Numerical study of high-area-ratio H2/O2 rocket nozzles
Author:
Affiliation:
1. NASA, Lewis Research Center; Sverdrup Technology, Inc., Cleveland, OH
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1991-2434
Reference21 articles.
1. Low thrust cryogenic engine technology
2. Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle
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