Customized Grid Generation Codes for Benchmark Three-Dimensional Flows

Nishikawa, Hiroaki; Diskin, Boris

doi:10.2514/6.2018-1101

Cited by 10 publications

(2 citation statements)

References 7 publications

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“…The grid generation, coarsening, partition, and multigrid capabilities for the OM6 model are described in an accompanying paper. 26 The OM6 wing geometry used in this study has been slightly redefined for numerical analysis of turbulence model simulations.…”

Section: Transonic Flow Around An Om6 Wingmentioning

confidence: 99%

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Grid Convergence for Three Dimensional Benchmark Turbulent Flows

Diskin

Anderson

Pandya

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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Grid convergence studies are performed to establish reference solutions for benchmark three dimensional turbulent flows in support of the ongoing turbulence model verification and validation effort at the Turbulence Modeling Resource website curated by NASA. The benchmark cases are a subsonic flow around a hemisphere cylinder and a transonic flow around the ONERA M6 wing with a sharp trailing edge. The study applies widely-used computational fluid dynamics codes developed and supported at the NASA Langley Research Center: FUN3D, USM3D, and CFL3D. Reference steady-state solutions are computed for the Reynolds-Averaged Navier-Stokes equations with the Spalart-Allmaras turbulence model on families of consistently-refined grids composed of different types of cells. Coarse-to-fine and code-to-code solution variation is described in detail.

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Section: Transonic Flow Around An Om6 Wingmentioning

confidence: 99%

“…24,25 Capabilities of these codes are described in an accompanying paper to be presented at the same SciTech-2018 special session. 26 The RANS equations with the SA-neg variant 22 of the SA turbulence model 21 are solved for all flows considered in this paper. Three NASA CFD codes, FUN3D, USM3D, and CFL3D, are used in this study.…”

Section: Introductionmentioning

confidence: 99%

Grid Convergence for Three Dimensional Benchmark Turbulent Flows

Diskin

Anderson

Pandya

et al. 2018

2018 AIAA Aerospace Sciences Meeting

Self Cite

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Speculative anisotropic mesh adaptation on shared memory for CFD applications

Tsolakis,

Chrisochoides

2024

Engineering with Computers

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Efficient and robust anisotropic mesh adaptation is crucial for Computational Fluid Dynamics (CFD) simulations. The CFD Vision 2030 Study highlights the pressing need for this technology, particularly for simulations targeting supercomputers. This work applies a fine-grained speculative approach to anisotropic mesh operations. Our implementation exhibits more than 90% parallel efficiency on a multi-core node. Additionally, we evaluate our method within an adaptive pipeline for a spectrum of publicly available test-cases that includes both analytically derived and error-based fields. For all test-cases, our results are in accordance with published results in the literature. Support for CAD-based data is introduced, and its effectiveness is demonstrated on one of NASA’s High-Lift prediction workshop cases.

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