Coupling of Integral Acoustics Methods with LES for Jet Noise Prediction

Uzun, Ali; Lyrintzis, Anastasios S.; Blaisdell, Gregory A.

doi:10.2514/6.2004-517

Cited by 53 publications

(62 citation statements)

References 52 publications

(23 reference statements)

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“…It should be also stated that the CAA results are mesh dependent. A relatively fine mesh would show less difference between the two methods than a relatively coarse mesh [1,43].…”

Section: Specification Of Integral Surfacementioning

confidence: 94%

Surface integral analogy approaches for predicting noise from 3D high-lift low-noise wings

et al. 2014

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Three surface integral approaches of the acoustic analogies are studied to predict the noise from three conceptual configurations of three-dimensional high-lift low-noise wings. The approaches refer to the Kirchhoff method, the Ffowcs Williams and Hawkings (FW-H) method of the permeable integral surface and the Curle method that is known as a special case of the FW-H method. The first two approaches are used to compute the noise generated by the core flow region where the energetic structures exist. The last approach is adopted to predict the noise specially from the pressure perturbation on the wall. A new way to construct the integral surface that encloses the core region is proposed for the first two methods. Considering the local properties of the flow around the complex object-the actual wing with high-lift devices-the integral surface based on the vorticity is constructed to follow the flow structures. The surface location is discussed for the Kirchhoff method and the FW-H method because a common surface is used for them. The noise from the core flow region is studied on the basis of the dependent integral quantities, which are indicated by the Kirchhoff formulation and by the FW-H formulation. The role of each wall component on noise contribution is analyzed using the Curle formulation. Effects of the volume integral terms of Lighthill's stress tensors on the noise preThe project was supported by the Clean Sky Joint Undertaking (CSJU) (diction are then evaluated by comparing the results of the Curle method with the other two methods.

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“…It should be also stated that the CAA results are mesh dependent. A relatively fine mesh would show less difference between the two methods than a relatively coarse mesh [1,43].…”

Section: Specification Of Integral Surfacementioning

confidence: 94%

Surface integral analogy approaches for predicting noise from 3D high-lift low-noise wings

et al. 2014

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“…8 Far field noise computations in this study are performed by coupling the time-accurate, unsteady near-field data provided by the LES with the FWH method. 10,11 In our implementation, we apply the FWH method on the fly, that is, while the LES is running and computing unsteady data on the FWH control surface. The additional subroutine included in the LES code for the application the FWH method on the fly requires negligible computing cost as compared to the main LES.…”

Section: Computational Methodologymentioning

confidence: 99%

High-Fidelity Numerical Simulations of a Round Nozzle Jet Flow

Uzun¹,

Hussaini²

2010

16th AIAA/CEAS Aeroacoustics Conference

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This paper reports results from our ongoing research on high-fidelity jet noise simulations. We have previously presented results from the simulations of moderate Reynolds number cold jet flows exhausting from chevron nozzles. This paper presents results from the simulation of a baseline round nozzle without chevrons. The previous chevron nozzles and the current round baseline nozzle were experimentally studied by researchers at the NASA Glenn Research Center. Results from the simulations are compared with the experimental measurements. In this study, the flow inside the nozzle and the free jet flow outside are computed simultaneously by a high-order accurate, multi-block, large eddy simulation (LES) code with overset grid capability. For the round nozzle jet test case, we solve the governing equations on approximately 370 million grid points. The main emphasis of these simulations is to compute the jet flows in as much detail as possible and accurately capture the physical processes that lead to noise generation. The calculations resolve the jet flow field in an unprecedented level of detail by utilizing extreme computational resources and thus, they are the first of their kind. Two separate simulations are performed using turbulent and laminar inflow conditions at the jet nozzle inlet. Results are compared with experimental measurements. Results clearly show that nozzle inflow conditions have an influence on the jet flow field and far field noise.

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“…They argued that the aerodynamic sound is due to three different acoustic analogies, namely, monopoles, dipoles, and quadrupoles, from turbulences and other parameters related to the fluid around the solid object and the motion of the object. The extended theory is commonly used in the prediction of jet noise [12,13], rotor noise [14,15], and fan noise [16,17]. Lowson [18] also worked on the case of predicting the far-field noise due to a compressor.…”

Section: Introductionmentioning

confidence: 99%