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

Authors

  • João Luiz F. Azevedo Instituto de Aeronáutica e Espaço - São José dos Campos/SP
  • Heidi Korzenowski VSE- Vale Solutions in Energy

Keywords:

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

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.

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Published

2011-07-26

Issue

Vol. 1 No. 2 (2009): Jul./Dec. 2009

Section

Original Papers

License

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