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Aerothermal Analysis for Configuration Design of Swept Leading Edge Hypersonic Vehicle

Authors
  • KUMAR, S
  • MAHULIKAR, SP
Publication Date
Jan 01, 2016
Source
DSpace at IIT Bombay
Keywords
License
Unknown
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Abstract

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. (C) 2016 American Society of Civil Engineers.

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