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

• Published in: Journal of aerospace technology and management Vol. 1; no. 2
• Main Authors: João Luiz F. Azevedo, Heidi Korzenowski
• Format: Journal Article
• Language: English
• Published: Instituto de Aeronáutica e Espaço (IAE) 01.07.2011
• Subjects: Cold gas flow; Finite volume method; Hypersonic flow; Spatial discretization schemes; Unstructured grids

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.