A space vehicle in atmosphere travels mostly at supersonic speed and generates a very strong bow shock wave around its blunt nose. This causes a large high-pressure area at the front nose surface accompanied with high temperature. It suggests high-pressure drag and high risk of heat shield failure. Oblique shock and conical separated flow zone generated by a forward disk-tip spike significantly reduce the drag by reducing the high-pressure area on the blunt nose. In the present work, aerodynamics of the high-speed spike-tipped blunt nose is investigated here numerically with Mach number up to 4.5. It is highlighted here that there exists an optimal combination of spike length and disk-tip diameter giving rise to minimal drag at supersonic speed. The reason for drag reduction is analyzed in detail.


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    Titel :

    Drag Reduction and Aerodynamic Shape Optimization for Spike-Tipped Supersonic Blunt Nose


    Beteiligte:
    Xue, Yuan (Autor:in) / Wang, Liang (Autor:in) / Fu, Song (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2018-03-26


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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