Aerodynamic computations using a higher-order algorithm

Abstract

Introduction D ESPITE impressive progress in both algorithms and computers, the time required to compute the solution of the steady compressible Navier-Stokes equations for the flow about aerodynamic configurations remains excessive for routine use in aircraft design. Consequently, numerical solution techniques applicable to simpler physical models, such as panel methods or solvers incorporating the boundary-layer equations, are heavily used in the design process, despite their limitations. Although a substantial portion of the time required in a simulation based on the Navier-Stokes equations is involved in problem setup, including geometry definition and grid generation, and this needs to be addressed, the solution time is also excessive. One way to reduce the solution time is to improve the iterative method used to achieve a steady state. 1 Alternatively, the accuracy of the spatial discretization can be increased. This allows a reduction in the n