Coupled Wall Heat Conduction and Coolant Flow Analysis for Liquid Rocket Engines
Author:
Affiliation:
1. Dipartimento di Ingegneria Meccanica e Aerospaziale, University of Rome “La Sapienza”, 00185 Rome, Italy
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.B34533
Reference38 articles.
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3. Heat transfer characteristics of H2/O2-combustion chambers
4. Comparison of high aspect ratio cooling channel designs for a rocket combustion chamber
5. NUMERICAL SOLUTIONS OF FLOWS IN ROCKET ENGINES WITH REGENERATIVE COOLING
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