Supersonic laminar boundary layer flow past a wavy wall with multiple separation regions
Abstract
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, various Reynolds numbers, Tw/To = 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.
- Publication:
-
Interim Report
- Pub Date:
- February 1974
- Bibcode:
- 1974cinn.rept.....P
- Keywords:
-
- Boundary Layer Flow;
- Laminar Boundary Layer;
- Separated Flow;
- Supersonic Boundary Layers;
- Boundary Layer Separation;
- Finite Difference Theory;
- Mathematical Models;
- Numerical Analysis;
- Stagnation Temperature;
- Fluid Mechanics and Heat Transfer