

j" 
RESEARCH 'MEMORANDUAA- 
CHORDWISE PRESSURE DISTRJBUTION AT HIGH SUBSONIC SPEEDS 
NEAR MIDSEMISPAN O F  A TAPERED 35O SWEFTBACK WING OF 
ASPECT RATIO 4 HAVING NACA 65A006 AIRFOIL SECTIONS 
AND EQUIPPED WITH VARIOUS SPOILER AILERONS 
By Alexander D. Hammond and Barbara M. McMullan 
Langley Aeronautical  Laboratory 
NATIONAL ADVISORY COMMITTEE 
FOR AERONAUTICS 
WASHINGTON 
June 24, 1952 
https://ntrs.nasa.gov/search.jsp?R=19930087253 2020-06-17T11:33:14+00:00Z
1x 
.I 
r) 
NACA RM ~ 5x28 
NATIONAL ADVESORY COl&iITTEh FOR m O N A U T I C S  
. .  RESEXFtCH MENORANDUM 
CIlORDWIsE PRESSURE DISTRIBUTION AT HIGH SUBSONIC SPEEDS 
NEAR MIDSEMISPAN OF A TAPERED 35' SWEPIBACK WING OF 
ASPECT  RATIO 4 HAVING NACA 65AOO6 A I R F O I L  SECTIONS 
AND EQUIPPED WITH VARIOUS SPOILER AILERONS 
By Alexander D. Hamrnond and Barbara M. McMullan 
SUMMARY 
I 
An investigation was made in  the Langley high-speed 7- by 10-foot 
tunnel through a Mach number range from 0.60 t o  0.93 to  determine the 
ef fec t s  on %he chordwise pressure distributions of projecting vazious 
spoiler-type ailerons- on a swept wing. The semispa+ 35O sweptback wing 
had an NACA 65~006 airfoil section, an aspect  ratio  of 4, a s d .  a taper 
r a t i o  of 0.6. 
The re su l t s  of the investigation are presented as curves of chord- 
wise pressure distributions near the midspan of the spoi lers  (0.46"- 
semispan s ta t ion) .  
INTRODUCTION 
The use of spoiler-type ailerons for lateral control has been tzle 
subject of. a number of Tnvestigations at- both low and high speed. These 
investigations have for   the  most part deal t  with force measurements t o  
determine the effects of various spoiler configurations on the charac- 
t e r i s t i c s  of both swept and unswept wings. There is, however, very l i t t l e  
information concerning the aerodynamic loads on swept wings equipped with 
spoiler-type controls at high subsonic speeds. In order to obtain some 
information on such loads and'on the flow in  the   v ic ln i ty  of the spoi ler  
on swept w i n g s ,  chordwise pressure masurements have been made at one 
spanwise locat ion on the upper and lower surfaceis of a 35O .sweptback 
semispan w i n g  equipped with various spoiler-type controls in the Langley 
high-speed 7- by 10-foot tunnel. 
For these t e s t s  a solid plug-type spoiler aileron was projected 
verious height6 from 3 percent of the   loca l  w i n g  chord below the lower -
, 
. 
s 
wing surface to 4.percent of the  loca l  wing chord above the upper wing 
surface. The tests were made at Mach numbers from 0.60 to  0.93 f o r  an 
angle-of -attack range from 0' t o  20°. I n  addition three f ingered-type 
spoiler-aileron  configurations and a perforated plug-type-spoiler aileron 
were investigated at a projection.of 4 percent of t h e l o c a l  wing chord 
above the wing surface through the same angle-of -attack .md Mach number 
ran@;e. 
