The PARC3D code was selected by the authors to analyze a variety of complex and high-speed flow configurations. Geometries considered for code validation include ramps and corner flows, which are characteristic of inlets and nozzles. Flows with Mach numbers of 3-14 were studied. Both two- and three-dimensional experimental data for shock-boundary-layer interaction were considered to validate the code. A detailed comparison of various flow parameters with available experimental data is presented; agreement between the solutions and the experimental data in terms of pitot pressure profiles, yaw-angle distributions, static pressures, and skin friction is found to be very good. In addition, two- and three-dimensional flow calculations were performed for a hypersonic nozzle. Comparison of the wall pressure results with the published solutions is made for the two-dimensional case.


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    Title :

    Three-dimensional viscous flow computations of high area ratio nozzles for hypersonic propulsion


    Contributors:


    Publication date :

    1991-02-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Three-dimensional viscous flow computations of high area ratio nozzles for hypersonic propulsion

    REDDY, D. R. / HARLOFF, G. J. / Sverdrup Technology et al. | AIAA | 1991


    Reactive and Viscous Flow in Hypersonic Nozzles

    Zeitoun, D. | Online Contents | 1994


    Reactive and viscous flow in hypersonic nozzles

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    Two- and three-dimensional viscous computations of a hypersonic inlet flow

    KUNIK, WILLIAM / BENSON, THOMAS / NG, WING-FAI et al. | AIAA | 1987


    Reactive and viscous flow in hypersonic nozzles

    Zeitoun, D. / Boccaccio, E. / Druguet, M.C. et al. | Tema Archive | 1994