Coupled Heat Transfer Analysis in Regeneratively Cooled Thrust Chambers
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Publisher
American Institute of Aeronautics and Astronautics
Reference29 articles.
1. 1Niino, M., Kumakawa, A., Yatsuyanagi, N., and A.Suzuki, "Heat Trasfer Characteristics of Liquid Hydrogen as a Coolant for the L02/LH2 Rocket Thrust Chamber with the Channel Wall Construction," AIAA Paper 1982-1107, June 1982, 18th SAE/ASME Joint Propulsion Conference.
2. 2Frohlich, A., Popp, M., Schmidt, G., and Thelemann, D. "Heat Transfer Characteristics of H2/O2: Combustion Chambers," AIAA Paper 1993-1826, July 1993, 29th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.
3. 3Wadel, M. F. "Comparison of High Aspect Ratio Cooling Channel Designs for a Rocket Combustion Chamber," AIAA Paper 1997-2913, July 1997, 33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference.
4. NUMERICAL SOLUTIONS OF FLOWS IN ROCKET ENGINES WITH REGENERATIVE COOLING
5. 5Naraghi, M. H., Dunn, S., and Coats, D. "A Model for Design and Analysis of Regeneratively Cooled Rocket Engines," AIAA Paper 2004-3852, July 2004, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.
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