Experimental Studies of Quasi-Two-Dimensional and Three-Dimensional Viscous Interaction Regions Induced by Skewed-Shock and Swept-Shock Boundary Layer Interactions

摘要: Abstract : This report describes results from 3 experimental studies designed to examine the aerothermal characteristics of regions three-dimensional shock wave/boundary layer interaction in high-speed flow over non-adiabatic surfaces. The objectives were: (1) explore basic mechanisms associated with 3D boundary separation flows special emphasis on large heat transfer rates and gradients developed reattachment these flows; (2) obtain detailed sets measurements which extend simple semi-empirical prediction methods hypersonic/cooled wall regime where no previous data existed. These were conducted at mach 11 for Reynolds number up 40 million Calspan's 96-Inch Shock Tunnel. In first study we examined effects crossflow scale properties attached separated region induced a flate plate base skewed/oblique shocks. Analysis pressure together visualization demonstrated that, sweep angles 45 deg, had little effect size or regions. second swept-shock was normal flat by generator mounted perpendicular plate. Our corner highly-cooled hypersonic flows, rise induce incipient is significantly larger than predicted methods.