In this article, experiments are carried out in a hypersonic shock tunnel with helium as driver gas and air as the test gas to obtain the convective heating rate and surface pressure distribution on a cone model placed at hypersonic speed. Test is performed in hypersonic shock tunnel for a flow Mach number of 6.5 at two different angles of attack, 0° and 5°. The sputtered thin film platinum sensors are used to measure the heat flux on a cone model. The measured heat-transfer rate compares well with theoretically estimated values using reference enthalpy method and computational fluid dynamics (CFD) simulation. The measured surface pressure compares well with CFD.


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    Titel :

    Convective heat-transfer rate and surface pressure distribution over a cone model at hypersonic speeds


    Beteiligte:
    Saiprakash, M (Autor:in) / SenthilKumar, C (Autor:in) / Balu, G (Autor:in) / Shanmugam, V (Autor:in) / Rampratap, Singh Prakash (Autor:in) / sunil, G Kadam (Autor:in)


    Erscheinungsdatum :

    2019-08-01


    Format / Umfang :

    16 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch