@inproceedings{oai:jaxa.repo.nii.ac.jp:00038058,
 author = {沖, 良篤 and 酒田, 威志 and 内山, 直樹 and 前田, 一郎 and 安藤, 武 and Oki, Yoshiatsu and Sakata, Takeshi and Uchiyama, Naoki and Maeda, Ichiro and Ando, Takeshi},
 book = {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, Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001},
 month = {Jan},
 note = {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., 資料番号: AA0032819022, レポート番号: NAL SP-53},
 pages = {131--136},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {CASPERを用いたONERA M5形態まわりの流れ解析},
 volume = {53},
 year = {2002}
}