A New Version of Detached-eddy Simulation, Resistant to Ambiguous Grid Densities
By P. Spalart, Sébastien Deck, M. Shur, Kyle D. Squires, M. Strelets, A. Travin. 2006
2,644 citations recorded by the source corpus.
Subfields: Computational Mechanics, Environmental Engineering
View Paper: https://www.semanticscholar.org/paper/e4d8c51d85a11d670d8f6a9b178ca22873b938e8
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In Computational Mechanics
- F. Menter
- P. Spalart
- A. Travin
- A. Garbaruk
- M. Strelets
- Jochen Fröhlich
- Dominic von Terzi
- M. S. Gritskevich
In Environmental Engineering
Citations in the corpus
- Development of DDES and IDDES Formulations for the k-ω Shear Stress Transport Model (2012, methodology): “The resulting formulation was termed Delayed Detached Eddy Simulation (DDES) [3].”
- Hybrid LES/RANS methods for the simulation of turbulent flows (2008, background): “A possible explanation for these artifacts is the so-called modeled stress depletion (MSD) [67].”
- A hybrid RANS-LES approach with delayed-DES and wall-modelled LES capabilities (2008, methodology): “…the original definition used in DES (Spalart et al., 1997), ensures DDES performance in its RANS mode in the major part of any attached boundary layer independently on the wall-parallel grid-spacings, thus eliminating the known incorrect DES performance on ‘‘ambiguous” grids (Spalart et al., 2006).”
- Large-Eddy Simulation: Current Capabilities, Recommended Practices, and Future Research (2009, neutral): “[34] called delayed DES.”
- Assessment methods for unsteady flow distortion in aero-engine intakes (2018, methodology): “The numerical simulation used a DDES unsteady method, which applies the Unsteady Reynolds Averaged Navier-Stokes (URANS) equations in the boundary layer and the Large Eddy Simulation method in the highly unsteady regions away from the wall [30].”
- NUMERICAL PREDICTION OF BARE AND STRAKED CYLINDER VIV (2006, methodology): “Delayed DES The new version of the classic Spalart DES model, named DDES (Delayed Detached Eddy Simulation) was also examined [6].”
- Turbulence modelling of the flow past a pitching NACA0012 airfoil at 105 and 106 Reynolds numbers (2008, methodology): “To avoid a transition from URANS to LES in the boundary layer that could produce non physical artefacts, Spalart et al. (2006) introduced a modification of the rd parameter of the Spalart-Allmaras model, involved in near-wall damping, as follows : rd = ν + νt Sijκ2d2 .”