@inproceedings{oai:jaxa.repo.nii.ac.jp:00003644,
 author = {松島, 紀佐 and 小林, 大志 and 金崎, 雅博 and 楠瀬, 一洋 and Matsushima, Kisa and Kobayashi, Taishi and Kanazaki, Masahiro and Kusunose, Kazuhiro},
 book = {宇宙航空研究開発機構特別資料: 第47回流体力学講演会/第33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 47th Fluid Dynamics Conference / the 33rd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 東京, 47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan, To systematically investigate the aerodynamic characteristics of swept-back and forwarded wings with 0, 30, 45 and 60 degree of leading edge angles and different taper ratio, Navier-Stokes simulations for flows about 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 aspect ratio is 2. The simulation and investigation has revealed new knowledge on the relation between swept or forwarded angles and aerodynamic characteristics of a wing in a supersonic flow. Not only a leading edge angle but also a trailing edge angle take important role on aerodynamics of a wing. In addition, transition from detached shockwaves to attached ones at the both edge largely affects the C(sub D)., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630005019, レポート番号: JAXA-SP-15-013},
 pages = {127--132},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {超音速翼の空力特性に関する平面形状パラメトリックス数値シミュレーション},
 volume = {JAXA-SP-15-013},
 year = {2016}
}