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A synthesis approach for reproducing the response of aircraft panels to a turbulent boundary layer excitation
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10.1121/1.3514530
/content/asa/journal/jasa/129/1/10.1121/1.3514530
http://aip.metastore.ingenta.com/content/asa/journal/jasa/129/1/10.1121/1.3514530
View: Figures

Figures

Image of FIG. 1.
FIG. 1.

Block diagram of the AWG for the synthesis of the TBL and of the TBL-induced vibro-acoustic responses, and the signal post-processor that estimates the corresponding MSEs.

Image of FIG. 2.
FIG. 2.

MSEs associated with the simulation of the TBL (dashed-dotted, J d ) and of the panel response: Velocity (dashed, J v ); near-field pressures (dotted, J p ); pressures radiated over the hemisphere (solid, J p h ).

Image of FIG. 3.
FIG. 3.

Kinetic energy due to the TBL (gray), and the one generated when using 3 × 7 loudspeakers driven to reproduce the TBL (dashed-dotted), the velocity response (dashed), the acoustic response over a near-field grid of 12 × 28 microphones (dotted) and over a hemisphere of 20 microphones (solid).

Image of FIG. 4.
FIG. 4.

Sound power radiated due to the TBL (gray), and the one generated when using 3 × 7 loudspeakers driven to reproduce the TBL (dashed-dotted), the velocity response (dashed), the acoustic response over a near-field grid of 12 × 28 microphones (dotted) and over a hemisphere of 20 microphones (solid).

Image of FIG. 5.
FIG. 5.

(Color online) Normalized PSD distribution of the pressures radiated at 970 Hz over a hemispherical grid of 20 microphones due to the TBL [S p h p h , (a)] and those generated using 3 × 7 loudspeakers driven to reproduce the TBL [, (b)], the panel velocity [, (c)], and the far-field pressures over the grid [, (d)]. Right column: Configuration sketches with in black the assumed or target fields.

Image of FIG. 6.
FIG. 6.

Spatial correlation structures at 275 Hz associated with the excitation (top) and with the panel structural and acoustic responses (respectively, middle and bottom), when perfect reproduction of the TBL is assumed (left) and that of the approximate generated using 3 × 7 loudspeakers driven to reproduce the near-field panel acoustic response over a grid of 12 × 28 microphones (right). On top: Configuration sketches per column with in black the assumed or target field.

Image of FIG. 7.
FIG. 7.

Number of acoustic sources required for a 10 dB reduction in the MSEs associated with the TBL (dashed-dotted) to the panel velocity (calculated: Dashed; coincidence criterion: Black circles; mode count: Gray dashed) and to the panel near-field (dotted) and far-field acoustic response (calculated: Solid; mode count: Gray solid).

Image of FIG. 8.
FIG. 8.

(Color online) Photographs of the experimental set-up used for synthesizing the TBL excitation (a), the TBL-induced velocity response (a, b), and the TBL-induced acoustic response (a–c).

Image of FIG. 9.
FIG. 9.

Sound power radiated by the clamped panel, obtained from the measured plant matrix and assuming a Corcos model of the TBL excitation (gray) and that experimentally synthesized using 4 × 4 loudspeakers driven to reproduce: The TBL (dashed-dotted) or the velocity response (dashed) (a); the near-field (dotted) or far-field (solid) acoustic response (b).

Image of FIG. 10.
FIG. 10.

(a) Sound power radiated in a cavity by a panel and (b) cavity potential energy when then panel is subject to the TBL (gray) and that generated by 3 × 7 loudspeakers driven to reproduce the TBL-induced pressures radiated into a free-field over a planar grid of 12 × 28 microphones (solid) and over a far-field hemisphere of 20 microphones (dotted) with radius 1.5 m.

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/content/asa/journal/jasa/129/1/10.1121/1.3514530
2011-02-02
2014-04-20
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752b84549af89a08dbdd7fdb8b9568b5 journal.articlezxybnytfddd
Scitation: A synthesis approach for reproducing the response of aircraft panels to a turbulent boundary layer excitation
http://aip.metastore.ingenta.com/content/asa/journal/jasa/129/1/10.1121/1.3514530
10.1121/1.3514530
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