Supersonic Film Cooling Simulation with a DG Method
Author:
Affiliation:
1. China Academy of Aerospace Aerodynamics
2. Beijing Power Machinery Research Institute, Science and Technology on Scramjet Laboratory
Publisher
American Institute of Aeronautics and Astronautics
Link
https://arc.aiaa.org/doi/pdf/10.2514/6.2017-2248
Reference16 articles.
1. Influence of injectant Mach number and temperature on supersonic film cooling
2. 2D.G.BogardandK.A.Thole,Gasturbinefilmcooling,JournalofPropulsionandPower,December2005.
3. 3S. S.,Papell, and A.M., Trout, Experimental investigation ofair filmcooling applied to an adiabatic wall by meansofan axiallydischargingslot, NASATND-9,1959.
4. 4M. L., Hunt, K.A., Juhany and J. M. Sivo, Supersonic film cooling effectiveness using air and helium for a rangeofinjectant temperatureand Machnumbers, AIAA91-1416,1991.
5. 5Olsen G.C., Nowak R.J., Holden M.S., Baker N.R., Experimental results for film cooling in 2-D supersonic flowincludingcoolantdeliverypressure, geometry, and incident shockeffects, AIAA90-0605,1990.
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