Interaction of a conical shock wave with a turbulent boundary layer
Abstract
The paper reports an investigation on the interaction of an incident conical shock wave with a turbulent boundary layer. Although a conical shock theoretically creates a hyperbolic shock trace on the flat plate, the line joining all the experimental interaction origins takes a different form due to varying upstream influence. The existence of strong pressure gradients in the spanwise direction after the shock leads to the boundary-layer twist. A model based on the upstream influence of the shock when combined with McCabe's secondary-flow theory showed separation to occur at an external flow deflection of 11.8 deg. The oil flow measurements however show this to occur at 9.2 deg. This discrepancy is of the same order as that found by McCabe. Detailed data involving Schlieren and shadowgraph photography, surface-flow visualization, and surface-pressure measurements are presented.
- Publication:
-
ICAS, 18th Congress
- Pub Date:
- 1992
- Bibcode:
- 1992icas.conf.1647T
- Keywords:
-
- Cones;
- Interactional Aerodynamics;
- Shock Wave Interaction;
- Turbulent Boundary Layer;
- Flat Plates;
- Flow Visualization;
- Pressure Measurement;
- Separated Flow;
- Fluid Mechanics and Heat Transfer