並列タイトル等航技研二次元風胴の気流特性について(I)-マッハ数分布の気流偏角および側壁からの境界層吸込予備試験-
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-693
一般注記Experimental data on the flow quality of the NAL two-dimensional transonic wind tunnel are presented. Mach number distributions on the test section axis show good uniformity which is characterised by the two-sigma(standard deviation) values of 0.0003 to 0.001 for a range of Mach numbers from 0.4 to 1.0 Flow angularities, which were measured by using a wing model with a symmetrical cross section, remained within 0.04 degree for Mach numbers from 0.2 to 0.8. Side wall boundary layer suction was applied through a pair of porous plates. The variation of aerodynamic properties of the model due to the suction mass flow rate change is presented with a brief discussion. Two-dimensionality of the flow over the wing span is expected to be improved by applying the appropriate suction rate, which depends on the Mach number, Reynolds number and lift coefficient.
資料番号: NALTR0693000
レポート番号: NAL TR-693
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44950&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