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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    Titel :

    Evaluation of parallel injector configurations for supersonic combustion


    Beteiligte:
    Northam, G. Burton (Autor:in) / Greenberg, I. (Autor:in) / Byington, C. S. (Autor:in)

    Erscheinungsdatum :

    01.07.1989


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Evaluation of parallel injector configurations for supersonic combustion

    NORTHAM, G. / GREENBERG, I. / BYINGTON, C. | AIAA | 1989


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