AIAA-89-0537 Numerical Simulation of Vortical Flows on Flexible Wings G. Guruswamy , NASA Ames Research Center, Moffett Field, California

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27th Aerospace Sciences Meeting January 9-12, 19891Ren0, Nevada

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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

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c! = 15.5" a -5 " > 0

Z 0 t; ' 5 2

10

1 - 4 10 0

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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

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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

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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

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30

0 10 20 30 TIME,deg

RECTANGlJLAR WING IN RAMP MOTION

NACA 0015. AR .~ 4.0. M ~- 0.50, A = 0.3 , i ~ 0.94, R e ~ 60000