Experimental Investigation of Mechanical Distortions to Hypersonic Boundary Layers
Destabilization of the boundary layer in hypervelocity flight can significantly increase the surface heat flux. For example, a stretch of concave surface curvature has been found to increase the skin friction by 125 % . Goertler vortices were found to cause fluctuations in heat transfer of 20-30% in a Mach 7.1 flow over a concave compression ramp . Ekoto et al. carried out an extensive study of global (adverse, favorable, and combined pressure gradients) and local (due to surface roughness) distortions in a turbulent hypersonic boundary layer . Building on these works, we experimentally investigate the structure and breakdown of imposed vortex structures in a laminar hypervelocity boundary layer over a flat plate, and linear and curved compression surfaces.
KeywordsVortex Structure Vortex Breakdown Supersonic Boundary Layer Pressure Sensitive Paint Hypersonic Boundary Layer
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- 6.Flaherty, W., Austin, J.M.: Application of Fast Pressure Sensitive Paint in Hypervelocity Flow. In: 49th AIAA Aerospace Sciences Meeting, AIAA-2011-848 (2011)Google Scholar