@inproceedings{oai:jaxa.repo.nii.ac.jp:00006639,
 author = {木暮, 巧 and 伊藤, 靖 and 中橋, 和博 and 松島, 紀佐 and Kogure, Takumi and Ito, Yasushi and Nakahashi, Kazuhiro and Matsushima, Kisa},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003},
 month = {Mar},
 note = {Promoted by increasing demand for higher efficiency of commercial airplane, the importance of the transonic CFD is increasing. In order to verify the accuracy of CFD for transonic flows, 2nd AIAA drag prediction workshop was held in June 2003, for DLR-F6 models. This paper is to discuss results for the workshop. The computations were performed with two one-equation turbulence models: Goldberg-Ramakrishnan and Spalart-Allmaras, to verify the unstructured-mesh Navier-Stokes solver: TAS-code. From these computations, it was found that there was a remarkable difference in drag between the present computations and experiments. For example, in the case of DLR-F6 wing-body configuration with nacelle and pylon fling at M = 0.75 and AOA = 1, computation using medium size mesh: it had 5.6 million nodes, resulted in C(sub L) = 0.54 and C(sub D) = 0.0424 while C(sub L) = 0.5 and C(sub D) = 0.0338 by wind tunnel experiments. To improve the present unstructured-mesh Navier-Stokes solver, some more detailed investigations about the dependencies on numerical mesh and turbulence model was done, and tried other one-equation turbulence model: modified Spalart-Allmaras model. However, no remarkable improvements were achieved. Further investigations are required to identify the cause of the inaccuracy of the drag prediction. Currently, higher-order reconstructions for numerical flux and the reduction method for the grid dependency are under investigation., 資料番号: AA0047427038, レポート番号: JAXA-SP-03-002},
 pages = {214--219},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {非構造格子N-Sソルバーによる航空機遷音速計算の精度検証},
 volume = {JAXA-SP-03-002},
 year = {2004}
}