2000
DOI: 10.1002/(sici)1097-0363(20000430)32:8<903::aid-fld950>3.0.co;2-c
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The implementation of an aeronautical CFD flow code onto distributed memory parallel systems

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Cited by 3 publications
(2 citation statements)
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“…2 (2012) mesh and surface node-based pointers to define the nodes lying along the lines of off-surface structure in the mesh. Ierotheou et al (2000), reported also a flow solver (ESAUNA) for the compressible Navier-Stokes equations, that was able to utilize hybrid meshes. ESAUNA too, used a data structure that specially treated the block structured regions.…”
Section: Introductionmentioning
confidence: 99%
“…2 (2012) mesh and surface node-based pointers to define the nodes lying along the lines of off-surface structure in the mesh. Ierotheou et al (2000), reported also a flow solver (ESAUNA) for the compressible Navier-Stokes equations, that was able to utilize hybrid meshes. ESAUNA too, used a data structure that specially treated the block structured regions.…”
Section: Introductionmentioning
confidence: 99%
“…This partitioning strategy is usually used for problems where data is static or the domain is unchanging but the computation within different parts of the domain is dynamic. In the majority of the research investigations on parallel CFD, this terminology of domain decomposition is referred to as grid partitioning ([20], [21], [22], [23], [24], [25]). Behind this term of grid partitioning lays a simple idea which came from a natural way of dealing with large-scale computational meshes.…”
Section: Domain Decompositionmentioning
confidence: 99%