An effort is made to quantify the stagnation pressure losses associated with shock-wave systems that may be present in such high Mach number flows as those of scramjet hypersonic diffusers. If the shock-related contribution turns out to be much larger than that attributable to viscous effects, a designer could introduce methods for the minimization of the shock system's scale; in particular, the size of the normal shock should be reduced. The angles presently treated may be approached during vehicle maneuvering or other transients.


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    Titel :

    Prediction of inviscid stagnation pressure losses in supersonic inlet flows


    Beteiligte:
    Azevedo, David J. (Autor:in) / Liu, Ching Shi (Autor:in) / Rae, William J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.10.1990



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :