An assessment of unstructured grid finite volume schemes for cold gas hypersonic flow calculations
doi: 10.5028/jatm.2009.0102135152

João Luiz F. Azevedo*
Institute of Aeronautics and Space
São José dos Campos – Brazil
azevedo@iae.cta.br

Heidi Korzenowski
VSE- Vale Solutions in Energy
São José dos Campos – Brazil
heidi.korzenowski@vsesa.com.br

*author for correspondence

Abstract:

A comparison of five different spatial discretization schemes is performed considering a typical high speed flow application. Flowfields are simulated using the 2-D Euler equations, discretized in a cell-centered finite volume procedure on unstructured triangular meshes. The algorithms studied include a central difference-type scheme, and 1st- and 2nd-order van Leer and Liou flux-vector splitting schemes. These methods are implemented in an efficient, edge-based, unstructured grid procedure which allows for adaptive mesh refinement based on flow property gradients. Details of the unstructured grid implementation of the methods are presented together with a discussion of the data structure and of the adaptive refinement strategy. The application of interest is the cold gas flow through a typical hypersonic inlet. Results for different entrance Mach numbers and mesh topologies are discussed in order to assess the comparative performance of the various spatial discretization schemes.

Keywords:

Hypersonic flow, Cold gas flow, Finite volume method, Unstructured grids, Spatial discretization schemes.