Investigation on Hypersonic Shock Interacting and Boundary-Layer Separating Flowfield around Two-Stage-To-Orbit Vehicle

Author:

KITAMURA Keiichi,OZAWA Hiroshi,HANAI Katsuhisa,MORI Koichi,NAKAMURA Yoshiaki

Publisher

Japan Society for Aeronautical and Space Sciences

Reference40 articles.

1. 1) NASA: Constellation Program: Orion Crew Vehicle, http://www.nasa.gov/mission_pages/constellation/orion/index.html, 2007/02/18.

2. 3) 宇宙航空研究開発機構:JAXA2025/長期ビジョン,http:// www.jaxa.jp/about/2025/index_j.html, 2005/04/06.

3. 4) Dulepov, N. P., Lanshin, A. I., Sokolova, O. V. and Tjurikov, E. V.: Propulsion Systems for TSTO Airplane-Accelerators of Different Types, AIAA Paper 2001-1914, 2001.

4. 5) Liechty, D. S.: Aeroheating Characteristics for a Two-Stage-To-Orbit Concept During Separation at Mach 6, AIAA Paper 2005-5139, 2005.

Cited by 2 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. Three-Dimensional Hypersonic Aeroheating Computations Associated with Cross-Flow Jet Interactions;AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2020

2. Experimental Analysis of TSTO Aerodynamic Interactions Based on Oil Flow Patterns at Hypersonic Speed;47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition;2009-01-05

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