2023-02-04T17:09:08Zhttps://jaxa.repo.nii.ac.jp/?action=repository_oaipmhoai:jaxa.repo.nii.ac.jp:000449292022-09-28T02:42:16Z01887:0189301896:01898:01913:01917
Transonic Airfoil Design of Full Potential Flow I.Numerical Procedure and Its Computational Examplesenghttp://id.nii.ac.jp/1696/00044923/Technical Report完全ポテンシャル流の遷音速翼型設計Ⅰ.数値解法とその適用計算例石黒, 登美子神谷, 信彦河合, 伸坦ISHIGURO, TomikoKAMIYA, NobuhikoKAWAI, Nobuhiro航空宇宙技術研究所National Aerospace Laboratory(NAL)航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-672672441981-05A computational inverse procedure for transonic airfoils, in which geometries are determined from prescribed target pressure distributions, is presented. This is an iterative direct-inverse approach. The following two calculations are iterated until a target pressure distribution coincides with a direct solution on a temporary surface. One is the direct solution, which is calculated using the successive line over-relaxation method which solves the full inviscid compressible potential flow equation in the Neumann problem. The other is a modification of the temporary airfoil geometry, which is determined from the conservation law of mass flux using the normal velocity at the contour, which is obtained by solving the equation in the Dirichlet problem where the target pressure distribution is specified at the temporary contour. Furthermore, a boundary layer calculation is made and a displacement thickness is subtracted to yield an actual airfoil geometry. Several examples illustrating this method are presented for flows with and without shock waves.0389-4010https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44929&item_no=1&attribute_id=31&file_no=1資料番号: NALTR0672000レポート番号: NAL TR-6722020-01-29