Second- and third-order, noncentered finite-difference schemes are described for the numerical solution of the hyperbolic equations of fluid dynamics. The advantages of noncentered methods over the more conventional centered schemes are: simpler programming logic, nonhomogeneous terms are easily included, and generalization to multidimensional problems is direct. Second- and third-order methods are compared with regard to dissipative and dispersive errors and shock-capturing ability. These schemes are then used in a shock-capturing technique to determine the inviscid, supersonic flow field surrounding space shuttle vehicles (SSV). Resulting flow fields about typical pointed and blunted, delta-winged SSVs at angle of attack are presented and compared with experiment.


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    Titel :

    Computation of space shuttle flow fields using noncentered finite-difference schemes.


    Beteiligte:
    Kutler, P. (Autor:in) / Lomax, H. (Autor:in) / Warming, R. F. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1972 ; San Diego, CA


    Erscheinungsdatum :

    01.01.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :