Turbulent boundary layer separation on a curved wall with normal compression shock
Abstract
A numerical three-layer model is presented for analyzing the interaction between a turbulent boundary layer on a curved airfoil and a weak normal compression-shock wave in transonic flow for different Reynolds numbers; the flow is assumed to be inviscid and compressible. An explicit solution is obtained which can be used to calculate wall shear stress; the behavior of pressure disturbances within the boundary layer is investigated for different wall conditions. Conditions under which boundary layer separation occurs are investigated.
- Publication:
-
Gesellschaft angewandte Mathematik und Mechanik Jahrestagung Goettingen West Germany Zeitschrift Flugwissenschaften
- Pub Date:
- July 1978
- Bibcode:
- 1978GMMWJ..58..249B
- Keywords:
-
- Airfoils;
- Boundary Layer Separation;
- Normal Shock Waves;
- Turbulent Boundary Layer;
- Wall Flow;
- Compressible Flow;
- Inviscid Flow;
- Shock Wave Propagation;
- Transonic Flow;
- Fluid Mechanics and Heat Transfer