A laser velocimeter operating in the backscatter mode was used to survey the flow about a stalled wing installed in the Langley V/STOL tunnel. Mean velocities and magnitudes of velocity fluctuations were calculated from measurements of two orthogonal components of velocity. Free shear mixing layers above and below a large separated flow region were defined. Velocity power spectra were calculated at two points in the flow field. The flow-field survey was carried out about a rectangular aspect-ratio-8 wing with an airfoil section. The wing angle of attack was 19.4 deg, the Mach number was 0.148, and the nominal Reynolds number was 1 x 1 million.


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    Title :

    A laser velocimeter flow survey above a stalled wing


    Contributors:

    Publication date :

    1978-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


    A laser velocimeter flow survey above a stalled wing

    Young, Warren H. / Meyers, James F. / Hoad, Danny R. | TIBKAT | 1978


    A Laser Velocimeter Flow Survey Above a Stalled Wing

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


    Laser velocimeter systems analysis applied to a flow survey above a stalled wing

    Young, Warren H. / Meyers, James F. / Hepner, Timothy E. | TIBKAT | 1977



    Comparison of two flow surveys above stalled wings

    YOUNG, JR., W. / HOAD, D. | AIAA | 1979