@techreport{oai:jaxa.repo.nii.ac.jp:00043220,
 author = {海田, 武司 and 宮川, 淳一 and 廣瀬, 直喜 and 河合, 伸坦 and Kaiden, Takeshi and Miyakawa, Jun-ichi and Hirose, Naoki and Kawai, Nobuhiro},
 month = {Dec},
 note = {Computational aerodynamics as an aircraft design tool now stands shoulder to shoulder with wind tunnel testing due to the rapid progress of computer software and hardware. In particular, the Navier-Stokes computation which has been researched re-cently, enables us to analyze airflow not only at a design point but also in off-design regions. NSFOIL, the high Reynolds number transonic airfoil analysis code developed at NAL, has been verified by comparing computations based on the code with results obtained from actual wind tunnel tests. This paper presents a validative discussion of the NSFOIL code in the region of low speed and high attack angle. The computational results are compared with results of wind tunnel tests and the vortex method, which is a separated flow analysis method, to in-vestigate the validity of the code and to further the development of future improvements. NSFOIL is found to be able to predict non-linear characteristics, in which conventional numerical methods are powerless. There is still some room for improvement to be able to calculate an exact stall angle., 資料番号: NALSP0007004, レポート番号: NAL SP-7},
 title = {二次元粘性流計算ソフトウェアの実用化},
 year = {1986}
}