STAGNATION POINT HEAT TRANSFER FOR HYPERSONIC FLOW
CONVAIR SCIENTIFIC RESEARCH LAB SAN DIEGO CA
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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.
- Fluid Mechanics