Study on Restricted Shock Separation Phenomena in Rocket Nozzles-Reference-Cited by-同舟云学术

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Study on Restricted Shock Separation Phenomena in Rocket Nozzles

Published:2006-01-09 Issue: Volume: Page:
ISSN:
Container-title:44th AIAA Aerospace Sciences Meeting and Exhibit
language:
Short-container-title:

Author:

Verma Shashi¹,Haidn Oskar²

Affiliation:

1. National Aerospace Laboratories

2. DLR, German Aerospace Research Center

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2006-1431

Reference24 articles.

1. Restricted Shock Separation in Rocket Nozzles

2. Frey,M.andHagemann,G.``FlowSeparationandSide-LoadsinRocketNozzles",AIAA-99-2815

3. 4M.Frey, Behandlung von Stroemungsproblemen in Raketduesen bei Ueberexpansion, Ph.D thesis, Institut fuer Aerodynamikand Gasdynamik,Universitaet Stuttgart,2000,Germany.

Cited by 3 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Numerical investigation of flow separation behavior in an over-expanded annular conical aerospike nozzle;Chinese Journal of Aeronautics;2015-08

2. Shock unsteadiness in a thrust optimized parabolic nozzle;Shock Waves;2008-11-29

3. Flow Separation Studies in a Subscale Truncated Ideal Contour Nozzle;45th AIAA Aerospace Sciences Meeting and Exhibit;2007-01-08

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