Experimental Research on Swept Shock Wave/Boundary Layer Interactions
Abstract
This study of swept shock wave interactions with turbulent boundary layers relied entirely on non-intrusive, laser-based optical flow diagnostics. Experiments were carried out to define the flowfield structure of fin-generated interactions over a Mach number range 2.5 to 3.5 using the laser light-screen flow visualization technique. Further experiments resulted in accurate skin friction measurements in fin-generated swept interactions by way of the Laser Interferometer Skin Friction Meter. Techniques were perfected for the assessment of flowfield fluctuation levels using pulsed-laser holographic interferometry. The results of this research have given new insight into the fin-interaction flowfield structure, which involves a supersonic jet produced by shock wave refraction and impinging on the test surface. High skin friction levels were measured in the vicinity of this jet impingement, which compare well with computational predictions carried out by others. Finally, the observed jet impingement structure is shown to be similar to that of leading-edge shock wave impingement on high-speed flight vehicles. Keywords: Experimental design; High- speed flows; Viscous-inviscid interactions; Shock-boundary layer interactions; Supersonic flow; Experiments; Flow visualization; Fluid dynamics; Flow separation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 28, 1988
- Accession Number
- ADA196938
Entities
People
- Gary S. Settles
Organizations
- Pennsylvania State University