@techreport{oai:jaxa.repo.nii.ac.jp:00045041,
 author = {中村, 正義 and 鈴木, 弘一 and 中村, 正剛 and 白井, 正孝 and NAKAMURA, Masayoshi and SUZUKI, Koichi and NAKAMURA, Seigou and SHIRAI, Masataka},
 month = {Oct},
 note = {An experiment was carried out on transonic flows over an airfoil which was partially modified from an arbitrary airfoil. The modification was made to satisfy the shockless condition which predicted on NAL TR-602, TR-602T. Static pressure were measured at 88 points on the airfoil surface, when the test Mach number was 0.5～0.8, the test angle of attack was 0deg～4deg and the Reynolds number was 4.0～4.6×10(exp 6). A schockless transonic flow was observed under a test condition close to the design condition. The supersonic region extends from 0.3％ to 63％ of airfoil chord length and the local maximum Mach number is 1.36. The result of this experiment supports the artificial flow method for obtaining shockless transonic airfoils which are partially modified from an arbitrary airfoil., 資料番号: NALTR0783000, レポート番号: NAL TR-783},
 title = {衝撃波を伴わない遷音速翼型の実験},
 year = {1983}
}