The Institute of Computational Fluid Dynamics
The Institute of Computational Fluid Dynamics
Institute of Space and Astronautical Science
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-14
巻
14
ページ
141 - 146
発行年
1990-11
抄録（英）
The direct simulation without any turbulence models becomes effective method to study three dimensional unsteady flow fields at high Reynolds numbers. This progress has been made possible by the speed and memory capabilities of present-generation supercomputors and the development of improved computational algorithms and techniques. In this study, we investigated the unsteady shock-boundary interaction in the viscous transonic flow over the ONERA-M6 wing attached to a wall by using a finite difference approximation of the three dimensional Navier-Stokes equations. For this purpose, we used the LU-ADI factorization method with Chakravarthy & Osher type TVD scheme in the explicit term, and got the time-average of the unsteady flow field without using any turbulent eddy viscosity models. As the number of grid points gets large, the CP-curves of the time-average will become close to the results of the experiment.
3次元ナビエ・ストークス方程式を用いた翼まわりの非定常計算
nalsp0014022.pdf
(355.39KB)
