The desig of reusable spacecraft such as the Hermes (currently under consideration by the European Space Agency) will be enhanced by an accurate computational prediction of the flowfield during hypersonic re-entry into the atmosphere. This is particularly important on the leeward side of lifting surfaces where vortex phenomena have been judged responsible for intense local heating. A kinetic theory based Navier-Stokes solver has been implemented on a parallel supercomputer (Intel iPSC Touchstone Delta) to study the leeward flowfield of a blunt nosed delta wing at 30-deg incidence at hypersonic speeds. Computational Results are presented for a series of grids for both inviscid and laminar viscous flows. Our present aim is to make a detailed comparison of the shock structure generated above the leeward surface for the inviscid and laminar viscous flows at Reynolds numbers of 2.25x105 and 2.25x106. In addition, comparisons are made between the present and other independant calculations of the same flows.


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    Title :

    Numerical study of hypersonic leeward flow over a blunt nosed delta wing


    Additional title:

    Numerische Untersuchung der leewärtigen hypersonischen Strömung über einen Deltaflügel mit stumpfer Flügelnase


    Contributors:

    Published in:

    AIAA Journal ; 33 , 9 ; 1626-1633


    Publication date :

    1995


    Size :

    8 Seiten, 16 Bilder, 1 Tabelle, 15 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Numerical study of hypersonic leeward flow over a blunt nosed delta wing

    Mallett, E. R. / Pullin, D. I. / Macrossan, M. N. | AIAA | 1995


    Approximate viscous shock-layer method for hypersonic flow over blunt-nosed bodies

    Grantz, A. C. / Dejarnette, F. R. / Thompson, R. A. | NTRS | 1990


    Approximate viscous shock-layer method for hypersonic flow over blunt-nosed bodies

    GRANTZ, A. C. / DEJARNETTE, F. R. / THOMPSON, R. A. | AIAA | 1990