Integral moment method of L.Lees, B.L. Reeves for interacting, laminar boundary layer is applied to problem of supersonic flows; approach requires no prior knowledge of separation point and can be used to treat relatively weak interaction, including fully attached flow; it starts with small perturbations of self-induced interaction on flat plate; it can be applied to flows with hypersonic interaction parameter, based on distance of beginning station of interaction to leading edge, of order one; satisfactory agreement with theory was obtained for corresponding experiments conducted in Mach 6 wind tunnel at Graduate Aeronautical Laboratory of California Institute of Technology. (23296)


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    Title :

    Supersonic laminar boundary layer along two-dimensional adiabatic curved ramp


    Additional title:

    AIAA J


    Contributors:
    Ko, D.R.S. (author) / Kubota, T. (author)

    Published in:

    AIAA Journal ; 7 , n 2


    Publication date :

    1969


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :