Techniques for the enhancement of mixing in a scramjet combustor are presently investigated experimentally with wall-mounted parallel injector ramps that are speculated to prove useful at high speeds in the extraction of thrust from engine- or airframe-coolant hydrogen. The injector ramps were designed to generate a reflected shock wave from the duct top wall which will pass just downstream of the fuel injectors' barrel shock; fuel injector Mach number is 1.7, in virtue of which an underexpanded fuel flow is generated. Shadowgraph and UV-TV flow visualizations were conducted for three duct configurations.


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    Title :

    Evaluation of parallel injector configurations for supersonic combustion


    Contributors:

    Publication date :

    1989-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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