Abstract
The Navier-Stokes equations coupled with species continuity equations which govern the transpiration cooling at hypersonic Mach numbers are solved numerically. The flowfield variables over a flat plate are computed at a flow Mach number of 8.5 with helium and carbon dioxide as coolant gases. The analysis shows that the transpiration cooling has significant effect on the flowfield profiles, reduces the heat transfer and skin friction at the wall and increases the boundary layer thickness. Helium gas is found to be a relatively more effective coolant in transpiration cooling.
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