SYMBOLS 
M 
P 
- 
C 
Y 
Mach number 
pressure coefficient ; ") 
free-stream static pressure,  lb/sq ft- 
local  s ta t ic  pressure,  lb/sq f t  
. d . . 
atmospheric pressure. I . .  - . . -  . . - . . .  - 
crit-ical-pressure coefficient, that is,  the pressure coefficient 
corresponding to  the local  veloci ty  of sound 
free-stream dynamic pressure, Ib/sq f t  
angle of a t t ick ,  deg 
mean aerodynamic chord of .Mi& 1.020 f t  ( sgb /2  c2+ 
-twice wing area of semispan model, 4.00 sq f t  
wing span, f t  - . .   . .  . . .  
loca l  chora, f t  
chordwise coordinate, parallel to plane of-symmetry of the pres- 
sure ori f   ice ,  f t  
.. - 
spanwise distance. from plane of symmetry, f t-  
3 
A angle of sweep of the  quarter-chord line, deg 
. 6 s  projection of  spoiler  (projections below lower wing surface  are 
posit ive),   percent c 
A P P ~ ~ S  AWD MODEL 
The model used i n  th i s   inves t iga t ion  was a semispan sweptback-wing 
model mounted ve r t i ca l ly  in the Langley high-speed 7- by 10-foot tunnel 
with the ceiling serving as a reflection plane.  
The geometric characteristics and dimensions of the wing are shown 
in  figure 1. The wing wa8 made of steel and had 35O of sweepback of the 
quarter-chord line, an aspect ratio of 4, a taper  ra t io  of  0.6, and had 
no twist or dihedral. The wing had NACA 65~006  a i r fo i l  s ec t ions  pa ra l l e l  
t o  f r e e  stream. 
s 
The pressure  or i f   ices  were located on the, upper and lower  surfaces 
o f .  the chordwise section at the  46-percent-semispm  station which corre- ' 
sponds-to approximately the midspan of the various spoiler configurations 
table  I. 
.I investigated. The chordwise posi t ions of the   o r i f ice  are l i s t e d  in 
The spoiler configurations investigated (f-ig. 2 and t ab le  11) are 
as follows : 
\ 
(a) Configurations A, B, and C - A fingered spoiler aileron pro- 
Jected -0 . O h  (gap unqealed) 
(b)  Configurations E, F, G,  H, and J - A solid plug-type spoller 
aileron projected -O.Olc, -O.O2c, -O.O3c, - O . O k ,  and O.O3c, 
respectively (gap unsealed) 
(c)  Configuration K - A perforated plug-type spoiler aileron pro- 
jected -0.04~ (gap unsealed) 
(a) Configurations L and D - The p la in  wfng,. gap around spoiler 
sealed and unsealed, respectively 
TESTS 
A l l  the tests were made in the Langley high-speed 7- by 10-foot - tunnel? The various spoiler configurations were investigated through 
4 I NACA RM ~ 5 2 ~ 2 8  
the Mach number range from O..& t o  U.-43 . a t - e l e s  of attack. from 0' t o  
20°. The Reynolds nimber. vmied  from a h - &  J.1-x -io6 - a t  M = 0.60 t o  
about-4.0 x lo6 at-..M = 0.93 when based on-khe wing- m e a n  aerodynamic - 
chord. . . .  
PRESENTATION OF THE DATA 
Because of the in t e re s t  shown in the r e su l t s  of t h i s  investigation, 
the pressure  .distr,ibutions  over the various  -spoiler  configurations - are  
being presented wtthovt discussion In order t o  expedite the .publication 
of the data. It i s  f e l t ,  however, that the pressure .data as presented 
w i l l  be useful i n  the predict-ion of the local chordwise wing loadings . . 
and i n  the. predict-lon of some of the spoiler loads for spoiler configu- 
ra t ions similez t o  those of this investigation. 
The chordwise.pressure distributions as obtained i n  this  investiga- 
t ion .  on a 35' sweptback tapered w+ng equipped with various  spoiler-aileron 
configurations me presented i n  figures, 3 t o  13. . Table . M: l i s t s  the f ig -  
ure numbers for the data corresponding to each spoiler configuration 
investigated: It should be noted t ha t  the.a.zigle of a t tack  shown on the 
figures has  .not  been  corrected  .for air-stream misalinement and tunnel- 
w a l l  effects. .. - . . . .  . . . . . . . . . . .  . . . . .  . . . .  . . .  - 
The following diskussion describes. the pracedure used in obtaining 
the -data for . . the . . f igures-as   p resenm.  Each or i f i ce .  on the upper and 
lower surfaces of  the w i n g  was conneckd t o  . a  mwmeter tube whose.loca- 
t ion   re la t ive   to   an  arbitrary unit length o f -  the manometer board corre- 
sponded t o  the location of the orifi-ce relntLve tu the wing chord. Photo- 
graphs were me of the manometer board and the chordwise.pressure 
dis t r ibut ions were fa i red  on blueprints made from the negatives. These 
blueprints were l a t e r  bleached and used f o r  +&e ffnal f i b r e s .  I t - s h o u l d  
be noted therefore that the vertfcal scale for these plots is a function 
of the tunnel Mach  number ,and th@t he horizontd scale  is, of C O U ~ S ~ ? ,  
the same for-all figures.. 
. .  
. .  
Langley Aeronautical  Laboratory . . 
Langley Field, V a  . National Advisory Committee- for Aeronairtics 
. . .  
.. , 
NACA RM ~ 5 x 2 8  
, .  
TABI;EI 
LOCATION OF PRESSURF: ORIE'ICES 
4 
5 
6 
7' 
8 
9 
10 
11 ' 
12 . 
13 
14 
15 
16 
.. 
Percent chord 
Chordwise positions of 
orifices on upper surface 
O r i f  i ce  
1 
2 
3 
9% 
5 
Chordwise positions of 
or i f   i ces  on' lower surface 
Orifice 
1 
2 
3 
4 
5 ;  
6 
'I 
8 
9 
10 
11 
12 
1 3  
14 
Percent chord 
2 
6 
10 
=3 
1 
34 
5% 
585 
41- 2 
3 
66 
68 
77 
80 .* 
9% 
L 
. . 
Configuration 
A 
B 
C 
D 
E 
F; 
c: 
H 
J 
K 
L 
TABLF: I1 
GEOMETRIC CEIARACTERmICS OF SPOILEEI CONFpGuRAlcIONS 
Outboard 
(percent b/2) 
' end 
54 
54 
55 
98 
98 
98 
98 
98 
98 
50 
98 
Projection 
(percent c ) 
-4 
-4 
-4 
0 
-1 
-2 
-3 . .  
-4 
3 
"4 
0 
. ,  
rype 
Fingered 
Flngered 
Fingered 
. .  
""""" 
Solid 
Solid 
Solid 
&lid .  
Solid 
Perforated 
""""" 
Gap 
Unsealed 
Unsealea 
Unsealed 
I .  
Unsealed 
Unsealed 
Unsealed 
Unsealed 
Uneealed 
Unsealed 
Sealed 
?igure 
Ll 
12 
$3 
13 
. 6  
:7 
/ 8  
i9 
: 5  
10 
.4 
m", . I ,  ' 
. .  . ... . . . .  
NaCA FiM L52C28 
IC, 
i 
Figure 
Area 4 s g  f f  
Aspect rcrfiu 4 
Taper rufio 0.6 
NACA 6 5 A 0 0 6  section. 
" 
prsssurs wifices. 
a 
- Geometric characteristics of t h e  35O aweptback w h g  Wuipped 
8 
C 
Configurufion A 
I 
Con figurntion K 
Figure 2. - Details of the various. spoiler . .  .ai@ron configurations. . .  . .  
. 
2x 9 
a 
Axis of rotution .60c 
I -  
* 
D 0 
E -.o/c 
F -.02c 
G 703c 
H 0.04~ 
J .03c 
L 0 (Gup seu/M) 
Figure 2.- Concluded. 
10 
-." 
P 
0 
.5 
-1.5 
-1.0 
-3 
P 
0 
-1.5 
-1.0 
-.d 
P 
0 
(a) M = 0.60. 
Figure 3.- Chordwise pressure distribution over a 35' sweptback wing, 
at the 46-percent=semispan station, equipped. w i t h  a plug-type-sgoiler 
aileron: 6, = 0; gap WseaSed. 
. . .  
.. 
". 
. .. . . .. ~. . - .: . . ,  i 
11 
Upper surface o 
LOW@.? SUtfOGe A 
Configuratbn D 
r * O  Mm.80 
\- 
, I , , , , , ,  
f P J A . 5 d . ? B 9 1  
5 
(b) M = 0.80. 
Figure 3. - Continued. 
. .  
Upper surface o 
LOWW SUffOCe A 
I I I I I I I I 
J P J R . S S . 7 a 9 . 9  
% 
-1.0 
t5 
P 
0 
.5 
( c )  M = 0.90. 
