AN ASSESSMENT OF UNSTRUCTURED GRID FINITE VOLUME SCHEMES FOR COLD GAS HYPERSONIC FLOW CALCULATIONS. doi: 10.5028/jatm.2009.0102135152

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 inclu...

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Bibliographic Details
Published inJournal of aerospace technology and management Vol. 1; no. 2
Main Authors João Luiz F. Azevedo, Heidi Korzenowski
Format Journal Article
LanguageEnglish
Published Instituto de Aeronáutica e Espaço (IAE) 01.07.2011
Subjects
Cold gas flow
Finite volume method
Hypersonic flow
Spatial discretization schemes
Unstructured grids
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Summary: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.
ISSN:2175-9146