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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    Title :

    New theoretical solution of laminar, hypersonic near Wake


    Additional title:

    AIAA J


    Contributors:
    Weiss, R.F. (author)

    Published in:

    AIAA Journal ; 5 , n 12


    Publication date :

    1967


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :