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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    Title :

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


    Contributors:

    Publication date :

    1974-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English