Figure 3.- Continued. 
1 
... . .  . .  
:I 
. . .  . .. . . .. 
r L t 
-3 
P 
0 
u 
Figure 3.- Concluded. 
14 NACA RM ~ 5 2 ~ 2 8  
4 5  
I .  
(a )  M = 0.60. 
Figure 4. - Chordwise .d i s t r ibu t ion  over .a  35O sweptb.ack wing, 
et the  46-percent-semispan s ta t ion ,  equipped with a plug-type spoiler . . -. . . 
aileron. ES =. 0; gap seaxed. 
.- 
. . .  . .  - 
XACA RM L52C28 
P 
0 
.5 
Configuration L 
0 =I6 M1.60 
10, 4 I I I I ’  1 I I I 
0 J P J 4 .5 .6 .7 .8 .9 1.0 
% 
- 1.0 
-3 
*P  
0 
.5 
/.O 
Upper surface o 
Lower surface A 
Configuration L 
a= 20 M=.W 
./ 2 .3 .4 .5 6 .7 .8 .9 f0 
% 
(a )  M = 0.60. Concluded. 
Figure 4.- Continued. 
I 
Uwer surface o 
LOMET surface A 
-3 
P 
-2.6 
-1.5 
-5 
P 
0 
J 
Ip 
M = 0.80. 
a 
I 
a, 
... 
> I 
: 
Umer surface o 
Lower W a c e  A 
1 
(b) M = 0.80. Continued. 
~igure 4.- cantinuea. 
.. 
. . . . . . . . . . . . . . . . . . . . . . . . . . . .- . . ..... . .  . . . .  .. . . . . . . . , .
Uwer surface o 
Lowev surface A 
15, 
"P* 
-K 
P 
0 
d 
. . .. . 
(b) M = 0.80, Concluded. 
~ ~ g u r e  4.- Continued. 
. 
.... . . .  ! 
I 
Upper surfoce o 
LOUW ~ ~ r f f f C 8  A 
“5 
P 
-15 
I 
-t,o 
\ 
.. 
. . . . . . . . 
Upper swface o 
Lmw w f a c e  A 
. 
. .   . .  
-1.0 
-5 
P 
0 
( c )  M = 0.90, Continued. 
Ftgure 4.- Continued. 
I 
L 
- 1.5 
-1.0 
-2 
P 
0 
.S 
Upper =face o 
Lower surface A 
, , 
I I I I I I t I t 
./ 2 J .4 .5 6 J A 9 f.0 
I 
% 
21 
(c) M = 0.90. Concluded. 
Figure 4.- Continued. 
. .  . . . . . . . . . _ _  . . 
- 1.c 
-9 
P 
0 
.s 
I1 
. . .   . .  . . . 
- L 3  
-1.0 
-5 
P 
0 
.S 
I .  I I I I I I I I 
I 
(a) M = 0.93. 
Figure 4.- Conchcled. 
2 .3 a .7 B 
4.0 
P 
.5 OV"I 
-1.5 
pr" 
25 
I 
Upper d a c e  o 
Lower surface A 
.5 O 3  
( a )  M = 0.60. 
Figure 5.- Chordwise pressure distribution over a 35' sweptback wing, 
at the 46-percent-semispan station, equipped with a plug-type spoi ler  
aileron. = 0.03~;  gap unsealed. 
24 . . . .. . . . . .  . MACA RM L5X28 
Upper surface o 
iowef  stxface A 
") , n 
(b) M = 0.80. 
. . . .  . .- 
Figure 5.- Continued. 
NACA RM L5X28 
c 
I I I l I I I I I  
J . P . S U 5 . 6 I S S  
Q .  
Upper surface o 
Lower surfuce A 
(b) M = 0.80. Concluded. 
N cn 
- 1.5 
-1.0 
-3 
P 
0 
l.O, 
0 
( c )  M = 0.90. 
Figure 5.- Continued. 
. .. 
. I ,  
, .  ' I  ' ! 
NACA RFI L5X28 
t 
- 6 5  
-1.0 
-3 
P 
0 
25 
LC 
.I 2.3 . 4 d  6 3 . 8 . 9  (0 
5 
(c) M = 0.90. Concluded. 
