On the sensitivity of sound power radiated by aircraft panels to turbulent boundary layer parameters

Rocha, Joana; Palumbo, Daniel L.

doi:10.1016/j.jsv.2012.05.030

Cited by 23 publications

(19 citation statements)

References 34 publications

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“…The approach in this paper will be slightly different as the system contains only a single panel and radiates to free space. The coupled solutions developed by da Rocha 15 will be used to predict the panel response and this response will be used in a model based on Wallace's solution 16 to predict the radiated sound power, as derived in Rocha 14 . If H is the transfer function from boundary layer excitation to panel displacement, the cross spectrum matrix of the panel displacement,  ww , can be written as (4) where H is the conjugate and H T is the transpose of H. Given a modal radiation matrix, R, derived from Wallace's farfield intensity predictions 16 and the panel velocity cross spectrum matrix,  vv  2  ww , the radiated sound power can be written as .…”

Section: Source Response and Radiation Modelsmentioning

confidence: 99%

The Influence of Boundary Layer Parameters on Interior Noise

Palumbo

Rocha

2012

18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)

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Predictions of the wall pressure in the turbulent boundary of an aerospace vehicle can differ substantially from measurement due to phenomena that are not well understood. Characterizing the phenomena will require additional testing at considerable cost. Before expending scarce resources, it is desired to quantify the effect of the uncertainty in wall pressure predictions and measurements on structural response and acoustic radiation. A sensitivity analysis is performed on four parameters of the Corcos cross spectrum model: power spectrum, streamwise and cross stream coherence lengths and Mach number. It is found that at lower frequencies where high power levels and long coherence lengths exist, the radiated sound power prediction has up to 7 dB of uncertainty in power spectrum levels with streamwise and cross stream coherence lengths contributing equally to the total.

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Section: Source Response and Radiation Modelsmentioning

confidence: 99%

The Influence of Boundary Layer Parameters on Interior Noise

Palumbo

Rocha

2012

18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)

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“…In their work, the modal excitation terms and acoustical radiation efficiency can be predicted properly and the predicted results are also compared with that of the wind tunnel and in-flight test. Rocha and Palumbo [7] further investigated the sensitivity of sound power radiated by aircraft panels to TBL parameters, and discussed the findings by Liu [4] that ring stiffeners may increase TBL induced noise radiation significantly.…”

Section: Introductionmentioning

confidence: 99%

TBL-Induced Structural Vibration and Noise

Xilong¹,

Kou²,

Liu³

2020

Boundary Layer Flows - Theory, Applications and Numerical Methods

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One of most import noise sources in a jet powered aircraft is turbulent boundary layer (TBL) induced structural vibration. In this chapter, the general model for the prediction of TBL-induced plate vibration and noise is described in detail. Then numerical examples for a typical plate are illustrated. Comparisons of plate vibration and radiated noise between numerical results and wind tunnel test are presented. The effects of structural parameters on modal-averaged radiation efficiency and therefore the radiated noise are discussed. The result indicates that an increment of flow velocity will increase the acoustic radiation efficiency below the hydrodynamic coincidence frequency range. The main reason for this phenomenon is that a higher convection velocity will coincide with lower order modes which have higher radiation efficiencies.

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“…Therefore, when looking at simple shapes, like that of a flat panel, analytical computational methods become a better choice. The analytical expressions for RSP can be derived for a given aircraft panel, in terms of the displacement PSD [1,17,18]. The acceleration PSD is calculated from the displacement PSD, which is proportional to the RSP [18].…”

Section: Acceleration Power Spectral Density and Radiated Sound Powermentioning

confidence: 99%

“…To show that calculating either , , or will give direct correlations to their effects on the RSP of a panel, the basic equations required to calculate RSP have been provided [17]:…”

Section: Rocha's Modelmentioning

confidence: 99%

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Reproducing Acceleration Power Spectral Density from an Aircraft Fuselage Panel Excited by Turbulent Boundary Layer Using Piezoelectric Actuators

Sonnenberg¹

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Noise and vibration in an aircraft cabin during cruise conditions is predominantly caused by external flow excitations from the turbulent boundary layer. The turbulent boundary layer causes the fuselage panels on the aircraft to vibrate. These vibrations radiate sound energy in the form of noise. This thesis describes a method to analytically optimize aircraft's cabin panel parameters, to reduce the acceleration power spectral density of the panel caused by the turbulent boundary layer, thereby reducing the radiated sound power into the cabin. In addition, this thesis presents an experimental validation, and modification of two existing analytical models used to calculate acceleration power spectral density for an aircraft panel, with three different excitations: (1) an impact hammer force, (2) a turbulent boundary layer, and (3) a piezoelectric patch. Finally, an optimization method has been developed to reproduce the acceleration power spectral density of an aircraft panel, at constant cruise conditions, by optimally selecting the placement of a given number of piezoelectric actuators, excited with a white noise distribution of frequencies within the human hearing range.ii

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On the sensitivity of sound power radiated by aircraft panels to turbulent boundary layer parameters

Cited by 23 publications

References 34 publications

The Influence of Boundary Layer Parameters on Interior Noise

The Influence of Boundary Layer Parameters on Interior Noise

TBL-Induced Structural Vibration and Noise

Reproducing Acceleration Power Spectral Density from an Aircraft Fuselage Panel Excited by Turbulent Boundary Layer Using Piezoelectric Actuators

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