Title: STAGNATION POINT HEAT TRANSFER FOR HYPERSONIC FLOW
Abstract: Abstract : A design method is given for obtaining stagnation point heat transfer on a spherical nose in hypersonic flow. The heat transfer equation incorporates real gas effects through use of dissociated air properties and a fitted curve for the stagnation point velocity gradient. Comparison with numerical solutions of the compressible dissociated stagnation point heat transfer indicates agreement within plus or minus 5%. The derived equation for heat transfer is a function only of free stream Mach number, free stream pressure and body nose radius.
Publication Year: 1956
Publication Date: 1956-09-01
Language: en
Type: article
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Cited By Count: 14
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