@techreport{oai:jaxa.repo.nii.ac.jp:00043195,
 author = {丸山, 祐一 and 秋下, 貞夫 and 中村, 昭人 and Maruyama, Yuichi and Akishita, Sadao and Nakamura, Akihito},
 month = {Nov},
 note = {An aerodynamic program for steady supersonic linearized potential flow using a higher order panel method has been developed. Boundary surface is divided into planar triangular panels on each of which a linearly varying doublet and a constant or linearly varying source are distributed. Distributions of source and doublet on the panel assemblies of the panels can be determined by their strengths at nodal points, which are placed at the vertices of the panels for linear distribution or on each panel for constant distribution. Since Morino's boundary condition is employed, the source strengths at the nodal points are determined explicitly. The doublet strengths at the nodal points are so determined that the perturbation velocity potential vanishes at any point inside the panel assembly. For this purpose, control points, the total number of which is equal to that of the nodal points of the doublet, are distributed in he inside domain of the panel assembly. The positions of the control points can be chosen practically arbitrarily. This simplifies the evaluation of influence coefficients, which represent the influence of source or doublet strengths upon the potential at the control points. The strength of the doublet at each nodel point is determined by setting the potential at control points to zero. From the test run for flows around cones, it is shown that constant source strength on each panel is preferable to that varying linearly when linear distribution is used for the doublet. The arbitrariness of the control points' positions is also assured by the simulations for the same type of flows. The results for flows around cones and spindle show good agreement with analytical solutions unless the perturbation is too large to satisfy the condition of linearized flow. Moreover, the fact that the trend of our results is just the same as that of the PAN AIR pilot code suggests equivalent computations are done by both programs, though the former's scheme is much simpler than the latter's., 資料番号: NALSP0005015, レポート番号: NAL SP-5},
 title = {パネル法による超音速計算空力プログラムの開発},
 year = {1985}
}