An experimental study of jet noise part I: Turbulent mixing noise

Tanna, H. K.

doi:10.1016/0022-460x(77)90493-x

Cited by 307 publications

(196 citation statements)

References 10 publications

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“…• to the flow direction, in agreement with previously reported directivity patterns of subsonic jets [16,20,29,34]. No information at angles smaller than 18·5…”

Section: Acoustic Far Field Resultssupporting

confidence: 90%

“…Most of the work mentioned concerned low velocity jets (Ma<0·3), and do not or briefly discuss properties of the acoustic far field. Contrary to the aforementioned, Mollo-Christensen et al [20], Lush [16], Tanna [34] and Ahuja [1] reported properties of the acoustic far field of subsonic turbulent jets in detail, but did not investigate the flow field. Stromberg et al [29] combined measurements of the acoustic far field and flow field of a subsonic turbulent jet with a low Reynolds number in their work, but used their experimental results mainly to illuminate the process of jet noise production.…”

Section: Introductionmentioning

confidence: 97%

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Experiments on the Flow Field and Acoustic Properties of a Mach number 0·75 Turbulent Air Jet at a Low Reynolds Number

Slot

Moore

Delfos

et al. 2009

Flow Turbulence Combust

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In this paper we present the experimental results of a detailed investigation of the flow and acoustic properties of a turbulent jet with Mach number 0·75 and Reynolds number 3·5 10 3 . We describe the methods and experimental procedures followed during the measurements, and subsequently present the flow field and acoustic field. The experiment presented here is designed to provide accurate and reliable data for validation of Direct Numerical Simulations of the same flow. Mean Mach number surveys provide detailed information on the centreline mean Mach number distribution, radial development of the mean Mach number and the evolution of the jet mixing layer thickness both downstream and in the early stages of jet development. Exit conditions are documented by measuring the mean Mach number profile immediately above the nozzle exit. The fluctuating flow field is characterised by means of a hot-wire, which produced radial profiles of axial turbulence at several stations along the jet axis and the development of flow fluctuations through the jet mixing layer. The axial growth rate of the jet instabilities are determined as function of Strouhal number, and the axial development of several spectral components is documented. The directivity of the overall sound pressure level and several spectral components were investigated. The spectral content of the acoustic far field is shown to be compatible with findings of hot-wire experiments in the mixing layer of the jet. In addition, the measured acoustic spectra agree with Tam's large-scale similarity and fine-scale similarity spectra (Tam et al., AIAA Pap 96, 1996).

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“…• to the flow direction, in agreement with previously reported directivity patterns of subsonic jets [16,20,29,34]. No information at angles smaller than 18·5…”

Section: Acoustic Far Field Resultssupporting

confidence: 90%

Section: Introductionmentioning

confidence: 97%

Experiments on the Flow Field and Acoustic Properties of a Mach number 0·75 Turbulent Air Jet at a Low Reynolds Number

Slot

Moore

Delfos

et al. 2009

Flow Turbulence Combust

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“…The cold jet flow conditions (Test Point 7 of Tanna [29]) are specified. These conditions are widely used in jet dynamics and noise experiments with an acoustic Mach number at the jet exit M a ac = U j /a ∞ = 0.9 and a temperature ratio T j /T ∞ = 0.84.…”

Section: Computational Overviewmentioning

confidence: 99%

Turbulent jet characteristics for axisymmetric and serrated nozzles

Xia

2015

Computers & Fluids

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Turbulent jet large eddy simulations (LES) are performed at Mach 0.9 and Reynolds number around 10 6 . Implicit large-eddy simulation (ILES) is employed, namely omitting explicit subgrid scale models. The Reynolds-averaged Navier-Stokes (RANS) solution is blended into the near wall region. This makes an overall hybrid LES-RANS approach. A Hamilton-Jacobi equation is applied to remove the disparate turbulence length scales implied by hybridization. Computations are contrasted for a baseline axisymmetric (round) nozzle and a serrated (or chevron) nozzle with high bending and penetration. Jet characteristics for both nozzles are studied in detail with well documented experimental data compared. The chevron effects are demonstrated by comparing both solutions using the same mesh resolution and flow conditions. Higher order velocity moments with potential for aeroacoustic modeling and noise prediction, such as the two-point velocity spatial correlations, are also explored. Numerical simulations presented in this study utilize an in-house flow solver with improved parallel scalability and efficiency by means of data packeting and a scheduling algorithm similar to the Round Robin scheduling.

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“…The effect of temperature on jet noise has been widely investigated experimentally (Tanna, 1977;Tanna et al, 1975;Viswanathan, 2004). It has been observed that, for a fixed acoustic Mach number M a = U j /c 0 , where c 0 is the sound velocity at ambient temperature, the radiated noise directly depends on the jet temperature.…”

Section: Temperature Effectmentioning

confidence: 99%