@techreport{oai:jaxa.repo.nii.ac.jp:00041176,
 author = {須谷, 記和 and 松野, 謙一 and 神田, 宏 and 佐藤, 衛 and 三輪, 等 and 河本, 巌 and Sudani, Norikazu and Matsuno, Ken-ichi and Kanda, Hiroshi and Sato, Mamoru and Miwa, Hitoshi and Kawamoto, Iwao},
 month = {Jan},
 note = {BGK　No.1翼型に関する対応風洞試験が航空宇宙技術研究所(NAL)とカナダ国立航空研究所(IAR,旧NAE)の高レイノルズ数遷音速翼型試験設備において実施された。試験はレイノルズ数(翼弦長基準)21×10｛6｝を中心として低亜音速域から設計点を越える速度域まで実施され、圧力分布や空力係数の比較検討を行った。その結果、衝撃波の位置や衝撃波上流での圧力係数値に微妙な相違が認められ、側壁干渉効果補正の必要性が示唆された。そこで、ある側壁干渉補正法を適用したところ両者の測定結果は良好な一致を示すことが確認された。また、この試験により大仰角あるいは高マッハ数での抵抗測定の精度向上や流れの2次元性の確保などの新たな問題点が浮き彫りにされ、高精度の翼型試験の実現のための有益な資料を得ることができた。, A comparative study of BGK (Bauer Garabedian Korn) No. one airfoil data in the NAL (Japan) and IAR (Institute for Aerospace Research, Canada) high Reynolds number transonic wind tunnels was performed to evaluate the techniques and the accuracy of airfoil testing. Tests were conducted from a low subsonic speed over the design speed of the airfoil mainly at a Reynolds number of 21 million based on airfoil chord at both facilities. Pressure distributions and aerodynamic characteristics measured in both wind tunnels are compared and discussed. The results of the comparisons reveal slight differences in shock position and suction peak level ahead of the shock, suggesting the necessity of a correction for sidewall boundary-layer effects. Application of sidewall interference correction to both sets of wind tunnel data improves agreement between the two sets of data. The results also raise new issues on drag measurement and flow two dimensionality at a high angle of attack and/or a high Mach number. The results of this study will lead to improvements in the accuracy of airfoil testing., 資料番号: AA0004206000, レポート番号: NAL TR-1191T},
 title = {A comparative study of BGK No.1 airfoil data in high Reynolds number transonic wind tunnels},
 year = {1993}
}