The NASA Hypersonic Research Engine (HRE) Project was initiated for the purpose of advancing the technology of airbreathing propulsion for hypersonic flight. A large component (inlet, combustor, and nozzle) and structures development program was encompassed by the project. The tests of a full-scale (18 in. diameter cowl and 87 in. long) HRE concept, designated the Aerothermodynamic Integration Model (AIM), at Mach numbers of 5, 6, and 7. Computer program results for Mach 6 component integration tests are presented.


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    Title :

    Hypersonic research engine/aerothermodynamic integration model, experimental results. Volume 1: Mach 6 component integration


    Contributors:

    Publication date :

    1976-04-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English