The effect of an air‐spike in hypersonic flow is considered in the paper. The similarity laws of shape dependence and shock wave parameters, as a function of the strength of the heat source and characteristics of incident flow, are given. The numerical modeling is performed, based on the Euler gasdynamic equations for conditions identical to those tested in the RPI Hypersonic Shock Tunnel (M=10.1), where heat deposition took place with and without a blunt body in the stream. Good agreement between the individual shock wave shapes given by asymptotic theory, numerical modeling, and experiment is demonstrated. Results of numerical modeling show significant drag reduction and confirm the energy efficiency of the air‐spike concept.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Drag and Total Power Reduction for Artificial Heat Input in Front of Hypersonic Blunt Bodies


    Contributors:

    Conference:

    BEAMED ENERGY PROPULSION: Third International Symposium on Beamed Energy Propulsion ; 2004 ; Troy, New York (USA)


    Published in:

    AIP Conference Proceedings ; 766 , 1 ; 485-498


    Publication date :

    2005-04-27


    Size :

    14 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Drag and Total Power Reduction for Artificial Heat Input in Front of Hypersonic Blunt Bodies

    Myrabo, L. N. / Raizer, Y. P. / Shneider, M. N. | British Library Conference Proceedings | 2005


    Drag Reduction and Heat Transfer Mitigation Techniques for Blunt Bodies in Hypersonic Flight

    Riggins, David / Taylor, Trent / Barnett, Thomas | AIAA | 2003


    Numerical Study of Novel Drag Reduction Techniques for Hypersonic Blunt Bodies

    Marley, Christopher D. / Riggins, David W. | AIAA | 2011