@techreport{oai:jaxa.repo.nii.ac.jp:00043334,
 author = {麻生, 茂 and 二ツ寺, 直樹 and 藤本, 淳 and 林, 正徳 and Aso, Shigeru and Futatsudera, Naoki and Fujimoto, Atsushi and Hayashi, Masanori},
 month = {Nov},
 note = {Separated flows around a wing section at unsteady motion are simulated numerically by a discrete vortex method combined with a panel method. The potential flows around wing sections is expressed by vortex sheets and separated shear layers are expressed by discrete vortices. In the calculation a separation point is determined by solving boundary layer equation. The strength of shed vortex is estimated using local velocity near separation point. Also modification for the estimation of pressure coefficients around wing section are proposed. The estimated pressure distributions show good agreements with experimental results. At first calculations are carried out for a wing section at fixed angle of attack. The results show excellent agreements with experiments. Secondly separated flows around pitching airfoils are simulated. A histerisis of lift of airfoil at dynamic stall is obtained in the calculation. Those results suggest that the present method is quite useful to simulate separated flows around wing section both at steady and unsteady motions., 資料番号: NALSP0010005, レポート番号: NAL SP-10},
 title = {非定常運動をする二次元翼まわりの流れの離散渦法による計算},
 year = {1989}
}