並列タイトル等Wall Interference Estimation of the NAL’s Two-Dimensional Wind Tunnel
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-829
一般注記Experiments with airfoil models at high subsonic speeds were carried out in the NAL’s two-Dimensional Wind Tunnel. The models were NACA0012 and GK-75-06-12 in airfoil. There were two NACA0012 models with chord lengths of 250mm and 150mm. The GK-75-06-12 model had a chord length of 250mm. The upper and lower walls of the test section of the tunnel are slotted. The open area ratio of the slotted walls was set at 3 and 10％ in the tests. In the tests of the smaller NACA0012 model, the total pressure of the uniform flow was set at 1.667 times that for the larger NACA0012 model. Thus the test Reynolds number was set at the same value for tests of the two different size models. The data obtained were corrected by the wall interference correction method developed at NAL. Pressure measured along the upper and lower walls is used in this method. After correcting the test data at one Reynolds number and Mach number, the corrected CL-α, Cm-α, and CL-CD relations were unique and did not vary with changes in chord length or open area ratio of the upper and lower walls. This fact means the correction method works very well in the range tested. In addition, the wall interference characteristics of the NAL’s Two-Dimensional Wind Tunnel were examined at the same time.
資料番号: NALTR0829000
レポート番号: NAL TR-829
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