computational fluid dynamics, hypersonic wind tunnel, shock wave interaction, hypersonic flow, aerodynamic heating, Navier-Stokes equation, two body problem, numerical analysis
その他のタイトル（英）
CFD analysis and wind tunnel experiments of hypersonic shock-shock interaction heating for TSTO two body problem and proposal of new CFD workshop problem
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2001論文集
雑誌名(英)
Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001
巻
53
ページ
35 - 41
発行年
2002-01
抄録（英）
Hypersonic aerodynamic interactions for two hemisphere-cylinders have been investigated numerically and experimentally for future TSTO space transport problems. Two hemisphere models with a diameter of 3 cm and 6 cm are placed parallel or with the inclined angle from 13 to 16 deg and complicated shock-shock interactions which generates severe heating on the body surface are studied by using NAL Mach 10 Hypersonic Wind Tunnel and CFD analysis. The purpose of the present study is to understand the complicated flow phenomena and to predict the related severe peak heating rate in the interaction area. Finally, proposals of CFD workshop are made for these two body shock/shock interaction problems. These works contribute to future TSTO aerodynamic design problems in both cruising and separation stages.
TSTO2体問題衝撃波干渉加熱と検証課題の提案
nalsp0053007.pdf
(2.57MB)
