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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    Title :

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


    Contributors:
    Kutler, P. (author) / Lomax, H. (author) / Warming, R. F. (author)

    Conference:

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


    Publication date :

    1972-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :