並列タイトル等Measurements of Unsteady Pressure Distributions on an Oscillating Two-Dimensional Airfoil in Subsonic and Transonic Flow
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-501
一般注記The unsteady pressure distributions on an oscillating two-dimensional airfoil have been measured in the regions of subsonic and transonic flow, a Reynolds number range from 0.4×10(exp 6) to 2.0×10(exp 6) and a reduced frequency range from 0.01 to 0.1. Results of the experimental investigation are compared with those obtained by use of an incompressible theory and a doublet lattice method based on the lifting surface theory in the all Mach number ranges. In the subcritical regions the correction matrices to account for differences in the experimental and theoretical values have been calculated. In the supercritical regions the pressure deviations from the theoretical values due to the periodical motion of the shock are discussed and illustrated. Results, which are presented for supercritical flow with or without the shock, show that the transonic similarity law is valid in the unsteady reduced lift curve slope.
資料番号: NALTR0501000
レポート番号: NAL TR-501
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44754&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