Jet and jet–wing noise modelling based on the CABARET MILES flow solver and the Ffowcs Williams–Hawkings method

Semiletov, Vasily; Yakovlev, P. G.; Karabasov, Sergey A.; Faranosov, G. A.; Kopiev, V. F.

doi:10.1177/1475472x16659387

Cited by 26 publications

(4 citation statements)

References 22 publications

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“…Particular features of the CABARET method include compactness of the computational stencil and asynchronous time stepping for efficient calculations on non-uniform space-time grids (Semiletov and Karabasov, 2013). The CABARET solver was validated for a range of jet flows (Semiletov et al 2016b;Faranosov et al 2013). The LES implementation on GPUs further enabled a considerable reduction of the solution time in comparison with conventional LES approaches (Markesteijn and Karabasov, 2018a;Markesteijn and Karabasov, 2018b;Markesteijn and Karabasov, 2019;Markesteijn et al 2020).…”

Section: B Les Modellingmentioning

confidence: 99%

Broadband shock-associated noise modelling for high-area-ratio under-expanded jets

Gryazev

Kalyan

Markesteijn

et al. 2021

The Journal of the Acoustical Society of America

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Broadband Shock Associated Noise (BBSAN) is an important component of supersonic jet noise for jets at off-design conditions when the pressure at the nozzle exit is different from the ambient.Two high area ratio under-expanded supersonic jets at Nozzle Pressure Ratios (NPRs) 3.4 and 4.2 are considered. The jets correspond to conditions of the experiment in the Laboratory for Turbulence Research in Aerospace and Combustion (LTRAC) in the Supersonic Jet Facility of Monash University. Flow solutions are obtained by the Large Eddy Simulation (LES) and Reynolds Averaged Navier-Stokes (RANS) methods. The solutions are validated against the Particle Image Velocimetry (PIV) data. For noise spectra predictions, the LES solution is combined with the timedomain Ffowcs Wiliams -Hawkings method. To probe accuracy of the reduced-order method based on acoustic analogy, the RANS solutions are substituted in the Morris and Miller BBSAN method, where different options for modelling of the acoustic correlation scales are investigated. The noise spectra predictions are compared with the experimental data from the non-anechoic LTRAC facility and the NASA empirical sJet model. Apart from the low-frequencies influenced by the jet mixing noise, the RANS-based acoustic predictions align with those from LES for most frequencies in the range of Strouhal numbers (St) 0.4

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Section: B Les Modellingmentioning

confidence: 99%

Broadband shock-associated noise modelling for high-area-ratio under-expanded jets

Gryazev

Kalyan

Markesteijn

et al. 2021

The Journal of the Acoustical Society of America

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“…Pankaj and Sunil (2019) investigated the aerodynamic and acoustic features under the interaction of a nozzle injector with the main jet using large eddy simulations. Semiletov et al (2016) conducted integrated large eddy simulations (MILES) based on the CABARET scheme for a coaxial subsonic unheated jet with and without a swept lifting wing under free-stream conditions. Viswanathan (2018) developed a new method to predict the noise of realistic dual-stream jets.…”

Section: Introductionmentioning

confidence: 99%

Effects of Porous Parameters on the Aerodynamic Noise of the Blowing Device of Guardrails

2022

JAFM

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To solve the problem of the strong noise generated in the galvanizing process on the surface of the guardrail board, optimal design of the outlet structure of the blowing device is carried out according to the sound absorption and noise reduction theory of microperforated plates. The aerodynamic characteristics and aerodynamic noise analysis of the blowing device are investigated by large eddy simulation with dynamic grid technology. The oblique surface of the outlet is processed with blind holes, and then the influence of blind holes on the aerodynamic noise of the blowing device is explored, including different shapes, porosities and depths. The spectral study reveals that when the guardrail board just enters the blowing device, there is greater noise compared to other working conditions. The place with the highest noise sound pressure level (SPL) is at the outlet of the blowing device at the monitoring point of R=1 m and the direction of 90°. The SPLs of the monitoring points at 0° and 180° are smaller than those in other directions, while the SPL distribution of the monitoring points in other directions is relatively even. Compared with the original blowing device, the best noise reduction performance is achieved when the blowing device has cylindrical holes, with a porosity of 10% and a hole depth of 3 mm. The noise reduction value reaches up to 28.4 dB. In addition, an aerodynamic noise test was carried out on the blowing device in the corrugated board galvanizing workshop to demonstrate the correctness of the results of the numerical simulation.

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“…Due to the urgency of further reducing aircraft noise, jet-wing interaction noise has gained much attention in the research community in recent years (Mead & Strange 1998;Pastouchenko & Tam 2007;Bondarenko et al 2012;Brown 2013;Semiletov et al 2016;Bhat & Blackner 1998;Moore 2004;Vera et al 2015;Cavalieri et al 2014;Piantanida et al 2016;Lyu & Dowling 2016;. Recent work shows that the scattering of wave-packets can be used to model installed jet noise around peak frequencies.…”

Section: Introductionmentioning

confidence: 99%

Modelling installed jet noise due to the scattering of jet instability waves by swept wings

Lyu

Dowling

2019

J. Fluid Mech.

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Jet noise is a significant contributor to aircraft noise, and on modern aircraft it is considerably enhanced at low frequencies by a closely installed wing. Recent research has shown that this noise increase is due to the scattering of jet instability waves by the trailing edge of the wing. Experimentalists have recently shown that noise can be reduced by using wings with swept trailing edges. To understand this mechanism, in this paper, we develop an analytical model to predict the installed jet noise due to the scattering of instability waves by a swept wing. The model is based on the Schwarzschild method and Amiet’s approach is used to obtain the far-field sound. The model can correctly predict both the reduction in installed jet noise and the change to directivity patterns observed in experiments due to the use of swept wings. The agreement between the model and experiment is very good, especially for the directivity at large azimuthal angles. It is found that the principal physical mechanism of sound reduction is due to destructive interference. It is concluded that in order to obtain an effective noise reduction, both the span and the sweep angle of the wing have to be large. Such a model can greatly aid in the design of quieter swept wings and the physical mechanism identified can provide significant insight into developing other innovative noise-reduction strategies.

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Jet and jet–wing noise modelling based on the CABARET MILES flow solver and the Ffowcs Williams–Hawkings method

Cited by 26 publications

References 22 publications

Broadband shock-associated noise modelling for high-area-ratio under-expanded jets

Broadband shock-associated noise modelling for high-area-ratio under-expanded jets

Effects of Porous Parameters on the Aerodynamic Noise of the Blowing Device of Guardrails

Modelling installed jet noise due to the scattering of jet instability waves by swept wings

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