Supersonic Laminar Boundary Layer Flow Past a Wavy Wall with Multiple Separation Regions.
Interim rept. 1 Jan 74-1 Jan 75,
CINCINNATI UNIV OHIO DEPT OF AEROSPACE ENGINEERING
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Laminar flow over wave shaped walls with multiple separation bubbles were studied using an implicit finite difference technique. Solutions are presented for Mach 3 and 6, Re 100 000 and 200 000, TwTo 0.45, and 0.675 and protuberance height to width ratio from 0 to 0.1. Results are compared with empirical correlations and experimental data.
- Fluid Mechanics