Wall modeling for implicit large-eddy simulation and immersed-interface methods

Chen, Zhen Li; Hickel, Stefan; Devesa, Antoine; Berland, Julien; Adams, Nikolaus A.

doi:10.1007/s00162-012-0286-6

Cited by 50 publications

(35 citation statements)

References 39 publications

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“…The experimental and numerical data are well documented and available on line [67]. Hickel and his coworkers [27,68] obtained ILES results in good agreement with the experimental data, based on the ALDM scheme and Cartesian mesh. For the present compressible calculation, the bulk Mach number is set to be 0.2 to neglect the compressibility [69] and to facilitate comparisons with the water tunnel experimental data.…”

Section: Case Descriptionsupporting

confidence: 74%

A low dissipation numerical scheme for Implicit Large Eddy Simulation

Zhang

Chen

2015

Computers & Fluids

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Section: Case Descriptionsupporting

confidence: 74%

A low dissipation numerical scheme for Implicit Large Eddy Simulation

Zhang

Chen

2015

Computers & Fluids

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“…The forcing term f i is obtained directly from the imposed velocity satisfying a boundary condition of the next time step , using the discrete form of Eq. (6) and discrete time l: (11) where RHS is a term of the sum of advection, diffusion and the pressure gradient. τ w is the wall friction stress.…”

Section: Methodsmentioning

confidence: 99%

“…Tessicini et al [11] compared analytical results with results obtained in an IBM-large eddy simulation (LES) using a logarithmic wall function and discussed the deviations with results obtained in a fully resolved LES. Capizzano et al [12] proposed a wall diffusion model that can generate inner boundary layer points using a sub-grid approach in a Reynolds-averaged Navier-Stokes (RANS) simulation to get an accurate flow profile within the boundary layer, but they have not yet reported an extension of the model to include a convective term or to handle three-dimensional problems.…”

Section: Introductionmentioning

confidence: 96%

Vehicle Aerodynamics Simulation for the Next Generation on the K Computer: Part 2 Use of Dirty CAD Data with Modified Cartesian Grid Approach

Onishi¹,

Tsubokura²,

Obayashi³

et al. 2014

SAE Int. J. Passeng. Cars - Mech. Syst.

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The applicability of high-performance computing (HPC) to vehicle aerodynamics is presented using a Cartesian grid approach of computational fluid dynamics. Methodology that allows the user to avoid a large amount of manual work in preparing geometry is indispensable in HPC simulation whereas conventional methodologies require much manual work. The new frame work allowing a solver to treat 'dirty' computer-aided-design data directly was developed with a modified immersed boundary method. The efficiency of the calculation of the vehicle aerodynamics using HPC is discussed.The validation case of flow with a high Reynolds number around a sphere is presented. The preparation time for the calculation is approximately 10 minutes. The calculation time for flow computation is approximately one-tenth of that of conventional unstructured code. Results of large eddy simulation with a coarse grid differ greatly from experimental results, but there is an improvement in the prediction of the drag coefficient prediction when using 23 billion cells.A vehicle aerodynamics simulation was conducted using dirty computer-aided-design data and approximately 19 billion cells. The preparation for the calculation can be completed within a couple of hours. The calculation time for flow computation is approximately one-fifth of that of conventional unstructured code. Reasonable flow results around a vehicle were observed, and there is an improvement in the prediction of the drag coefficient prediction when using 19 billion cells. The possibility of the proposed methodology being an innovative scheme in computational fluid dynamics is shown.

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“…The delta wing geometry is mapped on the Cartesian grid via a conservative immersedinterface method (CIIM). 13 The wall-model is based on the turbulent boundary layer equations (TBLE), 4 and for comparison we also performed LES with a simple no-slip boundary condition.…”

Section: Numerical Methods and Setupmentioning

confidence: 99%

Wall modeled large eddy simulation of the VFE-2 delta wing

Zwerger

Hickel

Breitsamter

et al. 2015

33rd AIAA Applied Aerodynamics Conference

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We performed wall-modeled large-eddy simulation of the flow field around the VFE-2 delta wing, focusing on two aspects: (1) leading-edge bluntness e↵ects on the primary vortex separation and (2) vortex breakdown above the wing and its control. Regarding aspect (1), the VFE-2 delta wing with sharp leading-edge (SLE) and medium radius round leading-edge (MRLE) are considered for three angles of attack ↵ (13 , 18 , and 23 ) leading to di↵erent overall flow characteristics. The numerical simulations correctly predict the main flow phenomena and are quantitatively in reasonable to good agreement with experimental measurements of steady and unsteady surface pressures, velocity distributions, and vortex breakdown position and frequency. Regarding aspect (2), flow control by oscillating control surfaces and flow control by a geometric modification leading to an injection of fluid from the pressure side are investigated for the SLE at ↵ = 28 . Considering the influence on vortex breakdown position, the numerical simulations confirm experimental observations regarding oscillating control surfaces, and show promising potential for flow control.

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Wall modeling for implicit large-eddy simulation and immersed-interface methods

Cited by 50 publications

References 39 publications

A low dissipation numerical scheme for Implicit Large Eddy Simulation

A low dissipation numerical scheme for Implicit Large Eddy Simulation

Vehicle Aerodynamics Simulation for the Next Generation on the K Computer: Part 2 Use of Dirty CAD Data with Modified Cartesian Grid Approach

Wall modeled large eddy simulation of the VFE-2 delta wing

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