A shock-capturing methodology based on adaptative spatial filtering for high-order non-linear computations

Bogey, Christophe; Cacqueray, Nicolas de; Bailly, Christophe

doi:10.1016/j.jcp.2008.10.042

Cited by 295 publications

(226 citation statements)

References 63 publications

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“…The space derivatives in the governing equations are approximated by means of optimized finite difference schemes. Specifically, the convective terms are approximated by fourth-order optimized finite differences with an eleven-point stencil in each mesh direction [10], and the viscous terms by standard fourth-order finite differences. As a part of the algorithm, an optimized selective sixth-order filter also using an eleven-point stencil is applied in each direction to damp grid-to-grid oscillations in smooth flow regions.…”

Section: Governing Equations and Numerical Methodsmentioning

confidence: 99%

“…As a part of the algorithm, an optimized selective sixth-order filter also using an eleven-point stencil is applied in each direction to damp grid-to-grid oscillations in smooth flow regions. In order to ensure computational robustness for compressible flows with shocks, an adaptive nonlinear selective filtering strategy is employed [10]. Finally, time integration is carried out by means of a low-storage six-step Runge-Kutta scheme optimized in the wave number space [11].…”

Section: Governing Equations and Numerical Methodsmentioning

confidence: 99%

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DNS of turbulent flows of dense gases

Sciacovelli

Cinnella

Gloerfelt

et al. 2017

J. Phys.: Conf. Ser.

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Abstract. The influence of dense gas effects on compressible turbulence is investigated by means of numerical simulations of the decay of compressible homogeneous isotropic turbulence (CHIT) and of supersonic turbulent flows through a plane channel (TCF). For both configurations, a parametric study on the Mach and Reynolds numbers is carried out. The dense gas considered in these parametric studies is PP11, a heavy fluorocarbon. The results are systematically compared to those obtained for a diatomic perfect gas (air). In our computations, the thermodynamic behaviour of the dense gases is modelled by means of the Martin-Hou equation of state. For CHIT cases, initial turbulent Mach numbers up to 1 are analyzed using mesh resolutions up to 512 3 . For TCF, bulk Mach numbers up to 3 and bulk Reynolds numbers up to 12000 are investigated. Average profiles of the thermodynamic quantities exhibit significant differences with respect to perfect-gas solutions for both of the configurations. For high-Mach CHIT, compressible structures are modified with respect to air, with weaker eddy shocklets and stronger expansions. In TCF, the velocity profiles of dense gas flows are much less sensitive to the Mach number and collapse reasonably well in the logarithmic region without any special need for compressible scalings, unlike the case of air, and the overall flow behaviour is midway between that of a variable-property liquid and that of a gas.

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Section: Governing Equations and Numerical Methodsmentioning

confidence: 99%

Section: Governing Equations and Numerical Methodsmentioning

confidence: 99%

DNS of turbulent flows of dense gases

Sciacovelli

Cinnella

Gloerfelt

et al. 2017

J. Phys.: Conf. Ser.

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“…If we let ξ be the direction normal to an interface, we can transform equation (2) to characteristic form, as follows:…”

Section: Methodsmentioning

confidence: 99%

“…The sliding velocity was increased to 0.2U. The 6th-order filter of Bogey et al [2] was used in both cases, with a filtering strength σ sf of 0.2. This filter is designed to dissipate waves too short for the discretisation to represent without large dispersion errors, and has a significant effect only for π/2 < k∆x < π (see figure 1).…”

Section: Cylinder Wake At Re=1000mentioning

confidence: 99%

A sliding characteristic interface condition for direct numerical simulations

2015

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A characteristic interface condition serves as the basis for a novel sliding grid method, with a view to solving the compressible Navier-Stokes equations on block-structured grids that are delimited by boundary conditions in motion relative to each other. This requires that the convective and source terms of the equations in characteristic form be transformed to the reference frame of the neighbouring block, and interpolated. The method facilitates accurate interpolation at the interface, because the characteristic interface condition requires only a single layer of halo nodes. When a homogeneous direction is present, only 1-D interpolation is required, and schemes that might otherwise be too costly become affordable. The treatment also enjoys the same advantages as fixed characteristic interfaces do in relation to tolerance of grid discontinuities at block interfaces. The implementation and parallelisation of this method in a simulation code is described, and accuracy and performance demonstrated on a selection of test cases.

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“…However, a particular attention must be paid to the possible artificial dissipation of the turbulent structures and shocks motion 35 by the shock capturing procedure. Over the last years, DNC has been successfully applied to high-Reynolds-number subsonic jets to study noise sources 16 using large-eddy simulation (LES) approach.…”

mentioning

confidence: 99%

Direct Noise Computation of a Shocked and Heated Jet at a Mach Number of 3.30

Cacqueray

Bogey

Bailly

2010

16th AIAA/CEAS Aeroacoustics Conference

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An overexpanded axisymmetric jet at an exit Mach number of 3.30 and a Reynolds number of 10 5 is computed by compressible large-eddy simulation (LES) to determine directly its radiated sound field, using low-dissipation schemes in combination with an adaptative shock-capturing method. At the jet nozzle exit, static pressure and temperature are respectively equal to 0.5 × 10 5 Pa and 360 K, and a laminar flow profile is imposed. To assess the validity of the simulation, the mean aerodynamic field and the near-field pressure levels, obtained directly by LES, are compared to available literature data. The axial velocity fluctuations in the shear-layer are also characterized using azimuthal decomposition, and exhibit properties close to those observed in screeching jets. The acoustic field is dominated by axisymmetric and first azimuthal modes, and noise sources are investigated from the acoustic near field: Mach waves, shock-associated noise and turbulent mixing noise occuring around the end of the potential core are identified.

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A shock-capturing methodology based on adaptative spatial filtering for high-order non-linear computations

Cited by 295 publications

References 63 publications

DNS of turbulent flows of dense gases

DNS of turbulent flows of dense gases

A sliding characteristic interface condition for direct numerical simulations

Direct Noise Computation of a Shocked and Heated Jet at a Mach Number of 3.30

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