並列タイトル等Transonic Internal Flow About an Airfoil Oscillating in Pitch -Comparisons between Computation and Experiment-
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As a preliminary investigation into the relationship between the transonic flutter characteristics and the shock behavior of a transonic cascade, a numerical analysis using a finite-difference method was carried out for a cascade oscillating in pitch about its midchord anti-phase with each other and a zero stagger angle, based on an assumption of inviscid flow. The computational method was examined by comparisons of computational results with experimental results of the shock wave periodic movements due to oscillation of the cascade, unsteady surface pressure and aerodynamic instability. Al-though quantitative differences in both results exists, which were caused by the presence of shock-boundary interaction in real phenomenon, the present computation was useful in the investigation of qualitative aspects of the shock wave behavior, aerodynamic instability and the relations between them. In such computation, it is necessary to make the computational mesh size small in comparison to the displacement of the shock wave.
資料番号: NALSP0003011
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=43153&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