Effect of a turbulent incoming boundary layer on noise radiation by the flow over cylindrical cavities

Chicheportiche, Jérémie; Gloerfelt, Xavier

doi:10.2514/6.2011-2862

Cited by 4 publications

(10 citation statements)

References 73 publications

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“…This is even more tricky when noise computations based on compressible equations are under investigation. Several tests have been conducted with more or less success in our team [1][2][3]10,25] and are used to identify lessons learned and to point to new directions. For that purpose, the turbulent inflow methods are classified as synthetic turbulence methods, recycling techniques, and transition by modal interaction.…”

Section: Critical Overview Of Inflow Turbulence Methods For Aeromentioning

confidence: 99%

“…Their synthetic eddy method (SEM) was improved by Pamiès et al [39] for triggering turbulent boundary layers. A comparison between RFM and SEM methods was conducted for the development of a supersonic boundary layer [2] or for prescribing a turbulent boundary layer ahead of a cylindrical cavity [3]. It was concluded that SEM was more efficient than RFM to reach a turbulent state rapidly for a well-chosen set of parameters.…”

Section: A Synthetic Turbulence Methodsmentioning

confidence: 99%

“…III. Some explorations conducted in the past [1][2][3] have shown that the issue is interrelated with the numerical choices for the inflow boundary condition and the discretization schemes. Furthermore, for a compressible simulation, it is important to specify correctly the thermodynamic quantities to ensure a quiet inflow.…”

Section: Introductionmentioning

confidence: 99%

“…The noise induced by the small step was not too penalizing at Mach 0.5 but it was seen to overwhelm the direct radiation for lower Mach numbers (0.1 to 0.3). Even if the trick used to ignite transition toward a turbulent state has been seen to produce considerably less spurious noise than other inflow conditions based on the introduction of synthetic turbulence or on recycling methods [1,3], further investigations toward an efficient and silent inflow method is needed to minimize inflow acoustic disturbance.…”

Section: Introductionmentioning

confidence: 99%

“…Preliminary studies, where instability modes are superimposed on an inlet inflectional velocity profile, were carried out for a cylindrical cavity flow [3] and for the interaction of an oblique shock with a supersonic turbulent boundary layer [10]. Besides, in previous studies about trailing edge noise [11] or boundary layer noise [4], the transition was triggered by using a two-dimensional step, similar to the tripping devices in experiments.…”

Section: Introductionmentioning

confidence: 99%

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Silent inflow condition for turbulent boundary layers

Gloerfelt

Robinet

2017

Phys. Rev. Fluids

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The generation of a turbulent inflow is a tricky problem. In the framework of aeroacoustics, another important constraint is that the numerical strategy used to reach a turbulent state induces a spurious noise which is lower than the acoustic field of interest. For the study of noise radiated directly by a turbulent boundary layer on a flat plate, this constraint is severe since wall turbulence is a very inefficient source. That is why a method based on a transition by modal interaction using a base flow with an inflection point is proposed to cope with that. The base flow must be a solution of the equations so we use a profile behind a backward-facing step representative of experimental trip bands. A triad of resonant waves is selected by a local stability analysis of the linearized compressible equations and is added with a weak amplitude in the inlet plane. The compressible stability calculation allows the specification of the thermodynamic quantities at the inlet, which turns out to be fundamental to ensure a quiet inflow. A smooth transition is achieved with the rapid formation of -shape vortices in a staggered organization as in subharmonic transition. The dominance of oblique waves promotes a rapid breakdown by the liftup mechanism of low-speed streaks. The quality of the fully turbulent state is assessed and the direct noise radiation from a turbulent boundary layer at Mach 0.5 is obtained with a very low level of spurious noise.

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Section: Critical Overview Of Inflow Turbulence Methods For Aeromentioning

confidence: 99%

Section: A Synthetic Turbulence Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Silent inflow condition for turbulent boundary layers

Gloerfelt

Robinet

2017

Phys. Rev. Fluids

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Study of interpolation methods for high-accuracy computations on overlapping grids

Chicheportiche

Gloerfelt

2012

Computers & Fluids

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is an open access repository that collects the work of Arts et Métiers ParisTech researchers and makes it freely available over the web where possible. AbstractOverset strategy can be an efficient way to keep high-accuracy discretization by decomposing a complex geometry in topologically simple subdomains.Apart from the grid assembly algorithm, the key point of overset technique lies in the interpolation processes which ensure the communications between the overlapping grids. The family of explicit Lagrange and optimized interpolation schemes is studied. The a priori interpolation error is analyzed in the Fourier space, and combined with the error of the chosen discretization to highlight the modification of the numerical error. When high-accuracy algorithms are used an optimization of the interpolation coefficients can enhance the resolvality, which can be useful when high-frequency waves or small turbulent scales need to be supported by a grid. For general curvilinear grids in more than one space dimension, a mapping in a computational space followed by a tensorization of 1-D interpolations is preferred to a direct evaluation of the coefficient in the physical domain. A high-order extension of the isoparametric mapping is accurate and robust since it avoids the inversion of a matrix which may be ill-conditioned. A posteriori error analyses indicate that the interpolation stencil size must be tailored to the accuracy of the discretization scheme. For well discretized wavelengthes, the resultsshow that the choice of a stencil smaller than the stencil of the corresponding finite-difference scheme can be acceptable. Besides the gain of optimization to capture high-frequency phenomena is also underlined. Adding order contraints to the optimization allows an interesting trade-off when a large range of scales is considered. Finally, the ability of the present overset strategy to preserve accuracy is illustrated by the diffraction of an acoustic source by two cylinders, and the generation of acoustic tones in a rotor-stator interaction.Some recommandations are formulated in the closing section.

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A silent inflow condition for the study of boundary layer noise

Gloerfelt

Robinet

2013

19th AIAA/CEAS Aeroacoustics Conference

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Effect of a turbulent incoming boundary layer on noise radiation by the flow over cylindrical cavities

Cited by 4 publications

References 73 publications

Silent inflow condition for turbulent boundary layers

Silent inflow condition for turbulent boundary layers

Study of interpolation methods for high-accuracy computations on overlapping grids

A silent inflow condition for the study of boundary layer noise

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