The heavy reliance on CFD in the design of hypersonic flight vehicles emphasizes the importance of choosing computationally efficient techniques. As a result, the development and application of space-marching flow solvers for the parabolized Navier-Stokes equations have received considerable attention in the past decade. This paper summarizes a space-marching approach used at NASA Ames Research Center for the analysis of hypersonic vehicle forebodies. Aspects of the simulation process are addressed that contain features unique to space-marching flow solvers, such as grid generation, initial condition specification, and finite-rate chemistry models. For completeness, sections are also included on turbulence modeling and equilibrium air chemistry modeling. The discussion includes an overview of the computational methods utilized as well as a number of relevant results.


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    Titel :

    Application of space-marching methods to hypersonic forebody flow fields


    Beteiligte:

    Kongress:

    AIAA, International Aerospace Planes Conference ; 1992 ; Orlando, FL, United States


    Erscheinungsdatum :

    1992-12-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



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