@techreport{oai:jaxa.repo.nii.ac.jp:00041181,
 author = {佐藤, 衛 and 神田, 宏 and 須谷, 記和 and 松野, 謙一 and Sato, Mamoru and Kanda, Hiroshi and Sudani, Norikazu and Matsuno, Kenichi},
 month = {Apr},
 note = {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},
 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},
 year = {1993}
}