@techreport{oai:jaxa.repo.nii.ac.jp:00045074,
 author = {河合, 伸坦 and 廣瀬, 直喜 and KAWAI, Nobuhiro and HIROSE, Naoki},
 month = {Jun},
 note = {A computer code, called NSFOIL, has been developed for analyzing high Reynolds number transonic flow around an airfoil. The implicit approximate factorization scheme for the Navier-Stokes (NS) equations with an algebraic eddy viscosity model of the turbulent boundary layer is used with the implicit boundary condition on the airfoil and the wake cut boundary. The present code contains various option parameters for physical models, and I/O forms, i.e., full or thin layer approximate NS equations, fully turbulent or transition models of boundary layer, etc. Emphasis is put on the various output forms of the computed results to provide aerodynamics designers with full information on aerodynamic, boundary layer and wake characteristics including shock-induced separation and trailing edge separation phenomena. Some of the computed results are presented and compared with the wind tunnel experiment results. In the appendix, the operation manual of the code is described., 資料番号: NALTR0816000, レポート番号: NAL TR-816},
 title = {高レイノルズ数遷音速流翼型解析プログラムNSFOILの開発},
 year = {1984}
}