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• W2465347710 abstract "AbstractThe 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 aerot..." @default.
• W2465347710 created "2016-07-22" @default.
• W2465347710 creator A5064876242 @default.
• W2465347710 creator A5084664182 @default.
• W2465347710 date "2016-11-01" @default.
• W2465347710 modified "2023-09-24" @default.
• W2465347710 title "Aerothermal Analysis for Configuration Design of Swept Leading Edge Hypersonic Vehicle" @default.
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• W2465347710 doi "https://doi.org/10.1061/(asce)as.1943-5525.0000651" @default.
• W2465347710 hasPublicationYear "2016" @default.
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