Chiba University Faculty of Engineering
Chiba University Graduate School
Chiba University Graduate School
Kisarazu National College of Technology
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集
雑誌名(英)
JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005
巻
JAXA-SP-05-017
ページ
100 - 105
発行年
2006-02-28
抄録（英）
Three-dimensional flow around the slender body, such as aircraft body or rocket cause drastic variation of flow with high angle of attack and have considerable influence on the aerodynamic characteristics. Here the projectile in the inertia flight after thrust of the body has been stopped is studied numerically by a finite difference scheme. This study aims at clarifying the mechanism of free flight, which is affected by the pitching and gravity on body. The initial condition is the flow at steady 'flight' which develops just after the power of engine is shutdown and the vehicle starts free flight with inertia. It has been predicted that in the lower Reynolds number less than 100,000 the flow is symmetric. Therefore, in this numerical study, the flow over a paraboloidal-nose cylinder at pitching rotation in 'free flight' is considered for Reynolds numbers lower than 100,000. The coordinate system fixed on the body, which yields additional terms in Navier Stokes equation. The dual-time pseudo compressibility code is applied for incompressible case, instead PC-TVD scheme for Mach = 0.3 case. The Newton's 2nd law is used with the balance of aerodynamic force and gravity together with angular momentum equation. The aerodynamic coefficients Cd, Cl, Cm are discussed, as well as the trajectory of body.
慣性飛行時の軸対象物体の流体解析
49212016.pdf
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