Current design philosophy for hydrogen-fueled, scramjet-powered hypersonic aircraft results in configurations with strong couplings between the engine plume and vehicle aerodynamics. The experimental verification of the scramjet exhaust simulation is described. The scramjet exhaust was reproduced for the Mach 6 flight condition by the detonation tube simulator. The exhaust flow pressure profiles, and to a large extent the heat transfer rate profiles, were then duplicated by cool gas mixtures of Argon and Freon 13B1 or Freon 12. The results of these experiments indicate that a cool gas simulation of the hot scramjet exhaust is a viable simulation technique except for phenomena which are dependent on the wall temperature relative to flow temperature.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Validation of scramjet exhaust simulation technique at Mach 6


    Contributors:
    Hopkins, H. B. (author) / Konopka, W. (author) / Leng, J. (author)

    Publication date :

    1979-03-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Validation of Scramjet Exhaust Simulation Technique at Mach 6

    H. B. Hopkins / W. Konopka / J. Leng | NTIS | 1979


    Validation of scramjet exhaust simulation technique

    Hopkins, H. B. / Konopka, W. / Leng, J. | TIBKAT | 1976


    Vaidation of scramjet exhaust simulation technique at Mach 6

    Hopkins, H. B. / Konopka, W. / Leng, J. | TIBKAT | 1979


    Simulation of Hypersonic Scramjet Exhaust

    R. A. Oman / K. M. Foreman / J. Leng et al. | NTIS | 1975


    Simulation of hypersonic scramjet exhaust

    Oman, R. A. / Foreman, K. M. / Leng, J. et al. | NTRS | 1975