@inproceedings{oai:jaxa.repo.nii.ac.jp:00004409,
 author = {大竹, 智久 and 昼問, 洋樹 and 村松, 旦典 and 本橋, 龍郎 and Otake, Tomohisa and Hiruma, Hiroki and Muramatsu, Akinori and Motohashi, Tatsuo},
 book = {宇宙航空研究開発機構特別資料: 第43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2011論文集, JAXA Special Publication: Proceedings of 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011},
 month = {Mar},
 note = {第43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2011 (2011年7月7日-8日. 早稲田大学国際会議場) 東京, 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8,  2011. Waseda University, International Conference Center), Tokyo Japan, We carried out aerodynamic forces measurements of thin circular arc airfoil in order to clarify influence of camber ratio of the airfoil into aerodynamic characteristics at low Reymolds numbers. The measurements were performed with three cases of chord based Reymolds number of 30,000, 40,000 and 50,000, and two types of wing model which applied 6% and 12% cambered thin circular arc airfoils to cross section of the wing model were used. The results of aerodynamic characteristics of 6% cambered airfoil show a small discontinuity in lift and pitching moment characteristics at all Reynolds numbers, and dependency of Reynolds number changing could not confirm in the aerodynamic characteristics. The aerodynamics of 12% cambered airfoil, in contrast, show remarkable discontinuity and hysteresis which result from abrupt increases in lift characteristics and abrupt decreases in drag and pitching moment characteristics. Magnitude of this discontuity in lift coefficient shows about from 0.4 to 0.5, in drag coefficient shows about 0.05, and pitching moment coefficient shows about from 0.01 to 0.03 with increasing of Reynolds number from 30,000 to 50,000. And, range of angle of attack in which the hysteresis of aerodynamics appeared also changes with Reynolds numbers too. These changes of aerodynamic characteristics might be come from flow field around the airfoil, laminar separation of boundary layer or separation bubble, due to chamber of camber ratio of the airfoil., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065207037, レポート番号: JAXA-SP-11-015},
 pages = {215--218},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {低レイノルズ数領域での異なるキャンバーを持つ薄円弧翼型の空力特性},
 volume = {JAXA-SP-11-015},
 year = {2012}
}