2026-03-13T18:05:24Z https://jaxa.repo.nii.ac.jp/oai

oai:jaxa.repo.nii.ac.jp:00043211 2023-06-20T22:20:12Z 1887:1893 1896:1898:1913:1915

逆解法コード“WINDES"による遷音速翼設計の諸例 Transonic Wing and Airfoil Design Using Inverse Code WINDES 高梨, 進 Takanashi, Susumu In this paper, an iterative design procedure is presented for two- and three-dimensional transonic wings with prescribed (target) pressure distributions. The inverse code WINDES developed by the present author is used in combination with existing flow analysis codes in the iterative design method. The iteration proceeds in the following steps: First, the flow field is solved for an initially assumed wing by an analysis code. Next, "WINDES" is operated, which provides the approximate amount of wing geometry correction needed to compensate for the difference between the computed and the target pressure distributions. Consequently a new wing is obtained which can be used again as the input data for the analysis code. The same process is repeated until convergence is achieved. The advantage of the present approach is that the analysis code is retained in its original form and therefore can be treated as a "black box." The adoption of several analysis codes for potential, Euler, and ever Navier-Stokes equations has been successfully applied to transonic design problems. 資料番号: NALSP0005031 レポート番号: NAL SP-5 航空宇宙技術研究所 National Aerospace Laboratory(NAL) 1985-11 jpn technical report https://jaxa.repo.nii.ac.jp/records/43211 0289-260X AN10097345 航空宇宙技術研究所特別資料 Special Publication of National Aerospace Laboratory SP-5 5 251 256 https://jaxa.repo.nii.ac.jp/record/43211/files/nalsp0005031.pdf application/pdf 411.4 kB 2020-01-28