Broadband trailing-edge noise prediction with a stochastic source model

Cozza, Ivan Flaminio; Iob, Andrea; Arina, Renzo

doi:10.1016/j.compfluid.2011.12.011

Cited by 11 publications

(10 citation statements)

References 33 publications

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“…However, this simple integer is unsuitable for the flap noise prediction.The power is N SL = 5.5 for low frequency side-edge component and N SH = 6.5 for high frequency side-edge component. For the trailing-edge component, the power is set to N T = 5.5, which is in good agreement with the fitted result 5.4 and 5.6, respectively provided by Cozza et al [31] and Ewert et al [32], based on CFD solutions and experimental data. To close the prediction model, we also need to formulate the normalized spectrum F (St), the flow energy conversion efficiency β and the directivity factor D (θ).…”

Section: Prediction Modelsupporting

confidence: 75%

Component-based model for Flap Noise Prediction

Jiang

Filippone

2019

25th AIAA/CEAS Aeroacoustics Conference

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Section: Prediction Modelsupporting

confidence: 75%

Component-based model for Flap Noise Prediction

Jiang

Filippone

2019

25th AIAA/CEAS Aeroacoustics Conference

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“…A synthetic turbulent spectra is generated by an advanced digital filter method. 16 Digital filter methods have been extensively used for CAA applications 23,24,25 due to their ability to reproduce realistic turbulence spectra with a low computational cost. In the current work, an advanced digital filter method 16 is used to generate a two-dimensional, isotropic, and frozen turbulence with a Gaussian energy spectrum, which is specified by the integral length scale Λ, and the turbulent intensity I xx .…”

Section: Ivb Broadband Turbulencementioning

confidence: 99%

Towards a Generic Non-Reflective Characteristic Boundary Condition for Aeroacoustic Simulations

Fattah

Gill

Zhang

2016

22nd AIAA/CEAS Aeroacoustics Conference

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A blended zonal characteristic boundary condition is proposed following a quantitative investigation of the performance of several non-reflective boundary conditions. Two test cases are considered that investigate the effects of acoustic and vortical plane waves impinging on the domain outflow region. A third test case investigates the effects of broadband turbulent flow impinging on a non-reflective outflow boundary condition. From these studies, two non-reflective boundary conditions based on a zonal characteristic method are found to provide a minimal acoustic response for impinging acoustic and vortical disturbances, respectively. These methods both make use of the transverse characteristic terms to improve performance, although each method uses a different inclusion of these terms. A final boundary condition is proposed that blends the performance of the two zonal characteristic methods. A blending function is used that switches the characteristic boundary condition smoothly between regions dominated by acoustic, or vortical, disturbances. The feasibility of this novel method is demonstrated on a test case where broadband turbulence impinges on a small section of an outflow region.

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“…Computational aeroacoustic (CAA) work-flows, based on stochastic sound source generation and sound propagation in the frequency domain, have previously been investigated in the literature. For instance, in Cozza et al [9], the sound sources are calculated using a digital filter-based stochastic turbulence method and the acoustic field is computed from the APE equations in the frequency domain. In Casalino et al [10], a stochastic Fourier method is used to compute the source terms of Howe's acoustic analogy [11], which is solved in frequency domain using a finite element method (FEM).…”

Section: Introductionmentioning

confidence: 99%

Airfoil trailing-edge noise prediction combining a random particle-mesh method with a Helmholtz solver

Kadar

Bras

Bériot

et al. 2018

2018 AIAA/CEAS Aeroacoustics Conference

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In this study, a computational aeroacoustic strategy is presented for the prediction of airfoil trailing-edge noise. This strategy is based on the use of a random particle-mesh method to compute noise sources, and the use of a Helmholtz solver to propagate sound waves. The random particle-mesh method is a stochastic approach that reconstructs sound sources from the steady mean flow statistics provided by an incompressible Reynolds-averaged Navier-Stokes simulation. The sound propagation is carried out in the frequency domain using a high-order finite element solver. For low-Mach number flows, assuming negligible mean flow convection effects, a non-homogeneous Helmholtz equation with a source term provided by the random particle-mesh method is solved. The performance of the numerical strategy is evaluated by simulating the sound radiated from the trailing-edge of a controlled-diffusion airfoil. The flow around the airfoil is characterized by a Mach number of 0.047 and a Reynolds number based on the airfoil chord length of Re c = 1.6 × 10 5 . The frequency domain results are found to be in good agreement with experimental data from the literature and with a full time-domain computation, used as reference. In particular, the trailing-edge noise radiated in the far-field region is well predicted.

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Broadband trailing-edge noise prediction with a stochastic source model

Cited by 11 publications

References 33 publications

Component-based model for Flap Noise Prediction

Component-based model for Flap Noise Prediction

Towards a Generic Non-Reflective Characteristic Boundary Condition for Aeroacoustic Simulations

Airfoil trailing-edge noise prediction combining a random particle-mesh method with a Helmholtz solver

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