Higher-order aerodynamic computations using an edge based finite volume scheme

Abstract

Methods of improving the computational performance of conventional low order, unstructured grid, cell vertex, finite volume codes, for the simulation of high speed compressible viscous flow, are considered. The objective is to improve the performance without requiring that major changes be made to existing codes. With this in mind, higher order discretisations and improved equation solution has been attempted, within wall boundary layer regions only. This is possible, using the structure that is present in the grids normally used to discretize the boundary layer regions. A number of examples are included to illustrate the improvement in computational performance that can be obtained in this way. © 2010 Springer-Verlag Berlin Heidelberg.