Modifications to a 20-megawatt arc-heated facility for testing a hydrogen-burning, airframe-integratable, subscale, scramjet model are described. Arc-heated flow is mixed with unheated air to furnish a test flow duplicating Mach 7 flight. (Stagnation temperature is 2220 K.) Modifications to the commercially available heater to improve survivability and smoothness are described. Pitot profiles show uniform flow and a slightly thinner nozzle boundary layer than predicted. Comparison of the tunnel boundary layer, which will be ingested by the engine model, with the boundary layer that a flight engine might ingest from its vehicle forebody shows a difference in the density distribution through the boundary layer. Calculations of wall heating and transient wall temperatures of the engine model show that for a 30-sec burn, the heat sink model requires cooling at selected locations to avoid thermal-stress, cycle-life problems. Model performance predictions show that fuel equivalence ratio and nozzle exit area both have large effects on thrust. Average inlet entrance Mach number (as affected by boundary-layer ingestion) has little effect on thrust.


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    Title :

    Langley facility for tests at Mach 7 of subscale, hydrogen-burning, airframe-integratable, scramjet models


    Contributors:

    Conference:

    Aerospace Sciences Meeting ; 1976 ; Washington, DC


    Publication date :

    1976-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Langley Facility for Tests at Mach 7 of Subscale, Hydrogen-Burning, Airframe-Integratable, Scramjet Models

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