Supersonic Boundary-Layer Separation and Reattachment-Finite Difference Solutions.
CINCINNATI UNIV OHIO DEPT OF AEROSPACE ENGINEERING
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The boundary-layer equations including the effects of interaction with a supersonic mainstream are solved using an implicit finite difference scheme. The free interaction process is studied extensively and favorable comparisons made with experimental data, expirical correlations, and analytical results. Solutions are presented for shockwave and compression ramp induced separations and reattachments for a Mach 3 mainstream at moderate and cold wall temperatures. Surprisingly little overheating is observed aft of reattachment. Author
- Fluid Mechanics