Shock-induced three-dimensional separation of an axisymmetric hypersonic turbulent boundary layer
Author:
Affiliation:
1. Queensland, Univ., Brisbane, Australia
2. Imperial College of Science, Technology and Medicine, London, United Kingdom
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2000-2226
Reference14 articles.
1. Some properties of boundary layer flow during the transition from laminar to turbulent motion
2. Structure of a Supersonic Three-Dimensional Cylinder/Offset-Flare Turbulent Interaction
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2. Shock wave Boundary Layer Interaction (SWBLI) in hypersonic flow over a Blunt body double wedge configuration;Journal of Physics: Conference Series;2019-08-01
3. Experimental Investigation of Axisymmetric Transitional Shock Wave Boundary Layer Interactions at Mach 5;29th International Symposium on Shock Waves 2;2015
4. Experiments on transitional shock wave--boundary layer interactions at Mach 5;Experiments in Fluids;2013-09-28
5. Experimental investigation of axisymmetric hypersonic shock-wave/turbulent-boundary-layer interactions;Journal of Fluid Mechanics;2013-01-02
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