The results of an experimental investigation of shock-induced stall and leading-edge stall on a 64A010 airfoil section are presented. Advanced nonintrusive techniques - laser velocimetry and holographic interferometry - were used in characterizing the inviscid and viscous flow regions. The measurements include Mach contours of the inviscid now regions, and mean velocity, flow direction, and Reynolds shear stress profiles in the separated regions. The experimental observations of this study are relevant to efforts to improve surface-pressure prediction methods for airfoils at or near stall.


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    Title :

    Transonic Flow Past a Symmetrical Airfoil at High Angle of Attack


    Contributors:

    Conference:

    Fluid and Plasma Dynamics Conference ; 1979 ; Williamsburg, VA, United States


    Published in:

    Publication date :

    1981-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Transonic Flow Past a Symmetrical Airfoil at High Angle of Attack

    D. A. Johnson / W. D. Bachalo / F. K. Owen | AIAA | 1981


    Transonic flow past a symmetrical airfoil at high angle of attack

    Johnson, D. A. / Owen, F. K. / Bachalo, W. D. | NTRS | 1979


    Transonic Flow Past a Symmetrical Airfoil at High Angle of Attack

    D. A. Johnson / W. D. Bachalo / F. K. Owen | NTIS | 1981


    Transonic flow past a symmetrical airfoil at high angle of attack

    JOHNSON, D. / OWEN, F. / BACHALO, W. | AIAA | 1979