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-7
巻
7
ページ
1 - 12
発行年
1986-12
抄録（英）
A 3D Navier-Stokes program based upon a Beam-Warming diagonalization scheme has been combined with a moving grid system so that it can be applied to the solution around an oscillating wing. The wing is in a pitching motion with an amplitude of 1 degrees and a reduced frequency of 0.428 (based upon the root semichord). The free stream Mach number is 0.9 and the mean angle of attack of the wing is 4 degrees. To the extent that results have been compared with experimental data, the unsteady flow is successfully simulated and the leading edge separations are observed, which is one of the most significant aspects of the experiment. It is demonstrated that the present code is feasible and applicable to the computation of the unsteady viscous compressible flow field around an oscillating wing.
三次元振動翼回りの圧縮粘性流解析の一試み
nalsp0007001.pdf
(695.1KB)
