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Experimental Investigation of Mechanical Distortions to Hypersonic Boundary Layers

Flaherty, W. and Austin, J. M. (2012) Experimental Investigation of Mechanical Distortions to Hypersonic Boundary Layers. In: 28th International Symposium on Shock Waves. Vol.1. Springer , Berlin, pp. 675-680. ISBN 978-3-642-25687-5.

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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.

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Additional Information:© 2012 Springer. The authors gratefully acknowledge researchers at ISSI, Prof. G.S. Elliott, and the support of AFOSR FA9550-08-1-0172 with Dr. John Schmisseur as Program Manager and AFRL FA8650-10-M-3023 with Dr. Daniel Tejtel as Program Manager.
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Air Force Office of Scientific Research (AFOSR)FA9550-08-1-0172
Air Force Research Laboratory (AFRL)FA8650-10-M-3023
Record Number:CaltechAUTHORS:20140930-094655581
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:50116
Deposited By: Tony Diaz
Deposited On:03 Oct 2014 22:30
Last Modified:03 Oct 2019 07:20

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