並列タイトル等Numerical Analysis for Steady Transonic Flows Past an Airfoil Using AF 2 Scheme
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 approximate factorization scheme has been developed for analyzing transonic flows past an airfoil. In this scheme, upwind differencing is used for introducing artificial viscosity in the supersonic region and central differencing is used in the subsonic region. The resulting simple two- and three-banded matrices are solved by the relaxation proce-dure. This scheme is fully implicit, and in principle can be combined with the solution-adaptive method. In both sub- and super-critical cases, the computed surface pressure distributions for an NACA0012 airfoil are in good agreement with those obtained by other methods.
資料番号: NALSP0003024
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=43166&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