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
雑誌名(英)
Special Publication of National Aerospace Laboratory SP-3
巻
3
ページ
43 - 52
発行年
1984-11
抄録（英）
A numerical procedure for solving the flow field generated by a moving body is presented based on a finite difference solution of Navier-Stokes equations. A conservation-law form of the equations in a general time-varying coordinate system is derived from the Cartesian expression by applying the concept of Lie derivatives. Specifically, a moving coordinate expression of the streamfunction-vorticity formulation is derived, and is used for the analysis of the dynamic-stall phenomenon of an oscillating airfoil in incompressible flow. A computation example is given for an NACA 0012 airfoil oscillating in pitch at an amplitude of lO degrees about a mean angle of attack of 15 degrees with a reduced frequency of 0.4pi and a Reynolds number of 2 by 104 based on the chord length and the uniform advance speed of the airfoil.
非定常ナビエ・ストークスの数値シミュレーション
nalsp0003006.pdf
(1.52MB)
