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AIAA-89-0537 Numerical Simulation of Vortical Flows on Flexible Wings G. Guruswamy , NASA Ames Research Center, Moffett Field, California
d
27th Aerospace Sciences Meeting January 9-12, 19891Ren0, Nevada
RECTANGULAR WING NACA 64A010, AR = 4.0. M z 0.80, ,L = 0.0 , Re = 2.4 X 10'
~- NAVIER STOKES - - - E U L E R
90% SEMI SPAN
$ 0 ' t i 0
SEMI-INFINITE RECTANGULAR WING IN RAMP MOTION, NACAO012 A IRFOIL
M, ~ 0.3. A = 0.025, Re ~ 2.5 x lo6
-10 4
c! = 15.5" a -5 " > 0
Z 0 t; ' 5 2
10
1 - 4 10 0
0.
> 0
+ YI
3
" -2
$ O
2 2
6
0 .2 .4 .6 .8 1.0 XIC
6
RECTANGULAR WING I N RAMP MOTION AR ~ 4.0. NACA oni5. M ~ 0.5. A ~ 0.3. ~e ~ Goono
it. deg TIME 8.8 0.31 13.5 0.47
. . . . . 18.1 0.63 !R) - 20.0 0.79
20.0 0.94
.........
. I - - l 0 1 .o
TIME, rad
-4 I
7
RECTANGULAR WING I N RAMP M O r i O N NACA 0015, AR = 4.0, M = 0.50, A ~ 0.3, 7 ~ 0.94. R e i 60000
-4 a
V
a V
x/c
RECTANGULAR WING IN RAMP MOTION NACA 0015, AR ~ 4.0. M = 0.50. A = 0.3. i = 0.94. R e = 60000
. . . RIGID WING FLEXIBLE WING
v
- 1
30
0 10 20 30 TIME,deg