@inproceedings{oai:jaxa.repo.nii.ac.jp:00014352,
 author = {小嶋, 亮次 and 李, 東輝 and 野々村, 拓 and 大山, 聖 and 藤井, 孝蔵 and Kojima, Ryoji and Lee, Dong-Hwi and Nonomura, Taku and Oyama, Akira and Fujii, Kozo},
 book = {宇宙航行の力学シンポジウム: 平成22年度, Symposium on Flight Mechanics and Astrodynamics: 2010},
 month = {Aug},
 note = {宇宙航行の力学シンポジウム 平成22年度 (2010年12月16-17日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Symposium on Flight Mechanics and Astrodynamics,  2010 (December 16-17, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The flow fields around NACA0002 and its aerodynamic characteristics obtained with Three-Dimensional Navier Stokes solver with implicit Large-Eddy Silmuation (3D-iLES) and Two Dimensional Farve-averaged_Navier-Stokes solver without turbulence model (2D-Lam.) are compared at Reynolds number of 23,000. Around this Reynolds number, the flow of upper airfoil separates from a leading edge, transits and reattaches to create a laminar separation bubble at higher angle of attack than 3 degree. The results show that 2D-Lam. evaluates reattachment point a little earlier than 3D-iLES. Plesent results, however, show that time-averaged flows from 2D-Lam. duplicate span-and-time-averaged those from 3D-iLES at lower angle of attack than 9 degree where a complete separation from leading edge occurs. Moreover, aerodynamic characteriscs obtained by 2D-Lam. have good agreement with those from 3D-iLES without completely separated flows., 資料番号: AA0065106033},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {低レイノルズ数における薄翼の空力性能評価手法に関する研究},
 year = {2011}
}