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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    A Laser Velocimeter Flow Survey Above a Stalled Wing


    Contributors:
    W. H. Young (author) / J. F. Meyers (author) / D. R. Hoad (author)

    Publication date :

    1978


    Size :

    138 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    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

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