Circumferential Behavior of Tangential Film Cooling and Injector Wall Compatibility in a High Pressure LOX/GH2 Subscale Combustion Chamber
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American Institute of Aeronautics and Astronautics
Reference21 articles.
1. 2Rachuk, D. V., Gontcharov, N., and Matrinyenko, D. Y. “Evolution of the RD-0120 for Future Launch Systems,” 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Lake Buena Vista, CA, July 1st-3rd 1996, AIAA96-3004.
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1. Modelling and Simulation of Film Cooling in Liquid Rocket Engine Propulsion Systems;48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2012-07-30
2. Numerical Study of Heat Transfer in Film Cooled Thrust Chambers;48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2012-07-30
3. Film Cooling in a High-Pressure Subscale Combustion Chamber;Journal of Propulsion and Power;2010-05
4. Film Cooling of Accelerated Flow in a Subscale Combustion Chamber;Journal of Propulsion and Power;2009-03
5. Influence Parameters on Film Cooling Effectiveness in a High Pressure Subscale Combustion Chamber;47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition;2009-01-05
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