LE-7A Engine Nozzle Flow Separation Phenomenon and the Possibility of RSS Suppression by the Step Inside the Nozzle
Author:
Affiliation:
1. Japan Aerospace Exploration Agency
2. Osaka University
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2004-4014
Reference7 articles.
1. [1]Hoffman, J. D.,Design ofCompressedTruncated Perfect Nozzle,AIAA85-1172,July1985
2. Restricted Shock Separation in Rocket Nozzles
3. Tomita, T. etal, Sub -scale Nozzle Combustion Tests of the LE-7A Engine for Clarification of Large Side-load (II),AIAA2002-4002,July2002
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