Supersonic Laminar Boundary Layer Flow Past a Wavy Wall with Multiple Separation Regions.

摘要

Laminar flow over wave shaped walls with multiple separation bubbles were studied using an implicit finite difference technique. Solutions are presented for Mach 3and 6,Re 100 000and 200 000, Tw/To = 0.45,and 0.675and protuberance height to width ratio from 0to 0.1. Results are compared with empirical correlations and experimental data.