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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    Titel :

    Interaction between detonation waves and flowfields


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Mc Kenna, W.W. (Autor:in)

    Erschienen in:

    AIAA Journal ; 5 , n 5


    Erscheinungsdatum :

    1967


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




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