Flow visualization of shock-boundary layer interaction
Abstract
Two and three-dimensional shock-boundary layer interaction data were obtained from supersonic wind tunnel tests. These interactions are studied both with and without boundary layer bleed. The data verify computational fluid dynamic codes. Surface static pressure, pitot pressure, flow angularity, and bleed rates, are studied by flow visualization techniques. Surface oil flow using fluorescent dye and laser sheet using water droplets as the scattering material are used for flow visualization.
- Publication:
-
Flow Visualization and Laser Velocimetry for Wind Tunnels
- Pub Date:
- September 1982
- Bibcode:
- 1982fvlv.rept..101H
- Keywords:
-
- Boundary Layer Control;
- Boundary Layer Flow;
- Flow Visualization;
- Shock Loads;
- Shock Tunnels;
- Supersonic Wind Tunnels;
- Bleeding;
- Fluid Dynamics;
- Fluorescence;
- Three Dimensional Boundary Layer;
- Two Dimensional Boundary Layer;
- Instrumentation and Photography