NUMERICAL SIMULATION OF 3D TRANSONIC INVISCID FLOW OVER A SWEPT WING

1.Introduction 2.Mathematical Model 3.Numerical Methods 4.Numerical Results 5.ConclusionProceedings of the Czech-Japanese Seminar in Applied Mathematics 2008Takachiho University of Miyazaki, Miyazaki, Japan, September 1-7, 2008AMS subject classifications. 76M12, 76H05, 76N99The aim of this work is to investigate some of the phenomena occuring in the numerical solution of transonic flows in outer aerodynamics. A comparison of various computational schemes based on the Finite Volume Method (FVM) is presented, particularly their ability to capture the important characteristics of an inviscid transonic flow around a wing, the well known test case - the Onera M6 wing. All the results are compared both in-between and with the experimental data. For the numerical computation at first two rather classical schemes based on Lax-Wendroff approach were used (cell-centered MacCormack and cell-vertex Ron-Ho-Ni) with added artificial dissipation along with two different structured finite volume meshes (C and H type). Simultaneously, the computation was carried out with the use of an unstructured grid using two modern schemes the first of which was based on Roe-Riemann solver and the second on an implicit scheme using the combination of HLLC numerical flux and WLSQR scheme