Figure 5.- Continued. . 
P 
Upper strfoce o 
Lower surface A 
4 5 ,  I -Ld 
4 
-5 
P 
0 
.5 
111 
(a) M = 0.93. 
Figure 5.- Continued. 
' . X  
I , .  
NACA RM L52C28 - 
Upper surfuce o 
Lowe? surface A 
(a) M = 0.93. Concluded. 
Figure 5. - Concluded; 
30 - NACA BM L5X28 
P 
0 
.5 
(a) M = 0.60. 
Figure 6.- Chordwise pressure dis.trib.ution over a 35' sweptback w i n g ,  
aG the  46-percent-seespan  station,  equipped - a t h  a. plug-type spoiler 
aileron. 8 s  = -0.01~; gap unsealed. 
. . .  . 
NACA RM ~ 3 x 2 8  
Upper surface o 
Lower surface A 
P 
0 
(b) M = 0.80. 
Figure 6.- Continued. 
b 
P 
0 
4 
4.5 
-.5 
P 
0 
3 
LC 
0 
Upper surface a 
Lower surface a 
, I ,, , . 
.I 2 J r4 .5 4 .I .8 .9 1.b 
5 
(b) M = 0.80. Conchidea. -. 
Figure 6. - Cont.inued. . .  
.. 
* 
5x 
. 
P 
0 
i 
. 
i 
. _" .3 
-5 
P 
0 
.5 
-/.. , + 
33. LO O J B . 3 . 4 . . 5 b ~ . & . @ / D  
0 
( c )  M = 0.90. 
\ 
. .. . 
33 
Figure 6 .  - *  Concluded. 
34 . .. . .  . .  . .. NACA RM L52C28 . .  
. .. 
Upper  surface o 
Lower  surface a 
-. 5 
P 
0 
" . .  . 5i 
1. 
0 J .P .3 # .5 .6 .I .8 .9 ID 
b 
. " 
" . 7. 
.. " _ .  
. .. " - 
. .  
t -10, 
P 
0 
-2.0 
4.5 
40 
-3 
P 
0 
.5 
II: 
Upper surface o 
Lower surface P 
a 
fb) M = 0.80, 
Figure 7.- Continued. 
(b) M = 0.80. Concluded. 
Figure 7. - Continued. 
L 
. . . 
. 
' 37 
Lovtsr wface a -1 
( c )  M = 0.90. 
Figure 7.- Continued. 
I 
( c )  M = 0.90. Concluded. 
Figure 7.- Continued. 
. . .  
I 
.S 
P 
0 
.3 
11 
. .  . 
(a) M = 0.93. 
Figure 7.- Continued. 
. . .. 
I p 
(a) M = 0.93. Concluded 
Figure 7.- Concluded. 
. . 
I :  . . . .  . 
41 
JX 
-25 
P 
0 
- r l  
-3 
P 
0 
.5 
42 
-5 
P 
0 
t I 
' I  
rD ss 
O . I P . 3 c c . 5 S I . 8 . 9 1  
5 
(b) M = 0.80. 
Figure 8.- Continued. - 
NACA RM L52C28 43 
Upper surfoce o 
Lower surface A 
Configuration G 
-16 M=ao 
5 
(b) M = 0.80. Concluded. 
Figure 8..- Continued. 
- f.5 . .  
U ~ s r  surfoce a 
Lower surface A 
. ". 
-1.0 
P 
0 
d 
, . " 
. -.- ". 
C" 
( c )  E9 = 0.90. 
Figure 8.- Continued. 
! 
Upper surfoce o 
Lower surface A 
4 5 ,  I 
( c )  M = 0.90. Concl*d. 
Figure 8. -I Continued. 
. .  
Lower SUffOC8 A 
upper sraface o 
(d) M = 0.93. 
Figure 8.- Continued. 
.. . . . .  
c 
-3 
P 
0 
1 
(d) M = 0.93. Concluded. 
~igure 8.- concluaea. 4 
P 
NACA RM L52C28 
-.5 
P 
0 
.. . . I 
upper swface o 
Loww surface A 
0 . -  . , , = .  
