http://swrc.ontoware.org/ontology#TechnicalReport
Transonic Airfoil Design of Full Potential Flow I.Numerical Procedure and Its Computational Examples
en
石黒 登美子
神谷 信彦
河合 伸坦
ISHIGURO Tomiko
KAMIYA Nobuhiko
KAWAI Nobuhiro
航空宇宙技術研究所
National Aerospace Laboratory(NAL)
Technical Report of National Aerospace Laboratory TR-672
672
1981-05
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.
0389-4010
資料番号: NALTR0672000
レポート番号: NAL TR-672