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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    Titel :

    Hypersonic model testing in a shock tunnel


    Weitere Titelangaben:

    Erprobung eines Hyperschallmodells im Stoßwellenkanal


    Beteiligte:
    Olivier, H. (Autor:in) / Grönig, H. (Autor:in) / Bozec, A. Le (Autor:in)

    Erschienen in:

    AIAA Journal ; 33 , 2 ; 262-265


    Erscheinungsdatum :

    1995


    Format / Umfang :

    4 Seiten, 5 Bilder, 8 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Hypersonic Model Testing in a Shock Tunnel

    Olivier, H. | Online Contents | 1995


    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


    Hypersonic model testing in a shock tunnel

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