Investigation of behavior of detonation wave in oncoming flowing stoichiometric mixture of hydrogen-oxygen gases was made to study combustion instability in rocket motors and possible application to supersonic combustion; apparatus was designed to measure relative wave velocity and to photograph wave profile as fully developed detonation wave propagated against flow; Mach number of flowing unburned gas was varied from 0.14 to 4; subsonic flow results were in good agreement with Chapman-Jouguet theory; but supersonic flow results indicated strong detonation wave.


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    Title :

    Interaction between detonation waves and flowfields


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 5 , n 5


    Publication date :

    1967


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




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