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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:
    G. Masuya (author) / N. Chinzei (author) / K. Kudo (author) / A. Murakami (author) / T. Komuro (author)

    Publication date :

    1983


    Size :

    22 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Study of Air Breathing Rockets. 3: Supersonic Mode Combustors

    G. Masuya / N. Chinzel / K. Kudo et al. | NTIS | 1983


    Liquid rockets for supersonic sleds

    Roth, Jr., C.E. / Poland, H.M. | Engineering Index Backfile | 1957


    Detection of supersonic rockets using passive bistatic radar

    Malanowski, Mateusz / Borowiec, Krzysztof / Rzewuski, Stanislaw et al. | IEEE | 2018



    Supersonic inlet buzz margin control of ducted rockets

    Shi, X / Chang, J-T / Bao, W et al. | SAGE Publications | 2010