An assessment of unstructured grid finite volume schemes for cold gas hypersonic flow calculations
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...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Instituto de Aeronáutica e Espaço (IAE)
2009-06-01
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| Series: | Journal of Aerospace Technology and Management |
| Subjects: | |
| Online Access: | http://www.jatm.com.br/papers/vol1_n2/JATMv1n2_p135-152_An_assessment_of_unstructured_grid_finite_volume_schemes_for_cold_gas_hypersonic_flow_calculations.pdf |
| 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. |
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| ISSN: | 1984-9648 2175-9146 |