A rocket based combined cycle inlet geometry has undergone wind tunnel testing and computational analysis with Mach 4 flow at the inlet face. Performance parameters obtained from the wind tunnel tests were the mass capture, the maximum back-pressure, and the self-starting characteristics of the inlet. The CFD analysis supplied a confirmation of the mass capture, the inlet efficiency and the details of the flowfield structure. Physical parameters varied during the test program were cowl geometry, cowl position, body-side bleed magnitude and ingested boundary layer thickness. An optimum configuration was determined for the inlet as a result of this work.


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    Title :

    A Combined Experimental/Computational Investigation of a Rocket Based Combined Cycle Inlet


    Contributors:

    Conference:

    Aerospace Sciences ; 2001 ; Reno, NV, United States


    Publication date :

    2001-01-01


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English





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