並列タイトル等Numerical Solution of Viscous Compressible Flows Past an Airfoil Using Unconditionally Stable Explicit Method
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-3
一般注記An unconditionally stable explicit method has been applied to compute compressible laminar flows past an NACA0012 airfoil. The method is based on a combination of central differencing for spatial derivatives with a rational Runge-Kutta time integration scheme. Both transonic (M
An unconditionally stable explicit method has been applied to compute compressible laminar flows past an NACA0012 airfoil. The method is based on a combination of central differencing for spatial derivatives with a rational Runge-Kutta time integration scheme. Both transonic (M = 0.8) and supersonic (M = 2.0) flow cases have been calculated for various Reynolds numbers. Physically plausible results are obtained for each case within practically feasible CPU time.
資料番号: NALSP0003025
レポート番号: NAL SP-3
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43167&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