Irregular Phenomena of Shock Reflection Transition in a Conventional Supersonic Wind Tunnel
Author:
Affiliation:
1. National Aerospace Laboratory of Japan, Tokyo 182-8522, Japan
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/2.2065
Reference29 articles.
1. Analysis of losses in supersonic mixing and reacting flows
2. Comparison of wall mixing concepts for scramjet combustors
3. Study of a Supersonic Combustor Employing Swept Ramp Fuel Injectors
4. Combustor data bases for hypersonic airbreathing propulsion systems
5. Numerical and experimental investigation of hydrogen combustion in a Mach 2 airflow with an unswept ramp fuel injector
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1. Some More on Transition Between Regular and Mach Reflection of Shock Waves in Steady Flow (Invited);38th Fluid Dynamics Conference and Exhibit;2008-06-15
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