遷音速翼型試験における側壁干渉効果に関する流れの可視化を用いた研究

• Material Type: 文書・図像類
• Title: 遷音速翼型試験における側壁干渉効果に関する流れの可視化を用いた研究
• Author/Editor: 佐藤, 衛; 神田, 宏; 須谷, 記和; 松野, 謙一; Sato, Mamoru; Kanda, Hiroshi; Sudani, Norikazu; Matsuno, Kenichi
• Author Heading: 佐藤, 衛; 神田, 宏; 須谷, 記和; 松野, 謙一; Sato, Mamoru; Kanda, Hiroshi; Sudani, Norikazu; Matsuno, Kenichi
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1993-04
• Publication Date (W3CDTF): 1993-04
• Alternative Title: Oil flow visualization studies of sidewall effects in transonic airfoil testing
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory
• No. or year of volume/issue: 1196
• Volume: 1196
• Pages: 1-22
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Subject Heading: 風洞側壁干渉; 2次元風洞; 風洞試験; 遷音速流れ; 遷音速翼型; 流れの可視化; オイルフロー試験; 流れ2次元性; 風洞側壁境界層; 境界層吸い取り; 衝撃波境界層干渉; 風洞模型アスペクト比; 風洞性能向上; 遷音速風洞; wind tunnel side wall interference; two dimensional wind tunnel; wind tunnel test; transonic flow; transonic airfoil; flow visualization; oil flow test; flow two dimensionality; wind tunnel side wall boundary layer; boundary layer bleed; shock boundary layer interaction; wind tunnel model aspect ratio; wind tunnel performance improvement; transonic wind tunnel
• Target Audience: 一般
• Note (General): 2次元遷音速翼型試験における風洞側壁の影響を調べるため、航空宇宙技術研究所(NAL)・2次元遷音速風洞においてBGK No.1翼を対象にオイルフロー試験により翼表面の流れの可視化を行った。遷音速域においては翼表面の流れは、マッハ数、迎角、レイノルズ数に強く依存し、大きく4つのパターンに分類できることが判明した。特にマッハ数および迎角が翼の設計点を越えた場合には側壁境界層の影響を強く受け、衝撃波下流に1対の大規模な渦が形成され、翼近傍の流れは2次元性を保つことが困難となる。ここでは翼弦長の異なる模型を使用しアスペクト比効果を調べるとともに、模型近傍での側壁境界層の吸い取りも実施し、その影響の排除のための実験を行った。側壁境界層の翼面上の流れに与える効果および影響領域(空間的領域)が明らかとなり、より精度の高い2次元風洞試験法の確立のための資料を得ることができた。; Oil flow visualization tests were conducted in the NAL Two-Dimensional Transonic Wind Tunnel to investigate the sidewall boundary-layer effects in transonic airfoil testing. Flow patterns on an airfoil surface at transonic speeds, which change dramatically with the free-stream Much number, the angle of attack, or the chord Reynolds number, fall into four categories: A) attached flow with no shock; B) attached flow with shock; C) separated, but unreversed flow; D) separated flow downstream of the shock. Above the airfoil design Much number and/or at a high angle of attack, the flow around airfoil models is strongly affected by the test section sidewall boundary-layers: A pair of vortices appear behind a strong shock-wave, and thus the two-dimensional flow cannot be maintained. Tests using three different chord models were conducted to examine the effects of the aspect ratio. Preparatory tests conducted with sidewall boundary-layer suction reveal the significance of the sidewall boundary-layer effects on the airfoil flow field. Especially, the spatial region affected by the sidewalls is clearly defined. The sidewall affects the spanwise width of the shock-induced local separation region at the midspan of the airfoil. Greater understanding of these confounding factors will undoubtedly lead to greater accuracy and reliability of data obtained in two-dimensional wind tunnel airfoil testing.; 資料番号: AA0004211000; レポート番号: NAL TR-1196
• 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