Curvilinear finite-volume schemes using high-order compact interpolation

Fosso, P Arnaud; Deniau, Hugues; Sicot, Frédéric; Sagaut, Pierre

doi:10.1016/j.jcp.2010.03.027

Cited by 45 publications

(27 citation statements)

References 27 publications

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“…The field of high-order methods has seen a surge of research activity over the last decade, particularly due to its potential in applications such as LES [30][31][32][33][34], DNS [35][36][37], Computational Aero-Acoustics (CAA) [38,39], turbulent combustion [40] and vortex-dominated flows [41]. However, this field has not yet reached the level of maturity required to solve real flow problems on complicated geometries.…”

Section: Challenges and Strategies With Using High-order Methodsmentioning

confidence: 99%

High accuracy flow simulations: Advances and challenges for future needs in aeronautics

2011

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Section: Challenges and Strategies With Using High-order Methodsmentioning

confidence: 99%

High accuracy flow simulations: Advances and challenges for future needs in aeronautics

2011

View full text Add to dashboard Cite

“…At the interfaces between the mesh blocks, the 4-point scheme (12) cannot be applied. Therefore, for conforming grids, Fosso et al 4 proposed a flux reconstruction at the interfaces. It consists in using a noncentered scheme to determine the values of U at the interfaces, and thus compute the convective fluxes.…”

Section: Conforming Grid Interfacesmentioning

confidence: 99%

“…As for the scheme of Fosso et al, 4 a specific procedure has also been developed 13 to apply the 7-point filter of Visbal and Gaitonde 5 near conforming grid interfaces. It consists in using the centered filter (13) and five ghost cells indexed by i = 0, 1, 2, 3, 4 in Fig.…”

Section: Conforming Grid Interfacesmentioning

confidence: 99%

A flux reconstruction technique for non-conforming grid interfaces in aeroacoustic simulations

Bras

Deniau²,

Bogey

2016

22nd AIAA/CEAS Aeroacoustics Conference

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In this study, a technique of flux reconstruction is proposed to perform aeroacoustic computations using high-order methods on multiblock structured meshes with non-conforming grid interfaces. The use of such grids facilitates zonal mesh refinements, and flows at high Reynolds numbers can thus be simulated at a reasonable cost. The high-order methods consists of low-dissipation and low-dispersion implicit finite-volume numerical schemes. Using a flux reconstruction method, they can be applied on non-conforming grids. In a first part, the method is described. It is based on the application of non-centered spatial schemes and the use of ghost cells. The flow variables in the ghost cells are computed from the flow field in the grid cells using local meshless interpolations with radial basis functions. Then, the performance of the method is evaluated by carrying out two-dimensional simulations of vortex convection and of a mixing layer. The results show that no significant spurious acoustic waves are produced at the grid interfaces. Finally, the flux reconstruction approach is applied to the computation of a three-dimensional jet at a Mach number of 0.6 and a Reynolds number based on the jet diameter of 5.7 × 10 5. In particular, nonconforming grids are used to obtain 384 points in the azimuthal discretization in the jet shear layers, while using less points at the center of the jet. Preliminary results regarding the jet development are shown and compared with experimental data.

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“…For the other variables, including the velocity components u, v, w as well as T for an isothermal wall, the wall discretization for WMLES is different. More precisely, for the scheme of Fosso et al, 14 the objective remains to compute the flow variablesq at the interfaces 1/2 and 3/2, according to figure 4. With this aim in view, a no-slip condition leading to a velocity equal to zero, and the wall temperature T w are directly imposed at the wall interface.…”

Section: Implementation With High-order Numerical Schemesmentioning

confidence: 99%

Development of compressible large-eddy simulations combining high-order schemes and wall modeling

Bras

Deniau²,

Bogey

et al. 2015

21st AIAA/CEAS Aeroacoustics Conference

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Compressible Large Eddy-Simulations (LES) combining high-order methods with a wall model have been developed in order to compute wall-bounded flows at high Reynolds numbers. The high-order methods consist of low-dissipation and low-dispersion implicit finite-volume schemes. In a first part, the procedure used to apply these schemes in nearwall regions is presented. This procedure is based on a ghost cell reconstruction. Its validity is assessed by performing the LES of a bi-periodic turbulent channel flow at a Mach number of M = 0.2 and a friction Reynolds number of Reτ = 395. In a second part, to consider flows at higher Reynolds numbers, a LES approach using a wall model is proposed. The coupling between the wall model and the high-order schemes is described. The performance of the approach is evaluated by simulating a bi-periodic turbulent channel flow at M = 0.2 and Reτ = 2000, and an isothermal subsonic round jet at M = 0.6 and ReD = 5.7 × 10 5 . The results are in agreement with Direct Numerical Simulation (DNS) data and experimental results. In particular, the turbulent intensities obtained in the logarithmic region of the boundary layers of the channel flow and the jet far-field noise are successfully predicted.

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Curvilinear finite-volume schemes using high-order compact interpolation

Cited by 45 publications

References 27 publications

High accuracy flow simulations: Advances and challenges for future needs in aeronautics

High accuracy flow simulations: Advances and challenges for future needs in aeronautics

A flux reconstruction technique for non-conforming grid interfaces in aeroacoustic simulations

Development of compressible large-eddy simulations combining high-order schemes and wall modeling

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