A theoretical analysis for the inlet of the NASA Hypersonic Research Engine (HRE) Aerothermodynamic Integration Model (AIM) has been undertaken by use of a method-of-characteristics computer program. The purpose of the analysis was to obtain pretest information on the full-scale HRE inlet in support of the experimental AIM program (completed May 1974). Mass-flow-ratio and additive-drag-coefficient schedules were obtained that well defined the range effected in the AIM tests. Mass-weighted average inlet total-pressure recovery, kinetic energy efficiency, and throat Mach numbers were obtained.


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    Titel :

    An inlet analysis for the NASA hypersonic research engine aerothermodynamic integration model


    Beteiligte:
    Andrews, E. H., Jr. (Autor:in) / Russell, J. W. (Autor:in) / Mackley, E. A. (Autor:in) / Simmonds, A. L. (Autor:in)

    Erscheinungsdatum :

    1974-11-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch