Effects of TSTO Orbiter Configuration on Supersonic Flow Field with Aerodynamic Interactions
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Publisher
Japan Society for Aeronautical and Space Sciences
Link
https://www.jstage.jst.go.jp/article/jjsass/55/646/55_646_509/_pdf
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1. Investigation of Two-Stage-to-Orbit Airbreathing Launch-Vehicle Configurations
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3. 3) Bradley, M., Bowcutt, K., McComb, J., Bartolotta, P. and McNelis, N.: Revolutionary Turbine Accelerator (RTA) Two-Stage-To-Orbit (TSTO) Vehicle Study, AIAA Paper 2002-3902, 2002.
4. 4) Liechty, D. S.: Aeroheating Characteristics for a Two-Stage-To-Orbit Concept during Separation at Mach 6, AIAA Paper 2005-5139, 2005.
5. 5) 棚次亘弘:宇宙輸送システムの展望,日本航空宇宙学会第34期年会講演会講演集, 2003, 2A2, pp. 140–143.
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1. Investigation on Hypersonic Shock Interacting and Boundary-Layer Separating Flowfield around Two-Stage-To-Orbit Vehicle;JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2008
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