Analysis of hypersonic ramjet cycles shows that supersonic combustion is requirement; paper presents experimental results where supersonic combustion in constant area duct is initiated by shock wave, evaluates possibility of analyzing data with one-dimensional flow equations, determines how closely current chemical kinetic computations agree with experimental results, and discusses problems encountered; shock-induced combustion is experimentally feasible in ducted flow, and can be controlled by varying inlet temperature, pressure, Mach number, on fuel concentration.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Shock-induced supersonic combustion in constant-area duct


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1965


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Shock-induced supersonic combustion in a constant-area duct

    CUNNINGHAM, T. H. M. / RUBINS, P. M. | AIAA | 1965


    Combustion and Pseudo-Shock Wave in Diverging Supersonic Duct Flow

    Masuya, G. / Han, M. / Amano, M. et al. | British Library Conference Proceedings | 2005


    Shock Wave Train Control in Supersonic Duct

    Leonov, Sergey B. / Andrews, Philip S. / Ombrello, Timothy et al. | AIAA | 2024



    Applications of shock-induced mixing to supersonic combustion

    YANG, JOSEPH / KUBOTA, TOSHI / ZUKOSKI, EDWARD E. | AIAA | 1993