The aerothermal analysis of a hypersonic vehicle is of fundamental interest for designing its configuration. The convection coefficients and wall temperatures due to aerodynamic heating to critical surfaces of a hypersonic vehicle are obtained computationally. Convective heat flux to the swept-back leading edge (SBLE) surface is obtained by splitting the velocity vector along and perpendicular to the surface, and thereby appropriately using the two-dimensional (2D) stagnation region and flat plate heat fluxes together. The main purpose of this work is to propose aerothermal concepts for configuration design of a swept leading edge hypersonic vehicle. Results obtained from these computational analyses reveal the existence of temperature and drag-minimized sweepback, temperature and heat flux-variations-minimized sweepback, and most importantly, the thermally benign sharp SBLE effect. There exists an optimum sweepback angle that is different from drag and temperature-minimized sweepback. These aerothermal concepts are also potential candidates for consideration in the configuration design of hypersonic vehicles.


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    Title :

    Aerothermal Analysis for Configuration Design of Swept Leading Edge Hypersonic Vehicle


    Contributors:

    Published in:

    Publication date :

    2016-07-11




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown






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