Paper derives equations governing performance of ramjet using detonative combustion, and evaluates performance; engine layout permits normal detonation wave stabilized in diverging combustion chamber passage, or oblique wave stabilized on wedge; lower speed limit of detonative ramjet and cycle calculation; difficulties encountered by ramjets designed for hypersonic speeds may be alleviated if ramjet is designed to burn incoming air at supersonic velocities in stabilized detonation wave. (see also abstract in SAE -- J v 69 n 11 Nov 1961 p 80-1)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Performance of hypersonic Ramjet using detonative combustion


    Additional title:

    SAE -- Paper


    Contributors:
    Arens, M. (author)

    Conference:

    SAE Meeting ; 1961



    Publication date :

    1961


    Size :

    8 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Performance of hypersonic ramjet using detonative combustion

    Arens, M. | Engineering Index Backfile | 1961



    Hypersonic Shock-Induced Combustion Ramjet Performance Analysis

    Sislian, J. P. / Dudebout, R. / AIAA | British Library Conference Proceedings | 1993


    Hypersonic flight performance improvements by overfueled ramjet combustion

    SACHS, G. / BAYER, R. / LEDERER, R. et al. | AIAA | 1991


    Investigation of Detonative Combustion Characteristics

    Han, Q.-x. / Wang, J.-h. / Wang, B. | British Library Online Contents | 2002