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.


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    Title :

    Comparison of two flow surveys above stalled wings


    Contributors:

    Conference:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA


    Publication date :

    1979-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Comparison of two flow surveys above stalled wings

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    A Laser Velocimeter Flow Survey Above a Stalled Wing

    W. H. Young / J. F. Meyers / D. R. Hoad | NTIS | 1978


    A laser velocimeter flow survey above a stalled wing

    Young, W. H., Jr. / Meyers, J. F. / Hoad, D. R. | NTRS | 1978