A simple method for predicting the axial distribution of supersonic combustor thrust potential is described. A complementary technique for illustrating the spatial evolution and distribution of thrust potential and loss mechanisms in reacting flows is developed. Wall jet cases and swept ramp injector cases for Mach 17 and Mach 13.5 flight enthalpy inflow conditions are numerically modeled and analyzed using these techniques. The visualization of thrust potential in the combustor for the various cases examined provides a unique tool for increasing understanding of supersonic combustor performance potential.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    A comparative study of scramjet injection strategies for high Mach numbers flows


    Contributors:

    Publication date :

    1992-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    A comparative study of scramjet injection strategies for high Mach numbers flows

    RIGGINS, D. / MCCLINTON, C. / ROGERS, R. et al. | AIAA | 1992


    Investigation of scramjet injection strategies for high Mach number flows

    Riggins, D. W. / McClinton, C. R. / Rogers, R. C. et al. | AIAA | 1995




    Hydrocarbon and Hydrogen-Fueled Scramjet Cavity Flameholder Performance at High Flight Mach Numbers

    Boyce, Russell / Houwing, Frank / Neely, Andrew et al. | AIAA | 2003