Experimental Investigation of Mechanical Distortions to Hypersonic Boundary Layers

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

Introduction

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.

Keywords

Vortex Structure Vortex Breakdown Supersonic Boundary Layer Pressure Sensitive Paint Hypersonic Boundary Layer 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

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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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