I 
-3 
. .  
P 
0 
1 . 0 ~ " " " " '  
0 J 2 . 3  4 5 .6 J . 8  S ID 
% 
. " 
.. . 
,- 
(a) M =. 0.60. - 
Figure 9.- Chordwise  pressure distribution over .a 35' sweptback wing, . .. .. 
at the 46-percent-semispan  station, equipped w i t h  a plug-typs spoiler 
aileron. 8s = -0.04~; gap- unsealed. 
. ." 
._. _- - -I 
. I . 
NACA RM L5X28 49 
- I . ,  
P 
0 
c 
(b) M = 0.80. 
Figure 9:- Continued. 
50 
I I I I 1  I t  I I  
.I 2 .3 .4 3 6 .7 .8 9 I 
9 
-.5 
P 
0 
.5 
rL 
Upper surface o 
Lower surface A 
9 
1 -  
(b) M = 0180. Concluded. 
Figure 9.- ContFnued- 
.- . 
. .  
.- 
.. . "" 
. . .  
b 
- Lb 
.B 
Upper surface o 
Lower surface n 
4.0 
-3 
P 
0 
( c )  M = 0.90. 
Figure 9.- Continued. 
. .  
- 1.5 - 1.5 ." 
P 
n o  
I . " . "" 
-3 
P 
0 
. . . .  
( c )  M = 0.90. Concluded. 
Figure 9.- Continued. 
. .. I 
I 
-3 
P 
0 
.5 
. 
9. - Continued. 
.5 
(a) M = 0.93. Concluded. 
FI.gure 9.- Concluded. 
. . . . . .. 
NACA RM ~5x28 1. 55 
-3 -.5 
P P 
0 0 
.5 
fD 
O J P . 3 d S . 6 . 7 8 9 / ~  
9 
. . .  - 
-3 
P 
0 
.5 
-3 
P 
0 
.5 
. .. . 
56 - NACA RM ~ 5 2 ~ 2 8  
-1.5 "_ 
Upper surface o 
Lower surfoce A 
-40 I -ID, 1 
-3 
P 
0 
. ID 
0 I P . 3  4 . 5  6 . 7 . 8 . 9  IO 
f 
- 
.. . a 
t 
.. . . 
. . "  I I I I I I I I I  
.I 2 .3 .4 3 8 7 .8 .9 
0 
l l 1 1 1 l I l l  
J P . 3 . 4 . 5 6 . 7 . 8 9 ~  
5 
x-. . 
= 0.80. 
Figure .lo. - Continued. 
, 
NACA RM L52C28 
8X 
57 
0 
Upper surface o 
Lower surface A 
P 
0 
ID I I I I I I I I I I I 
0 J 2 J U .5 R . 7 . 8  .9 1.0 
% 
(b) M = 0.80. Concluded. 
Figure 10. - Continued. 
. . . .. 
W r  surfoce o 
Lower surfom A 
I 
I 
. .  . . I .  
: , '  - 
1 . 8  . . . . . . . . . 
I F 
.. . 
. -  
-IS 
-LO 
-5 
P 
0 
( c )  M = 0.90. Concluded. 
Figure 10.- Continued. 
I 
Lower surface A 
Upper surface o 
. .  
P 
0 
-5 
u 
"--i 
(a) M = 0.93. 
Figure 10.- Continued. 
. .  ' a , . . , . j  
I . : . ,  I .  . : I I ' ! : L ! .  .. : .. . . .  . .   . - .  
I 
NACA RM ~5x28 
Upper surface o 
Lower surface A 
61 
'I 
(d) M = 0.93. Conkluded. 
Figure 10. - Concluded. 
6 2 '  . -  . . L .  :. NACA Rh5 ~ 5 2 ~ 2 8  
.- I 
Cmfigurotion A I a=O M =EO 
-.5 I h 
P 
0 
-2. C
-1.5 
-/fi 
-.5 
P 
0 
.5 
L C  
Confiwraiim A 
a112 M1.60 
-2.0 
Confipratkm A 
r=8  M a . 6 0  
/.o I I  I l l  1 1 1 1  
O J P J A S . 6 . 7 . 8 . 9  
Q 
-I 
1 1  $ 1 1  1 1 1 1  
.I .P .3 A .5 6 .7 .e .9 
b 
( e )  M = 0.60. 
