Interactive-boundary-layer method developed for computations of steady flow, extended under assumption of quasi-steady flow, to computations of evolution of two-dimensional flow about oscillating airfoil under light-dynamic-stall conditions. Represents advance toward ability to compute unsteady flows at even greater angles of attack with solutions of equations normally used for description of boundary-layer flows on airfoils prior to stall. Important in practical studies of flow on blades of helicopter rotors, axial compressors, and turbines.


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    Title :

    Interactive-Boundary-Layer Computations For Oscillating Airfoil


    Contributors:
    Carr, L. W. (author) / Cebeci, T. (author) / Jang, Hong-Ming (author)

    Published in:

    Publication date :

    1993-02-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :