ジェットを含む流れと風胴壁の干渉

• Material Type: 文書・図像類
• Title: ジェットを含む流れと風胴壁の干渉
• Author/Editor: 重見, 仁; 岩崎, 昭人; 深沢, 政広; SHIGEMI, Masashi; IWASAKI, Akihito; FUKASAWA, Masahiro
• Author Heading: 重見, 仁; 岩崎, 昭人; 深沢, 政広; SHIGEMI, Masashi; IWASAKI, Akihito; FUKASAWA, Masahiro
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1980-01
• Publication Date (W3CDTF): 1980-01
• Alternative Title: Boundary Wall Effects of Wind Tunnel on Flow Field Including Jet
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-596
• No. or year of volume/issue: 596
• Volume: 596
• Pages: 20-
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Target Audience: 一般
• Note (General): The recent demand for short take-off and landing makes designers of airplanes pay attention to powered high lift devices. When, however, they intend to test the model of such airplanes in wind tunnels, they sometimes face a new problem: the interference between boundary walls and the jet of high pressure, which is indispensable to simulate airplanes with powered high lift devices, may be so strong as to be beyond the ability of the existing methods of boundary-wall correction. An experiment was, therefore, conducted to inquire into the magnitude of interference between the boundary walls and the flow including jet. A two-dimensional wing was set in the gust wind tunnel of NAL Chofu Branch, which, contrary to the term used, can be used as an ordinary wind tunnel with the aid of a cart with fixed boundary walls. The working section of the cart is 2m×2m. The two-dimensional wing we used had an elliptical cross section, but the rear end part of it was replaced by a circular cylinder. High pressure air, introduced into the inside of the circular cylinder, was blown out as a jet through a slit cut along the meridian of the cylinder. In order to investigate the interference between the walls and the flow including jet systematically, some parameters were chosen. Relative strength of the jet was set to the desired value by changing the velocity of the free stream, with the pressure of the air in the circular cylinder being fixed. The angle of blowing of the jet was set to be 0deg, 30deg, 60deg, and 90deg by rotating the circular cylinder around its axis. The effective length of the slit was also changable to examine the effect of the three dimensionality of the jet. The measurement was made with the wing placed 1.0m, 0.55m, and 0.15m above the floor. The shifts of the path of the jet and the change of the lift force on the wing, due to the variation of the parameters mentioned above, were investigated carefully and the data were compared with those given by early workers. In order to estimate the strength of the interference between the boundary walls and the flow including jet, and to make the corrections of the data distorted by the effects of the boundary walls easy, a method to predict the induced angle of attack was developed. In this method, a formula of the panel method is applied to find an angle of attack, with which velocity distribution around the wing, in a potential flow, can be as close as possible to the destribution worked out from the measured pressure distribution. The amount of change of lift is thus transformed into that of an induced angle; that is, the magnitude of intereference between boundary walls and flow including jet is accounted for in terms of the induced angle of attack.; 資料番号: NALTR0596000; レポート番号: NAL TR-596
• Access Restrictions: 限定公開
• Data Provider (Database): 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）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 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