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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    Titel :

    Supersonic laminar boundary layer along two-dimensional adiabatic curved ramp


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Ko, D.R.S. (Autor:in) / Kubota, T. (Autor:in)

    Erschienen in:

    AIAA Journal ; 7 , n 2


    Erscheinungsdatum :

    1969


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :