Behavior of a turbulent boundary-layer subjected to a shock-induced separation
Abstract
Detailed turbulence measurements have been made in a Mach. 2.9 shockwave/boundary layer interaction produced by a 20 deg compression corner. In this particular flow, the shock wave was strong enough to induce a small separated zone. Dramatic increases in the turbulent normal and shear stresses were observed. It appears that the flow field unsteadiness, manifested by shock-wave oscillation has a significant effect on the turbulence structure. This result is in direct contrast to previous observations for the 8 and 16 deg corner flows. In those experiments, no separation was observed and shock oscillation did not appear to affect the turbulence behavior significantly.
- Publication:
-
AIAA, Aerospace Sciences Meeting
- Pub Date:
- January 1984
- Bibcode:
- 1984aiaa.meetX....M
- Keywords:
-
- Boundary Layer Separation;
- Interactional Aerodynamics;
- Shock Wave Interaction;
- Turbulent Boundary Layer;
- Hot-Wire Anemometers;
- Reynolds Stress;
- Shear Stress;
- Skin Friction;
- Supersonic Wind Tunnels;
- Turbulence Meters;
- Fluid Mechanics and Heat Transfer