A laser velocimeter (LV) surveyed the flow above two stalled wings. Each wing was tested in a different wind tunnel at different Mach numbers. The low-Mach-number test had an angle of attack of 19.4 deg, 0.15 Mach number, and 1 x 1,000,000 Reynolds number. The mean velocities above the reversed, separated flow were closely modeled by error function profiles. Thus, the flow resembled a turbulent free-shear layer. The high-Mach-number test had an angle of attack of 19.5 deg, 0.49 Mach number, and 1,400,000 Reynolds number. A series of strong, discrete vortices were shed from the airfoil crest at regular intervals. Both tests demonstrated the importance of the unsteady part of the velocities.
Comparison of two flow surveys above stalled wings
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA
01.01.1979
Aufsatz (Konferenz)
Keine Angabe
Englisch
Comparison of two flow surveys above stalled wings
AIAA | 1979
|A laser velocimeter flow survey above a stalled wing
TIBKAT | 1978
|A Laser Velocimeter Flow Survey Above a Stalled Wing
NTIS | 1978
|A laser velocimeter flow survey above a stalled wing
NTRS | 1978
|