Boundary-Layer Separation Due to Combustion-Induced Pressure Rise in a Supersonic Flow
Author:
Affiliation:
1. University of Queensland, Brisbane, Queensland 4072, Australia
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.40868
Reference16 articles.
1. Comparison of Shock-Induced Two- and Three- Dimensional Incipient Turbulent Seperation
2. Ram Accelerators: Outstanding Issues and New Directions
3. Design of Three-Dimensional Hypersonic Inlets with Rectangular-to-Elliptical Shape Transition
4. Study of Separating Compressible Turbulent Boundary-Layers
5. Structure of Flow over a Hypersonic Inlet with Side Compression Wedges
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