Experimental Investigation of Mechanical Distortions to Hypersonic Boundary Layers

  • W. Flaherty
  • J. M. Austin
Conference paper


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 % [1]. Goertler vortices were found to cause fluctuations in heat transfer of 20-30% in a Mach 7.1 flow over a concave compression ramp [2]. 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 [3]. 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.


Vortex Structure Vortex Breakdown Supersonic Boundary Layer Pressure Sensitive Paint Hypersonic Boundary Layer 
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Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • W. Flaherty
    • 1
  • J. M. Austin
    • 1
  1. 1.Department of Aerospace EngineeringUniversity of IllinoisUrbanaUSA

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