@inproceedings{oai:jaxa.repo.nii.ac.jp:00047341,
 author = {菅谷, 圭祐 and 今村, 太郎 and SUGAYA, Keisuke and IMAMURA, Taro},
 book = {宇宙航空研究開発機構特別資料: 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2020オンライン論文集, JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online},
 month = {Feb},
 note = {流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議), Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), Cartesian grid method and Immersed Boundary method is suitable for aerodynamic design of aircraft because of its fast, automatic and robust grid generation. In this study, we propose a modification of the Immersed Boundary method for improving the accuracy of pressure drag prediction. The key idea of the modified method is to choose the reference points which are used for enforcing boundary conditions according to the primitive variables. The Image Point is used to determine the velocity boundary conditions, and the cell which is closest to the wall is used for calculating the pressure boundary condition. The capability of the modified method is evaluated through the two- and three-dimensional transonic flow simulations. The RANS simulation around NASA Common Research Model shows that the drag coefficient calculated by the modified method is closer to that of the body fitted grid than the original method. Therefore, the accuracy of drag prediction by using the modified method is better than the original method., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030013020, レポート番号: JAXA-SP-20-008},
 pages = {149--155},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {NASA-CRMの抵抗予測精度の向上に向けた埋め込み境界法の改善},
 volume = {JAXA-SP-20-008},
 year = {2021}
}