Validation of OpenFOAM numerical methods and turbulence models for incompressible bluff body flows

Robertson, Eric D.; Choudhury, V.; Bhushan, Shanti; Walters, D. Keith

doi:10.1016/j.compfluid.2015.09.010

Cited by 178 publications

(81 citation statements)

References 37 publications

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“…The results are in agreement with experimental data [11] [12]. Several other studies in the literature have demonstrated OpenFOAM's effectiveness in modeling complex configurations [13] [14]. In acoustics, in addition to de Villiers' work, Olivier's work [15] addressed the noise of the trailing edge of NACA 0012.…”

Section: Introductionsupporting

confidence: 79%

A Numerical Approach to Possible Identification of the Noisiest Zones of a Wall Surface with a Flow Interaction

Kone¹,

Marchesse²,

Panneton³

2017

OJFD

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This paper examines the use of proper orthogonal decomposition (POD) and singular value decomposition (SVD) to identify zones on the surface of the source that contribute the most to the sound power the source radiates. First, computational fluid dynamics (CFD) is used to obtain the pressure field at the surface of the blade in a subsonic regime. Then the fluctuation of this pressure field is used as the input for the loading noise in the Ffowcs Williams and Hawkings (FW&H) acoustic analogy. The FW&H analogy is used to calculate the sound power that is radiated by the blade. Secondly, the most important acoustic modes of POD and SVD are used to reconstruct the radiated sound power. The results obtained through POD and SVD are similar to the acoustic power directly obtained with the FW&H analogy. It was observed that the importance of the modes to the radiated sound power is not necessarily in ascending order (for the studied case, the seventh mode was the main contributor). Finally, maps of the most contributing POD and SVD modes have been produced. These maps show the zones on the surface of the blade, where the dipolar aeroacoustic sources contribute the most to the radiated sound power. These identifications are expected to be used as a guide to design and shape the blade surface in order to reduce its radiated noise.

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Section: Introductionsupporting

confidence: 79%

A Numerical Approach to Possible Identification of the Noisiest Zones of a Wall Surface with a Flow Interaction

Kone¹,

Marchesse²,

Panneton³

2017

OJFD

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“…OpenFOAM-4.1 is an open-source MPI based finite volume CFD toolbox. In an earlier study, Robertson et al [44] verified and validated OpenFOAM's numerical methods and turbulence models for incompressible, single phase bluff-body flows, which involved flow over a sphere, a backward facing step, and a sharp leading-edge delta wing. Robertson et al determined that a 2 nd order implicit backward scheme was optimal for the time discretization; and a 2 nd -order linear upwind and blended 2 nd -order bounded central difference schemes are most efficient for URANS and DES simulations.…”

Section: Methodsmentioning

confidence: 99%

“…OpenFOAM simulations required a smaller time step, i.e., CFL < 2, for stability. In addition, OpenFOAM is more sensitive to grid topology than Ansys/Fluent and requires meshes with non-orthogonality (angle between the line connecting cell centers and face normal vector) less than 65 • to avoid instability in the pressure solution [44]. Highly non-orthogonal grids usually appear in the corners (at the intersection of the pin and the blade and/or hub) and were avoided by using a smaller near-wall grid spacing, as discussed in Section 4.2.…”

Section: Solution Parameters and High Performance Computingmentioning

confidence: 99%

Validation of Tidal Stream Turbine Wake Predictions and Analysis of Wake Recovery Mechanism

Salunkhe

Fajri

O'Doherty

et al. 2019

JMSE

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This paper documents the predictive capability of rotating blade-resolved unsteady Reynolds averaged Navier-Stokes (URANS) and Improved Delayed Detached Eddy Simulation (IDDES) computations for tidal stream turbine performance and intermediate wake characteristics. Ansys/Fluent and OpenFOAM simulations are performed using mixed-cell, unstructured grids consisting of up to 11 million cells. The thrust, power and intermediate wake predictions compare reasonably well within 10% of the experimental data. For the wake predictions, OpenFOAM performs better than Ansys/Fluent, and IDDES better than URANS when the resolved turbulence is triggered. The primary limitation of the simulations is under prediction of the wake diffusion towards the turbine axis, which in return is related to the prediction of turbulence in the tip-vortex shear layer. The shear-layer involves anisotropic turbulent structures; thus, hybrid RANS/LES models, such as IDDES, are preferred over URANS. Unfortunately, IDDES fails to accurately predict the resolved turbulence in the near-wake region due to the modeled stress depletion issue.

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“…The pimpleFoam code was selected as the computational solver. The reliability of the solver was tested previously [18,19]. The SSTDES model derived from the SST k-ω model was used to solve the Navier-Stokes equations.…”

Section: Methodsmentioning

confidence: 99%

Quantification and Analysis of the Irreversible Flow Loss in a Linear Compressor Cascade

Ottavy

et al. 2018

Entropy

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A local loss model and an integral loss model are proposed to study the irreversible flow loss mechanism in a linear compressor cascade. The detached eddy simulation model based on the Menter shear stress transport turbulence model (SSTDES) was used to perform the high-fidelity simulations. The flow losses in the cascade with an incidence angle of 2 • , 4 • and 7 • were analyzed. The contours of local loss coefficient can be explained well by the three-dimensional flow structures. The trend of flow loss varying with incidence angle predicted by integral loss is the same as that calculated by total pressure loss coefficient. The integral loss model was used to evaluate the irreversible loss generated in different regions and its varying trend with the flow condition. It as found that the boundary layer shear losses generated near the endwall, the pressure surface and the suction surface are almost identical for the three incidence angles. The secondary flow loss in the wake-flow and blade-passage regions changes dramatically with the flow condition due to the occurrence of corner stall. For this cascade, the secondary flow loss accounts for 26.1%, 48.3% and 64.3% of the total loss for the flow when the incidence angles are 2 • , 4 • and 7 • , respectively. Lastly, the underlying reason for the variation of the secondary flow loss with the incidence angle is explained using the L c iso-surface method.

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Validation of OpenFOAM numerical methods and turbulence models for incompressible bluff body flows

Cited by 178 publications

References 37 publications

A Numerical Approach to Possible Identification of the Noisiest Zones of a Wall Surface with a Flow Interaction

A Numerical Approach to Possible Identification of the Noisiest Zones of a Wall Surface with a Flow Interaction

Validation of Tidal Stream Turbine Wake Predictions and Analysis of Wake Recovery Mechanism

Quantification and Analysis of the Irreversible Flow Loss in a Linear Compressor Cascade

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