2026-03-15T18:03:00Z https://jaxa.repo.nii.ac.jp/oai

oai:jaxa.repo.nii.ac.jp:00045267 2023-06-20T21:42:22Z 1887:1893 1896:1898:1913:1917

A Numerical Method for Solving Transonic Flow past Aircraft in Cartesian Coordinates 航空機周辺遷音速流の物理座標数値解法 中村, 正義 NAKAMURA, Masayoshi A numerical method for computing inviscid transonic flow around an arbitrary aircraft configuration is described in this paper. The basic formula consists of simultaneous equations for variables of velocity potential and Mach number. This formula is a permutation of the full potential equation. The simultaneous equations are solved numerically, satisfying given boundary conditions. The shock wave is captured as a discontinuous surface where the flow conditions satisfy the shock wave relationship. The calculation flow field is a rectangular box field. Grid points and boundary points are generated in Cartesian coordinates. The grid points are equidistant but their intervals can be varied with the location. External forms of the aircraft and vortex sheets are shaped from numerous small triangular planes. The majority of the boundary points are on these external forms. The basic formula is expressed as difference equations using the grid points and the boundary points. The difference equations are solved in the numerical procedure. Several calculated results of this method are compared with the experimental and other numerical results. 資料番号: NALTR1008000 レポート番号: NAL TR-1008 航空宇宙技術研究所 National Aerospace Laboratory(NAL) 1988-12 eng technical report https://jaxa.repo.nii.ac.jp/records/45267 0389-4010 航空宇宙技術研究所報告 Technical Report of National Aerospace Laboratory TR-1008 1008 25 https://jaxa.repo.nii.ac.jp/record/45267/files/naltr01008.pdf application/pdf 2.5 MB 2020-01-29