To simulate high heating rates encountered in hypersonic flow, exhaust gases from rocket are used to power supersonic tunnel producing gas temperature of 4500 R; calibration pressure data indicate reproducibility of test conditions; physical, transport, and 1-dimensional aerodynamic data for combustion products of ammonia and oxygen included.


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    Titel :

    Mach 4 rocket-powered supersonic tunnel using ammonia-oxygen as working fluid


    Weitere Titelangaben:

    NACA -- Tech Note


    Beteiligte:
    Graham, R.W. (Autor:in) / Costilow Guentert, E. (Autor:in) / Huff, V.N. (Autor:in)


    Erscheinungsdatum :

    1958


    Format / Umfang :

    53 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    A Mach 4 Rocket-powered Supersonic Tunnel Using Ammonia-oxygen as Working Fluid

    Graham, Robert W / Guentert, Eleanor Costilow / Huff, Vearl N | NTRS | 1958


    A Mach 4 rocket-powered supersonic tunnel using ammonia-oxygen as working fluid

    Graham, Robert W. / Costilow Guentert, Eleanor / Huff, Vearl N. | TIBKAT | 1958



    Mach 3 wind tunnel test of mixed compression supersonic inlet

    MURAKAMI, AKIRA / YANAGI, RYOJI / SHINDO, SHIGEMI et al. | AIAA | 1992