Numerical Study of Acoustic Installation Effects with a Computational Aeroacoustics Method

Redonnet, Stephane; Desquesnes, G.; Manoha, Eric; Parzani, Céline

doi:10.2514/1.42153

Cited by 46 publications

(22 citation statements)

References 21 publications

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“…All the CAA calculations were conducted with ONERA's sAbrinA.v0 solver [3][4][5][6][7][16][17][18] , using NASA computational resources. sAbrinA.v0 is a structured grid, time-accurate CAA code that solves the full Euler equations, either in a conservative form or non-conservative, perturbed form (with a splitting of the complete variables into a 'frozen' mean flow and a 'fluctuating' perturbation).…”

Section: Iiic2 Computational Set Upmentioning

confidence: 99%

CFD-CAA Coupled Calculations of a Tandem Cylinder Configuration to Assess Facility Installation Effects

Redonnet¹,

Lockard

Khorrami

et al. 2011

17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)

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Section: Iiic2 Computational Set Upmentioning

confidence: 99%

CFD-CAA Coupled Calculations of a Tandem Cylinder Configuration to Assess Facility Installation Effects

Redonnet¹,

Lockard

Khorrami

et al. 2011

17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)

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“…We have not explicitly included the intereference effects associated with jet /JSI noise coupling (which we believe are responsible for the oscillations in the data, see Sec. 7). Note that the level of agreement in most cases lies within those oscillations; they are better at larger polar angles in the forward arc and higher Mach numbers.…”

Section: Rans--based Jet--surface Interaction Noise Predictionsmentioning

confidence: 70%

Effect of de-correlating turbulence on the low frequency decay of jet-surface interaction noise in sub-sonic unheated air jets using a CFD-based approach

Afsar

Leib

Bozak

2017

Journal of Sound and Vibration

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In this paper we extend the Rapid-distortion theory (RDT)-based model derived by Goldstein, Afsar & Leib (J. Fluid Mech., vol. 736, pp. 532-569, 2013) for the sound generated by the interaction of a large-aspect-ratio rectangular jet with the trailing edge of a flat plate to include a more realistic upstream turbulence spectrum that possess a de-correlation (i.e. negative dip) in its space-time structure and use results from three-dimensional Reynolds-Averaged Navier-Stokes (RANS) solutions to determine the mean flow, turbulent kinetic energy and turbulence length & time scales. Since the interaction noise dominates the low-frequency portion of the spectrum, we use an appropriate asymptotic approximation for the Rayleigh equation Green’s function, which enters the analysis, based on a two-dimensional mean flow representation for the jet. We use the model to predict jet-surface interaction noise for a range of subsonic acoustic Mach number jets, nozzle aspect ratios, streamwise and transverse trailing-edge locations and compare them with experimental data. The RANS meanflow computations are also compared with flow data for selected cases to assess their validity. We find that finite de-correlation in the turbulence spectrum increases the low-frequency algebraic decay (the low-frequency “roll-off”) of the acoustic spectrum with angular frequency to give a model that has a pure dipole frequency scaling. This gives better agreement with noise data compared to Goldstein et al. (2013) for Strouhal numbers less than the peak jet-surface interaction noise. For example, through sensitivity analysis we find that there is a difference of 10 dB at the lowest frequency for which data exists (relative to a model without de-correlation effects included) for the highest acoustic Mach number case. Secondly, our results for the planar flow theory provide a first estimate of the low-frequency amplification due to the jet-surface interaction for moderate aspect ratio nozzles when RANS meanflow quantities are used appropriately. This work will hopefully add to noise prediction efforts for aircraft configurations in which the exhaust systems are tightly integrated with the airframe

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“…(1) and (2). It can be said that LEE is wave equation with advective and input term, and this is sufficient to calculate the realistic sound propagation.…”

Section: A Linearized Euler Equationmentioning

confidence: 99%

Code Development of Linearized Euler Equation on Block-Structured Cartesian Mesh for Complicated Geometries

Fukushima

Sasaki

Nakahashi

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The Linearized Euler Equation code for aeroacoustic analysis has been developed on block-structured Cartesian mesh to treat the complicated geometries robustly and accurately. In the present method, spatial derivation and time integration are conducted by high order schemes and the immersed boundary method using ghost cell approach is employed at the wall boundary. At the block boundary, higher-order data exchange is conducted by Lagrange interpolation and near the outer boundary outgoing wave is damped by absorbing boundary domain. The present code is validated for two-dimensional and three-dimensional test cases. The accuracy and effectiveness of the present method are demonstrated in two-dimensional acoustic scattering problems. In the three-dimensional cases, acoustic scattering around a sphere and noise propagation from JT15D nacelle configuration were simulated and it showed the good agreement with the analytical and experimental results. Finally, noise shielding effect of an Over-the-Wing-mounted-Nacelle (OWN) configuration was estimated as an application. The results show that far-field SPL of OWN configuration is lower than that of conventional Under-the-Wing-mounted-Nacelle configuration by about 10dB due to the shielding effect of OWN configuration.

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Numerical Study of Acoustic Installation Effects with a Computational Aeroacoustics Method

Cited by 46 publications

References 21 publications

CFD-CAA Coupled Calculations of a Tandem Cylinder Configuration to Assess Facility Installation Effects

CFD-CAA Coupled Calculations of a Tandem Cylinder Configuration to Assess Facility Installation Effects

Effect of de-correlating turbulence on the low frequency decay of jet-surface interaction noise in sub-sonic unheated air jets using a CFD-based approach

Code Development of Linearized Euler Equation on Block-Structured Cartesian Mesh for Complicated Geometries

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