@techreport{oai:jaxa.repo.nii.ac.jp:00044929,
 author = {石黒, 登美子 and 神谷, 信彦 and 河合, 伸坦 and ISHIGURO, Tomiko and KAMIYA, Nobuhiko and KAWAI, Nobuhiro},
 month = {May},
 note = {A computational inverse procedure for transonic airfoils, in which geometries are determined from prescribed target pressure distributions, is presented. This is an iterative direct-inverse approach. The following two calculations are iterated until a target pressure distribution coincides with a direct solution on a temporary surface. One is the direct solution, which is calculated using the successive line over-relaxation method which solves the full inviscid compressible potential flow equation in the Neumann problem. The other is a modification of the temporary airfoil geometry, which is determined from the conservation law of mass flux using the normal velocity at the contour, which is obtained by solving the equation in the Dirichlet problem where the target pressure distribution is specified at the temporary contour. Furthermore, a boundary layer calculation is made and a displacement thickness is subtracted to yield an actual airfoil geometry. Several examples illustrating this method are presented for flows with and without shock waves., 資料番号: NALTR0672000, レポート番号: NAL TR-672},
 title = {Transonic Airfoil Design of Full Potential Flow I.Numerical Procedure and Its Computational Examples},
 year = {1981}
}