A shock tunnel has been used to study the hypersonic flow around typical re-entry bodies and space planes. From surface pressure and heat transfer measurements, pressure coeficients and Stanton numbers are deduced. The experimental data, achieved with different model geometries and for various flow conditions, could be correlated quite well by relations which have been found for blunt cone flows. The correlation takes into account entropy layer effects caused by curved shocks and viscous interaction phenomena. Variation of the stagnation temperature for constant Mach and Reynolds number has a strong influence on these two effects. For a thin body, where the entropy layer effect is not very strong, its influenced could be separated from the correlation relation. The corresponding experimental data also show a good correlation.


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    Title :

    Hypersonic model testing in a shock tunnel


    Additional title:

    Erprobung eines Hyperschallmodells im Stoßwellenkanal


    Contributors:
    Olivier, H. (author) / Grönig, H. (author) / Bozec, A. Le (author)

    Published in:

    AIAA Journal ; 33 , 2 ; 262-265


    Publication date :

    1995


    Size :

    4 Seiten, 5 Bilder, 8 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Hypersonic Model Testing in a Shock Tunnel

    Olivier, H. | Online Contents | 1995


    Hypersonic model testing in a shock tunnel

    Olivier, H. / Groenig, H. | AIAA | 1993


    Hypersonic model testing in a shock tunnel

    Olivier, H. / Groenig, H. / Le Bozec et al. | AIAA | 1995


    Hypersonic Model Testing in a Shock Tunnel

    Olivier, H. / Groenig, H. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1993