On the interaction of a sound pulse with the shear layer of an axisymmetric jet, III: Non-linear effects

Bayliss, A.; Maestrello, L.; Turkel, Eli

doi:10.1016/0022-460x(86)90291-9

Cited by 14 publications

(3 citation statements)

References 11 publications

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“…This has been shown in experiments [10,11,12] and studied by analytical [13, 1 4 , 15, 16] and numerical [12,17,18] methods. A modied version of the Euler equations is employed to calculate the long time response of the excited jet.…”

Section: Introductionmentioning

confidence: 73%

Interaction of Sound from Supersonic Jets with Nearby Structures

1998

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A model of sound generated in an ideally expanded supersonic (Mach 2) jet is solved numerically. Two congurations are considered; (i) a free jet and (ii) an installed jet with a nearby array of exible aircraft type panels. In the later case the panels vibrate in response to loading by sound from the jet and the full coupling between the panels and the jet is considered, accounting for panel response and radiation. The long time behavior of the jet is considered. Results for near eld and far eld disturbance, the far eld pressure and the vibration of and radiation from the panels are presented. Panel response crucially depends on the location of the panels. Panels located upstream of the Mach cone are subject to a low level, nearly continuous spectral excitation and consequently exhibit a low level, relatively continuous spectral response. In contrast, panels located within the Mach cone are subject to a signicant loading due to the intense Mach w a v e radiation of sound and exhibit a large, relatively peaked spectral response centered around the peak frequency of sound radiation. The panels radiate in a similar fashion to the sound in the jet, in particular exhibiting a relatively peaked spectral response at approximately the Mach angle from the bounding wall.

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Section: Introductionmentioning

confidence: 73%

Interaction of Sound from Supersonic Jets with Nearby Structures

1998

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“…One is associated with the growth and decay of the instability waves in a nonuniform flow field. This problem was analyzed by Michalke [8] and Tarn [9] and numerically computed by Maestrello, et al [10] and Bayliss, et al [11,12] for the case of inviscid disturbances. Manuscript received at ASME Headquarters, September 15, 1987. For the case of a wavepacket in a viscous flow, the mechanism has been analyzed by Crighton and Huerre [13] and by Haj-Hariri and Akylas [14], The other mechanism is the sound generated by an externally imposed entropy spot or a density inhomogeneity convecting through a region of nonuniform flow, as was studied by Ffowcs-Williams and Howe [15], Candel [16], and Marble [17].…”

Section: Introductionmentioning

confidence: 99%

Instability and Sound Emission From a Flow Over a Curved Surface

Maestrello

Parikh

Bayliss

1988

Journal of Vibration and Acoustics

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The growth and decay of a wavepacket convecting in a boundary layer over a concave-convex surface is studied numerically using direct computations of the Navier-Stokes equations. The resulting sound radiation is computed using the linearized Euler equations with the pressure from the Navier-Stokes solution as a time-dependent boundary condition. It is shown that on the concave portion the amplitude of the wavepacket increases and its bandwidth broadens while on the convex portion some of the components in the packet are stabilized. The pressure field decays exponentially away from the surface and then algebraically exhibiting a decay characteristic of acoustic waves in two dimensions. The far field acoustic pressure exhibits a peak at a frequency corresponding to the inflow instability frequency. AnalysisThis section is divided into three parts. Part 1 contains a 538/Vol. 110, OCTOBER 1988 Transactions of the ASME Copyright © 1988 by ASME Downloaded From: http://vibrationacoustics.asmedigitalcollection.asme.org/ on 06/11/2015 Terms of Use: http://asme.org/terms Journal of Vibration, Acoustics, Stress, and Reliability in Design OCTOBER 1988, Vol. 110/ 539 Downloaded From: http://vibrationacoustics.asmedigitalcollection.asme.org/ on 06/11/2015 Terms of Use: http://asme.org/terms

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“…This schemehas beenusedsuccessfullyon a wide range of fluid and aeroacoustics problems [3][4][5][6][7][8][9][10][11][12][13][14][15]. Sankar, Reddy,andHariharanhaveevaluatedthis scheme for aeroacoustics applications [16].…”

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confidence: 99%

On increasing the accuracy of MacCormack schemes for aeroacoustic applications

Hixon

1997

3rd AIAA/CEAS Aeroacoustics Conference

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On the interaction of a sound pulse with the shear layer of an axisymmetric jet, III: Non-linear effects

Cited by 14 publications

References 11 publications

Interaction of Sound from Supersonic Jets with Nearby Structures

Interaction of Sound from Supersonic Jets with Nearby Structures

Instability and Sound Emission From a Flow Over a Curved Surface

On increasing the accuracy of MacCormack schemes for aeroacoustic applications

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