並列タイトル等A Finite Volume, Upwind Scheme with Global Conservation for Incompressible Flows
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-14
一般注記A finite-volume, conservative upwind scheme has been developed, based on the flux-difference splitting method. Pseudo-compressibility is introduced in the continuity equation. The cell-centered layout is adopted, i.e., flow variable nodes are placed at the center of each grid cell. With this combination of the scheme and the node-cell layout the global conservation property has been derived in a straightforward manner. The scheme was applied to two types of flows. First the flow past a circular cylinder was computed at the Reynolds number Re=40. The integrated momentum and mass fluxes at inner and outer boundaries agreed up lo more than 11 significant figures. Thus the global conservation property was confirmed. The flow past a flat plate at zero angle of attack was computed. The integrated drag of the flat plate was found to be very insensitive to the grid resolution
資料番号: NALSP0014010
レポート番号: NAL SP-14
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43443&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