An experimental and numerical study of hypersonic turbulent boundary layer flows
Author:
Affiliation:
1. Imperial College of Science, Technology and Medicine, London, United Kingdom
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1997-2290
Reference30 articles.
1. Supersonic Turbulent Boundary Layer in Adverse Pressure Gradient. Part I: The Experiment
2. The effect of mean compression or dilatation on the turbulence structure of supersonic boundary layers
3. The response of a compressible turbulent boundary layer to short regions of concave surface curvature
4. A supersonic turbulent boundary layer in an adverse pressure gradient
5. Effect of short regions of surface curvature on compressible turbulent boundary layers
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1. Temperature Measurements in a Hypersonic Boundary Layer Using Planar Laser-Induced Fluorescence;AIAA Journal;2000-09
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