@techreport{oai:jaxa.repo.nii.ac.jp:00045368,
 author = {神田, 宏 and 佐藤, 衛 and 三輪, 等 and 松野, 謙一 and 高梨, 進 and SUDANI, Norikazu and KANDA, Hiroshi and SATO, Mamoru and MIWA, Hitoshi and MATSUNO, Kenichi and TAKANASHI, Susumu},
 month = {May},
 note = {航空宇宙技術研究所二次元風洞においてNACA0012翼型について表面圧力分布測定,後流測定を行い,他風洞での測定結果との比較を通して本風洞における壁干渉,特に側壁干渉についての検討を行った。その結果,翼のまわりには設定マッハ数よりも低いマッハ数の流れが実現されている可能性のあることが判明した。そこで,今回得られた実験結果に遷音速相似則に基づいた側壁干渉によるマッハ数修正を施し,衝撃波位置,圧力分布,抵抗値等に検討を加えた結果,他風洞と非常に良好な一致が認められた。さらに二次元のCFD解析結果との対比においても良好な一致が得られ,本検討は二次元風洞における翼型試験に一つの妥当な評価を与えることがわかった。, Surface pressure and drag measurements on the NACA0012 airfoil were conducted in the NAL Two-Dimensional Transonic Wind Tunnel. Using a comparison with other wind tunnel data, the wall interference effects are discussed, especially those from the sidewall. The results suggest that the Mach number of the actual flow around the airfoil is lower than the setting Mach number. The Mach number correction for the sidewall boundary-layer effects based on the similarity rule was applied to the present measurements, thereby showing that the shock positions, the pressure distributions, and the minimum drag coefficients are in good agreement with both other wind tunnel resutls and the Navier-Stokes calculation. It is shown that the evaluation indicates satisfactory transonic airfoil test results in the NAL Two-Dimensional Transonic Wind Tunnel., 資料番号: NALTR1109000, レポート番号: NAL TR-1109T},
 title = {Evaluation of NACA0012 Airfoil Test Results in the NAL Two-Dimensional Transonic Wind Tunnel},
 year = {1991}
}