Experimental studies of supersonic film cooling with shock wave interaction
Author:
Affiliation:
1. National Aerospace Lab., Kakuda, Japan
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1996-2663
Reference9 articles.
1. Effect of film cooling/regenerative cooling on scramjet engine performances
2. Turbulent Boundary-Layer Shock Interaction with and without Injection
3. Experimental studies of shock wave/wall jet interaction in hypersonic flow
4. 4Olsen, G. C., Nowak, R. J., Holden, M. S., and Baker, N. R. "Experimental Results for Film Cooling in 2-D Supersonic Flow Including Coolant Delivery Pressure, Geometry, and Incident Shock Effects," AIAA paper 90-0605, Jan.1990.
5. Flowfield measurements in supersonic film cooling including the effect of shock-wave interaction
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1. Visualization of Mach 3.0/3.8 Flow around Blunt Cone with Supersonic Film Cooling;Applied Mechanics and Materials;2013-10
2. Influence of Shock Waves on Supersonic Film Cooling;Journal of Spacecraft and Rockets;2009-01
3. View Factors for Rectangular Enclosures Using the Direct Discrete-Ordinates Method;Journal of Thermophysics and Heat Transfer;1997-10
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