Study of supersonic combustion ramjet (scramjet) and its mode of combustion involving fuel jet diffusing into supersonic oxidizing stream; simplified model, based on Newtonian flow concepts, for prediction of injectant path, and penetration distance for secondary liquid injection into supersonic stream, is presented; over 100 experiments were performed for water injection into Mach 3 supersonic airstream, for ranges of initial injection angle (28° upstream to 31° downstream), injector diameters (0.014 to 0.035 in.), and injectant total pressures (65 to 365 psia); simplicity of theory and accuracy with which it agrees with experiments appears to favor its use.


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    Titel :

    Secondary liquid injection into supersonic airstream


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Forde, J.M. (Autor:in) / Molder, S. (Autor:in) / Szpiro, E.J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch