Sub Scale Nozzle Combustion Tests of the LE-7A Engine for Clarification of Large Side-loads (I)-- Formation of RSS Structure Due to Combustion Condition-Reference-Cited by-同舟云学术

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Sub Scale Nozzle Combustion Tests of the LE-7A Engine for Clarification of Large Side-loads (I)-- Formation of RSS Structure Due to Combustion Condition

Published:2002-07-07 Issue: Volume: Page:
ISSN:
Container-title:38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
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Author:

Tomita Takeo,Sakamoto Hiroshi,Takahashi Mamoru,Sasaki Masaki,Tamura Hiroshi,Tsuboi Masanori

Publisher

American Institute of Aeronautics and Astronautics

Reference8 articles.

1. Restricted Shock Separation in Rocket Nozzles

2. Watanabe, Y. "LE-7A Engine Nozzle Separation Phenomenon During the Transient Process," ISTS 2002-a-24, 2002

Cited by 6 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. Influence study of flow separation on the nozzle vibration response;Propulsion and Power Research;2016-06

2. Experimental evaluation of side-loads in LE-7A prototype engine nozzle;Shock Waves;2009-03-26

3. Next Booster Engine LE-X in Japan;43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2007-07-08

4. Numerical Study of Restricted Shock Separation in a Compressed Truncated Perfect Nozzle;AIAA Journal;2006-03

5. Unsteady Side Loads in a Thrust-Optimized Contour Nozzle at Hysteresis Regime;AIAA Journal;2004-09

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