@inproceedings{oai:jaxa.repo.nii.ac.jp:00004023,
 author = {山口, 裕太 and 大竹, 智久 and 村松, 旦典 and Yamaguchi, Yuta and Ohtake, Tomohisa and Muramatsu, Akinori},
 book = {宇宙航空研究開発機構特別資料: 第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013論文集, JAXA Special Publication},
 month = {Mar},
 note = {第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013 (2013年7月4日-5日. タワーホール船堀), 東京, 45th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2013 (July 4-5, 2013. Tower Hall Funabori), Tokyo, Japan, The pressure distribution on a NACA0012 airfoil was measured in order to clarify the flow field around the airfoil in the low-Reynolds-number region from 10,000 to 50,000. In the present study, a wind tunnel and a NACA0012 wing model with 70 static pressure ports were used for the measurements. The pressure on the airfoil surface was measured by a micro-pressure sensor. Based on the obtained pressure distributions, we confirmed in detail the behavior of the separation bubble and observed the change of a short bubble into a long bubble. As the angle of attack was increased, the non-linearity of the aerodynamic characteristics was affected by both changes in the separation point and the length of the separation bubble. We confirmed that the behavior of the separation bubble is affected by flow field phenomena that depend on the Reynolds number., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062268023, レポート番号: JAXA-SP-13-011},
 pages = {127--130},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {低Re 数領域におけるNACA0012翼面上の圧力分布},
 volume = {JAXA-SP-13-011},
 year = {2014}
}