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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    Title :

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


    Additional title:

    NACA -- Tech Note


    Contributors:


    Publication date :

    1958


    Size :

    53 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    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