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.
Higher–Order Aerodynamic Computations Using an Edge Based Finite Volume Scheme
ADIGMA - A European Initiative on the Development of Adaptive Higher-Order Variational Methods for Aerospace Applications ; 2 ; 309-325
2010-01-01
17 pages
Article/Chapter (Book)
Electronic Resource
English
Boundary Layer , AIAA Paper , Unstructured Mesh , Delta Wing , Free Stream Mach Number Engineering , Engineering Fluid Dynamics , Astronomy, Astrophysics and Cosmology , Classical Continuum Physics , Aerospace Technology and Astronautics , Appl.Mathematics/Computational Methods of Engineering , Numerical and Computational Physics
Aerodynamic computations using a higher-order algorithm
AIAA | 1999
|Aerodynamic Computations Using a Higher-Order Algorithm
British Library Conference Proceedings | 1999
|"Development of a Higher-Order Algorithm for Aerodynamic Computations"
British Library Conference Proceedings | 1999
|