Gi Oi CO 0 “ 3 to § HYPERSONIC FLOW ALONG TWO INTERSECTING PLANES
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Laminar and Turbulent Aero Heating Predictions over Blunt Body in Hypersonic Flow
In the present work, an engineering method is developed to predict laminar and turbulent heating-rate solutions for blunt reentry spacecraft at hypersonic conditions. The calculation of aerodynamic heating around blunt bodies requires alternative solution of inviscid flow field around the hypersonic bodies. In this paper, the procedure is of an inverse nature, that is, a shock wave is assumed a...
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