@inproceedings{oai:jaxa.repo.nii.ac.jp:00003843,
 author = {竹内, 和也 and 直井, 健悟 and 松島, 紀佐 and Takeuchi, Kazuya and Naoi, Kengo and Matsushima, Kisa},
 book = {宇宙航空研究開発機構特別資料: 第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県, 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan, To systematically investigate the aerodynamics of wings with 30, 45 and 60 degree swept-back angle, and different taper ratio, Navier-Stokes simulations for flows over a wing have been conducted. The Mach numbers of the flows are from 0.8 to 2.8. The planforms of wings are in various shapes whose half span aspect ratio is 2. The simulation and investigation has revealed new knowledge on the relation between swept-back angles and aerodynamic characteristics of a wing in a supersonic flow. Not only the swept-back angle of a leading edge but also that of a trailing edge take important role on aerodynamics of a wing., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530023008, レポート番号: JAXA-SP-14-010},
 pages = {41--46},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {超音速流における主翼前縁および後縁の後退角の空力特性への影響のCFD解析},
 volume = {JAXA-SP-14-010},
 year = {2015}
}