Abstract

Prediction of wall pressure and heat flux due to aerodynamic heating in external flows is critical in the design of hypersonic vehicles as they are exposed to high aero-thermal loads. This paper examines and estimates the wall heat flux and pressure over a diamond airfoil in a supersonic flow (Mach = 5) for different angles of attack. We have obtained the wall heat flux results using the analytical correlations in order to justify the numerical results. Computed wall heat values agree with those given by correlations available in the literature. We find that the lower (high pressure) side of the airfoil experiences heat fluxes around 5 times the zero angles of attack values.

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