An experimental study was made on supersonic mode combustors of an air breathing rocket engine. Supersonic streams of room-temperature air and hot fuel-rich rocket exhaust were coaxially mixed and burned in a conically diverging duct of 2 degrees half-angle. The effect of air inlet Mach number and excess air ratio was investigated. Axial wall pressure distribution was measured to calculate one dimensional change of Mach number and stagnation temperature.


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    Titel :

    Study of Air Breathing Rockets (III): Supersonic Mode Combusters


    Beteiligte:
    G. Masuya (Autor:in) / N. Chinzei (Autor:in) / K. Kudo (Autor:in) / A. Murakami (Autor:in) / T. Komuro (Autor:in)

    Erscheinungsdatum :

    1983


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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