Solution is obtained by dividing flowfield into three subregions; vortical outer flow, resulting from inviscid expansion of boundary layer, is solved by method-of-characteristics; thin viscous layer above dividing streamline is treated with modified Oseen solution of boundary-layer equations; recirculation region is solved by finite-difference representation of full Navier-Stokes equations; iteration scheme is developed and shown to yield converged solutions of coupled flowfield; complete solutions up to rear stagnation point are found to be possible for range of base pressures.


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    Titel :

    New theoretical solution of laminar, hypersonic near Wake


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Weiss, R.F. (Autor:in)

    Erschienen in:

    AIAA Journal ; 5 , n 12


    Erscheinungsdatum :

    1967


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :