Pressure-Interaction Methods for Axisymmetric, Hypersonic, Laminar, Unseparated Flows.
Rept. for Jan 69-Nov 70,
AEROSPACE CORP EL SEGUNDO CALIF LAB OPERATIONS
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Local-similarity methods suitable for flows with axisymmetric hypersonic viscous interaction are provided for three limit flows. The first method is for flow with a strong shock wave over sharp or hollow cylinders this compares with an existing solution for cones and 34 power-law bodies. The second is a new local solution for general, very thin bodies it becomes exact when the pressure ratio approaches 1 or is unbounded. The third, for power-law bodies with linearized inviscid flow, becomes exact when the ratio of boundary-layer to body thickness vanishes or is unbounded. Together with classical results for very thin boundary layers, these diverse methods provide interpolated estimates of pressure and heat transfer rate on a very slender cone-cylinder in hypersonic flow that compare well with original experimental data. Author
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