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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Secondary liquid injection into supersonic airstream


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Forde, J.M. (author) / Molder, S. (author) / Szpiro, E.J. (author)

    Published in:

    Publication date :

    1966


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English