The study of the interaction between detonation waves and flowfields could lead to a better understanding of combustion instability in rocket motors and to possible application to supersonic combustion. Apparatus was designed to measure the relative wave velocity and to photograph the wave profile as a fully developed detonation wave propagated against a flow of stoichiometric mixture of hydrogen-oxygen gases. The Mach number of the flowing unburned gas was varied from 0.14 to 4. The subsonic flow results were in good agreement with the Chapman-Jouguet theory; but the supersonic flow results indicated a strong detonation wave. The schlieren photographs of the wave indicated propagation into the boundary layer, and a convex curvature of the complete wave front was observed in the Mach 4 experiments. Velocity measurements indicated that the detonation wave was steady, but in some experiments disturbances were observed downstream of the detonation wave. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Interaction Between Detonation Waves and Flowfields


    Contributors:

    Publication date :

    1967


    Size :

    8 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Interaction between detonation waves and flowfields

    Mc Kenna, W.W. | Engineering Index Backfile | 1967


    Quasi-Steady Modeling of Rotating Detonation Engine Flowfields

    Fievisohn, Robert T. / Yu, Kenneth H. | AIAA | 2015



    Interaction of Gun Exhaust Flowfields

    E. M. Schmidt / R. E. Gordnier / K. S. Fanslert | AIAA | 1984