Tohoku University Graduate School of Engineering
Tohoku University Graduate School of Engineering
Tohoku University Graduate School of Engineering
Tohoku University Graduate School of Engineering
Institute of Fluid Science, Tohoku University
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2002論文集
雑誌名(英)
Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002
巻
57
ページ
292 - 297
発行年
2003-03
抄録（英）
In this paper, numerical simulations of aerodynamic response to changes of the deflection angle of a longitudinal control surface of NAL experimental supersonic airplanes are discussed. To treat the change of the deflection angle of the control surface efficiently, an unstructured dynamic mesh method with surface grid movement is used. Computations of a rocket powered experimental supersonic airplane and a jet powered experimental supersonic airplane are performed at the supersonic cruising Mach numbers (M(sub infinity) = 2.0 and 1.7) and a transonic Mach number (M(sub infinity) = 0.95). The computational results are compared and are discussed.
航空機舵角変化に対する空力応答の数値シミュレーション
nalsp0057052.pdf
(3.83MB)
