並列タイトル等Numerical Calculations of Separating Flows Around Oscillating Airfoil
タイトル（掲載誌）航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-16
一般注記Dynamic stall phenomena have been investigated numerically by solving incompressible Navier-Stokes equations by a third order upwind scheme in order to reveal the flow structure and mechanism of dynamic stall. At first, separated flows around a wing section at fixed attack angle are calculated and the results show excellent agreements with experiments which are conducted by the present authors. Separated flows around oscillating airfoil in pitch are calculated by using moving mesh system. The flow conditions are selected from our experiments. The calculated separated region is small in pitching-up proces ; and it becomes large in a pitching-down process. Quite different characteristics of flow patterns between in a pitching-up and pitching-down processes are obtained. The hysteresis curves of CL and CM in dynamic stall are also simulated in the present calculations.
資料番号: NALSP0016011
レポート番号: NAL SP-16
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43507&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