@techreport{oai:jaxa.repo.nii.ac.jp:00043325,
 author = {福田, 正大 and 中橋, 和博 and 廣瀬, 直喜 and 河合, 伸坦 and 菊野, 栄次 and Fukuda, Masahiro and Nakahashi, Kazuhiro and Hirose, Naoki and Kawai, Nobuhiro and Kikuno, Eiji},
 month = {Dec},
 note = {In recent years, numerical simulation method based on viscous equation is widely applied to aerodynamic research and development in the field of airfoil, wing, fuselage, etc. It is proved powerful, and the application of this method to propellar blades research and development, especially for the ATP-blades, is natural. While many experiences with two-dimensional viscous simulation for thick airfoils are accumulated, however experience for such thin airfoils with very sharp leading edge as often propeller blades have the characteristics is relatively few. The verification of the two-dimensional viscous simulation codes, NSFOIL and NS2D applied to one of those airfoils, NACA 16-204 airfoil which was tested by the two-dimensional wind tunnel at NAL last year, is main object of the present report. Mach number sweeps at low angles of attack and angle of attack sweeps at M=0.6 and 0.85 were made. The comparison of the computed aerodynamic characteristics with the wind tunnel data assure us that the method is useful in this field, although some improvements of the codes are to be desired., 資料番号: NALSP0009034, レポート番号: NAL SP-9},
 title = {前縁半径の小さい単独翼廻りの2次元粘性流解析コードの検証},
 year = {1988}
}