Japan Defense Agency Technical Research and Development Institute
Japan Defense Agency Technical Research and Development Institute
Mitsubishi Heavy Industries Ltd.
Mitsubishi Heavy Industries Ltd.
Ryoyu Keisan Co. Ltd.
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2001論文集
雑誌名(英)
Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001
巻
53
ページ
131 - 136
発行年
2002-01
抄録（英）
The CASPER (Computational Aerodynamics System for Performance Evaluation and Research) was developed at TRDI-JDA (Technical Research and Development Institute of Japan Defense Agency) in 1998. An unstructured grid technique has a good flexibility for a complex geometry, and already its usefulness has been demonstrated for full aircraft computations. In the three-dimensional, high-Reynolds number viscous flow, the very fine and stretched grids are required to resolve accuately thin boundary layers developed along the body surface. In this paper, RANS (Reynolds-Averaged Navier-Stokes) computations are carried out in transonic and high Reynolds number flows around an ONERA Model M5 configuration by using a Spalart-Allmaras one-equation turbulence model on a hybrid unstructured grid system. With respect to pressure distributions, CL-a, CL-CD and CM-CL curves, and boundary layer transition lines, the present computed results are quantitatively compared with other computed results and wind-tunnel testing data. Especially, the drag prediction is considerately improved by the flowing strategies: (1) High resolution of surface grids around each leading edge; (2) Extension of NUM (Normalized Unstructured Mesh) method; and (3) Modification of transition parameters such as C13 and C14 in the Spalart-Allmaras one-equation model.
CASPERを用いたONERA M5形態まわりの流れ解析
nalsp0053022.pdf
(2.22MB)
