@inproceedings{oai:jaxa.repo.nii.ac.jp:00003636,
 author = {橋爪, 俊樹 and 大竹, 智久 and 村松, 旦典 and Hashizume, Toshiki and Ohtake, Tomohisa and Muramatsu, Akinori},
 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, We calculated flow around a NACA0012 airfoil at angle of attack 7 degrees in Re=30,000 by using Open FORM to investigate a separation bubble on the upper surface side. In Re=30,000, the laminar separation was formed and the flow on the leading edge was affected by a separation bubble. The pressure distribution from the leading edge to 30% chord was constant. The flow on 50% chord reattached to a wing surface. In lower-Reynolds-number (Re=20,000), the pressure distribution on the upper surface was approximately constant from 20% chord to 80% chord. The flow on the trailing edge changed three-dimensionally. The flow field in higher-Reynolds-number (Re=40,000) was similar to the flow field in Re=30,000. We confirmed a difference in the flow on the upper surface by changing of the Reynolds number., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630005011, レポート番号: JAXA-SP-15-013},
 pages = {79--84},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {RE=30,000におけるNACA0012翼まわりの流れ場の数値計算},
 volume = {JAXA-SP-15-013},
 year = {2016}
}