Figure .ll. - Chordwise p v s g r m . .  dis-tributioit over .a. 35' sweptback w i n g ,  
a t   t h e  46-percent-aemispan st.ation, equirrped with a plug-type 
fingered spoiler aileron. Conf'igrFratiop A; 6, = -0.04~; gap 
unsealed. . .. . . . .  . " . 
. . . . . . . . .. . , 
Conf@mtkw A 
0.0 M = B o  
P 
0 
(b) M = 0.80. 
Figure 11.- Continued. 
I 
" I 
P 7 
(b) M = 0.80. Concluded. 
Figure 11.- Cantlnued. 
i I 
c 
. .  . . .  . .   . .  .. . .  . . I 
Upper surface o 
LOWer W f O C 8  A 
Figure 
- 1.5 
-1.0 
-3 
P 
0 '  
I 
M 0.90. 
11.- Continued. 
I 
. .  . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 
( c )  M = 0.90. Concluded. 
Pigme U.- Continued. 
VI 
h) m 
r 
x 
. .  
. . . . . . .  
L 
.. . 
I 
. . 
U , w  surface o 
LOWW SWfOCS A 
-5 
P 
0 
-15 
- I .  
-5 
P 
0 
.5 
/a , 
(a) hi = 0.93. 
Figure 11.- Concluded, 
. . . ". 
F 9 1  
! 
i 
Umer surface o 
Lower surface A 
. . ." 
( a )  M = 0.60. 
Figure 12." .Chord%fise... pressure dist r ibut ion over a 35O sweptback w i n g ,  
at the 46-percent-semispan.  station, equipEd with a .plug7t31p.e- 
fingered spailer.:aileyo.n. .. Configuration B; . 6, = -0.04~; gap 
unsealed. 
. .  
- .  
- ..x- 
. . - 
. . .  
/. - -  
. . . _  
. .  . .  
:c 69 
4.5 . 
-LO 
, -3 
P 
0 
3 
f.0 
I 
-1.5 
40 
-5 
P 
0 
d 
1.0 
Configuratbn 8 
u - 0  M-BO 
1 
d 
I 
Configuratii B 
r = 8  bi-BO 
upper surfoce o 
Lower surfoce A 
-D f 
(b) M = 0.80. 
Figure 12.- Continued. 
I 
-.5 
P 
0 
-L5 
-1.0 
-.5 
P 
0 
.5 
c 
LO 
( c )  M = 0.9. 
Figure 12.- Continued. 
1 , *  
. . . . . . . . 
. . . .  . .  . . ,  
I 
72 
I a.0 M.33 I 
Figure 12, - Concluded.. 
lox 
. 
73 . 
Configuration C 
0.0 M-.60 I 
-3 
P 
0 
.5 - 
o . / P 3 . 4 5 6 . 7 8 9 1 o  
8 
Upper surface o 
Lower surface A 
-3 
P 
0 
.5 
1.0 
0 .I 2.3 4 . 5  B 3 . 8 9  ID 
9 
(a) M = 0.60. 
Figure 13.'- Chordwise pressure dietribution over a 35' sweptback w F n g ,  
a t   t h e  k6-percent-semispan s ta t ion,  equfpped with a plug-type 
fingered spoiler. aileron. Configuration C; 6, =- -0.04~; gap 
unsealed. 
74 . . .  NACA RM 13x28 
Conflgumfbn C 
a m 0  M*.BO 
I I I L I I I I I  
./ P J .4 5 B .7 .8 9 I 
Q 
p \  
-cT 
. .  ". 
c 
- . -  . . . . _. . . 
Upper surface o 
Lower surface 11 
(b) M = 0.80. , 
Figure 13.- Continued. - 
I 
I I 
. .  . I 
I 
-15 1 
-.5 
P 
0 
.5 
5 5 
P 
0 
b \ 
( c )  M = 0.90. Concluded. 
F i m  13.- Concluded. 
' ,  
I 
SECURITY I N F O R M A T I O N  
c . .  c 
i 
I 


Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons

Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons

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