@inproceedings{oai:jaxa.repo.nii.ac.jp:00004265,
 author = {佐藤, 雅幸 and 稲葉, 亮司 and 西田, 浩之 and 野々村, 拓 and 藤井, 孝蔵 and Sato, Masayuki and Inaba, Ryoji and Nishida, Hiroyuki and Nonomura, Taku and Fujii, Kozo},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012},
 month = {Mar},
 note = {第44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2012 (2012年7月5日-6日. 富山国際会議場大手町フォーラム), 富山市, 富山県, 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan, We have analyzed the asymmetric separation flow over a slender body at high angle of attack by numerical simulation aiming a control of the asymmetric vortices using a dielectric barrier discharge (DBD) plasma actuator. Reynolds Averaged Navier Stokes/Large-Eddy Simulation hybrid method (RANS/LES) is adopted with high-order compact spatial difference scheme. First, the characteristics of the asymmetric separation flow were explained for various angles of attack. When the angle of attack becomes higher, the asymmetricity of the flow field becomes stronger. The side force has nonlinearity in the relation with the angle of attack. We estimated the circumferential flow separation point using circumferential pressure distribution. Separation point is changed with the angle of attack, axial position and body side (right or left hand side). Next, numerical simulations of the flow field over the slender body with the plasma actuator actuation were con""" ducted. Plasma actuators are located circumferential position of plus or minus 80degs, plus or minus 100degs or plus or minus 120degs. We investigated the influence of the positional relation between the flow separation point and the actuator location on the side force control effect. As a result, the flow control effect can be improved by installing the actuator near to the flow separation point. The flow can be controlled by the plasma actuator located not only before the flow separation point but also after that; this result indicates the flow control is due to the Coanda effect., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0061958025, レポート番号: JAXA-SP-12-010},
 pages = {151--156},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {DBDプラズマアクチュエータを用いた大迎角細長物体の非対称剥離渦制御における周方向駆動位置の影響の数値解析},
 volume = {JAXA-SP-12-010},
 year = {2013}
}