The results of Murman and Krupp (1971) are used to develop a procedure for computing a transonic flow about a finite lifting wing. A small disturbance equation describing the velocity potential of three-dimensional wings is solved in the process. The procedure is applied to a wing with a symmetric biconvex airfoil section in a zero-incidence subsonic flow, to a supersonic rectangular lifting wing with a sharp leading edge and to a subcritical nonlifting rectangular wing with a blunt leading edge.


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    Title :

    Computation of transonic flow about finite lifting wings.


    Contributors:

    Published in:

    Publication date :

    1972-07-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Computation of Transonic Flow about Finite Lifting Wings

    P.A. NEWMAN AND E.B. KLUNKER | AIAA | 1972


    Transonic flow past lifting wings.

    Norstrud, H. | NTRS | 1973


    Transonic flow past lifting wings.

    NORSTRUD, H. | AIAA | 1973



    Computation of viscous transonic flow about a lifting airfoil

    WALITT, L. / KING, L. / LIU, C. | AIAA | 1977