Compressible Navier–Stokes analysis of an oscillating wing in a power-extraction regime using efficient low-speed preconditioning

Campobasso, M. Sergio; Drofelnik, Jernej

doi:10.1016/j.compfluid.2012.07.002

Cited by 26 publications

(33 citation statements)

References 16 publications

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“…Thus, the TD-counterpart of the steady smoother (7) is: In this study, the strongly coupled turbulent LSP approach for two-equation turbulence models was developed following the steps outlined in [6], but the 225 inviscid/viscous laminar kernel of the new turbulent preconditioner is that proposed by Weiss and Smith [16]. That preconditioner was previously successfully used for solving steady/unsteady inviscid and viscous laminar flows with the COSA code [7,33,2], and the turbulent preconditioner presented below was used for the analyses of [1]. 230…”

Section: Integration Of Time-dependent Equations 190mentioning

confidence: 99%

“…In these problem types, the choice of a density-based CFD solver is also very well suited [1]. However, the solution accuracy of these codes decreases in the presence of low-speed flow regions where the local Mach number drops below the threshold of 0.1 [2]. This is due primarily to improper scaling of 15 the numerical dissipation components as the local Mach number tends to zero (incompressible flow limit) [3,4].…”

Section: Introductionmentioning

confidence: 99%

“…where M is the local Mach number, M pg is a cut-off value based on the local pressure gradient [14,35], M vis is a viscous cut-off value [2], and is a small cut-off parameter that prevents (Γ c ) −1 from becoming singular where M p = 0.…”

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confidence: 99%

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Low-speed preconditioning for strongly coupled integration of Reynolds-averaged Navier–Stokes equations and two-equation turbulence models

Campobasso

Yan

Bonfiglioli

et al. 2018

Aerospace Science and Technology

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Please cite this article in press as: M.S. Campobasso et al., Low-speed preconditioning for strongly coupled integration of Reynolds-averaged Navier-Stokes equations and two-equation turbulence models, Aerosp. Sci. Technol. (2018), https://doi. AbstractComputational fluid dynamics codes using the density-based compressible flow formulation of the Navier-Stokes equations have proven to be very successful for the analysis of high-speed flows. However, solution accuracy degradation and, for explicit solvers, reduction of the residual convergence rates occur as the local Mach number decreases below the threshold of 0.1. This performance impairment worsens remarkably in the presence of flow reversals at wall boundaries and unbounded high-vorticity flow regions. These issues can be resolved using low-speed preconditioning, but there exists an outstanding problem regarding the use of this technology in the strongly coupled integration of the Reynoldsaveraged Navier-Stokes equations and two-equation turbulence models, such as the k − ω shear stress transport model. It is not possible to precondition only the RANS equations without altering parts of the governing equations, and * Corresponding author Email addresses: m.s.campobasso@lancaster.ac.uk (M.S. Campobasso), m.yan@lancaster.ac.uk (M. Yan), aldo.bonfiglioli@unibas.it (A. Bonfiglioli), there did not exist an approach for preconditioning both the RANS and the SST equations. This study solves this problem by introducing a turbulent lowspeed preconditioner of the RANS and SST equations that does not require any alteration of the governing equations. The approach has recently been shown to significantly improve convergence rates in the case of a one-equation turbulence model. The study focuses on the explicit multigrid integration of the governing equations, but most algorithms are applicable also to implicit integration methods. The paper provides all algorithms required for implementing the presented turbulent preconditioner in other computational fluid dynamics codes. The new method is applicable to all low-and mixed-speed aeronautical and propulsion flow problems, and is demonstrated by analyzing the flow field of a Darrieus wind turbine rotor section at two operating conditions, one of which is characterized by significant blade/vortex interaction. Verification and further validation of the new method is also based on the comparison of the results obtained with the developed density-based code and those obtained with a commercial pressure-based code.

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Section: Integration Of Time-dependent Equations 190mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Low-speed preconditioning for strongly coupled integration of Reynolds-averaged Navier–Stokes equations and two-equation turbulence models

Campobasso

Yan

Bonfiglioli

et al. 2018

Aerospace Science and Technology

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“…The test work in a wind tunnel by McKinney and DeLaurier [3] showed that the energy extraction efficiency was comparable to that of wind turbines. Extensive work related to energy extraction performance of oscillating foils can also be found in the study by Shimizu et al [4], Platzer et al [5], Zhu [6], Campobasso and Drofelnik [7,8], and Yu and Wang [9]. In their work sinusoidal flapping motions are usually used, and the effect of kinematic parameters (plunging and pitching amplitudes, oscillating frequency, and phase angle between pitching and plunging motions) and the corresponding flow evolutions are systematically investigated.…”

Section: Introductionmentioning

confidence: 97%

Systematic investigation of the flow evolution and energy extraction performance of a flapping-airfoil power generator

Xie

Zhang

et al. 2015

Energy

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“…The numerical results, obtained using = = 5 × 10 −3 and = 1 × 10 −3 , are then compared to the force predictions presented by [15,16]. The force coefficients , , and the moment coefficients , are presented in Figure 8.…”

Section: Validation Of Force Calculations Through An Oscillatingmentioning

confidence: 99%

Parametric Studies of Flat Plate Trajectories Using VIC and Penalization

Morency

Beaugendre

2018

Modelling and Simulation in Engineering

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Flying debris is generated in several situations: when a roof is exposed to a storm, when ice accretes on rotating wind turbines, or during inflight aircraft deicing. Four dimensionless parameters play a role in the motion of flying debris. The goal of the present paper is to investigate the relative importance of four dimensionless parameters: the Reynolds number, the Froude number, the Tachikawa number, and the mass moment of inertia parameters. Flying debris trajectories are computed with a fluid-solid interaction model formulated for an incompressible 2D laminar flow. The rigid moving solid effects are modelled in the NavierStokes equations using penalization. A VIC scheme is used to solve the flow equations. The aerodynamic forces and moments are used to compute the acceleration and the velocity of the solid. A database of 64 trajectories is built using a two-level full factorial design for the four factors. The dispersion of the plate position at a given horizontal position decreases with the Froude number. Moreover, the Tachikawa number has a significant effect on the median plate position.

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Compressible Navier–Stokes analysis of an oscillating wing in a power-extraction regime using efficient low-speed preconditioning

Cited by 26 publications

References 16 publications

Low-speed preconditioning for strongly coupled integration of Reynolds-averaged Navier–Stokes equations and two-equation turbulence models

Low-speed preconditioning for strongly coupled integration of Reynolds-averaged Navier–Stokes equations and two-equation turbulence models

Systematic investigation of the flow evolution and energy extraction performance of a flapping-airfoil power generator

Parametric Studies of Flat Plate Trajectories Using VIC and Penalization

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