Jet-installation noise and near-field characteristics of jet–surface interaction

Rego, Leandro F.; Avallone, Francesco; Ragni, Daniele; Casalino, Damiano

doi:10.1017/jfm.2020.294

Cited by 35 publications

(15 citation statements)

References 50 publications

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“…The connection between jet installation noise and the flow-field features of the corresponding isolated jet has also been studied by Rego et al. (2020) using lattice Boltzmann numerical simulations.…”

Section: Introductionmentioning

confidence: 97%

“…The near-field pressure and far-field noise generated by a jet installed close to a semi-infinite plate has been analysed by Lawrence, Azarpeyvand & Self (2011) and Jordan et al (2017Jordan et al ( , 2018. The connection between jet installation noise and the flow-field features of the corresponding isolated jet has also been studied by Rego et al (2020) using lattice Boltzmann numerical simulations.…”

Section: Introductionmentioning

confidence: 99%

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An experimental investigation into model-scale installed jet–pylon–wing noise

et al. 2021

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A model-scale experimental investigation of an installed jet–pylon–wing configuration was conducted at the University of Southampton, with the scope to study the effect a pylon has on noise generation and to clarify its impact on the fluctuating wall-pressure load. The set-up consisted of two single-stream nozzles, a baseline axisymmetric annular nozzle and a partially blocked annular pylon nozzle. The nozzles were tested first isolated and then installed next to a NACA4415 aerofoil ‘wing’ at a single nozzle–wing position. The jet Mach number was varied between $0.5 \leq M_{{j}} \leq 0.8$ and measurements were performed both under static and in-flight ambient flow conditions up to ${M_{{f}} = 0.2}$ . The jet flow-field qualification was carried out using a single-velocity-component hot-wire anemometer probe. The pressure field on the wing surface was investigated using two miniature wall-pressure transducers that were flush-mounted in the streamwise and spanwise directions within the pressure side of the wing. A linear ‘flyover’ microphone array was used to record the noise radiated to the far field. The unsteady pressure data were analysed in both time and frequency domains using multi-variate statistics, highlighting a far-field noise reduction provided by the presence of the pylon only in the installed case. Furthermore, the wake field generated behind the pylon is seen to significantly modify the wall-pressure fluctuations, particularly at streamwise locations close to the pylon trailing edge.

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Section: Introductionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

An experimental investigation into model-scale installed jet–pylon–wing noise

et al. 2021

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“…For jet installation noise reduction, the porous medium model is applied in the trailing-edge region of a surface in the vicinity of a subsonic jet at ambient temperature. The jet is generated by a singlestream nozzle (SMC000), with an exit diameter D j ¼ 50.8 mm, and the installation effects are accounted by positioning a flat plate of length L ¼ 6D j and height h ¼ 1.5D j (Rego et al 2020) (Fig. 11).…”

Section: Jet Installation Noisementioning

confidence: 99%

“…In order to verify the validity of the model for a jet installation noise application, the results from the numerical simulations are compared with experimental data by Rego et al (2021) in terms of SPL spectra versus Strouhal number (St ¼ f × D j =U j ). The data are obtained for a fine-resolution computational grid (Rego et al 2020). The spectra are obtained for a jet with acoustic Mach number M a ¼ 0.5, an observer distance of 100D j , and polar angle θ ¼ 90°(y-direction, normal to the jet axis) on the reflected side (negative y) of the plate for a constant-frequency band of 100 Hz.…”

Section: Jet Installation Noisementioning

confidence: 99%

Applications of the Multilayer Porous Medium Modeling Approach for Noise Mitigation

et al. 2021

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Porous materials have been widely investigated as a mean for noise reduction. Numerical simulations can be used to investigate the physical mechanisms responsible for noise reduction; however, a correct modeling of the porous medium through an equivalent fluid model is essential to minimize the computational costs. This paper reports a detailed review of a few applications of the equivalent fluid model based on a three-layer approach, a method that is particularly useful to account for the variation of porous material thickness in aerospace applications. The multilayer approach has been applied in three relevant aerodynamic noise issues: leading-edge impingement noise, turbulent boundary-layer trailing-edge noise, and jet installation noise. Comparison with experiments is used to validate the simulation approach.

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“…From an analytical and numerical standpoint, a lot of work has been done on this problem [10][11][12][13][14][15]. The discontinuity in the solid surface boundary condition can be treated formally using the Wiener-Hopf technique for a flat plate that is doubly infinite in the spanwise direction and lies parallel to the level curves of the streamwise mean flow.…”

Section: Introductionmentioning

confidence: 99%

Assessment of Optimization Methods for Aeroacoustic Prediction of Trailing-Edge Interaction Noise in Axisymmetric Jets

Stirrat¹,

Afsar²,

Minisci³

2021

Mathematics

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Our concern in this paper is in the fine-tuning of the arbitrary parameters within the upstream turbulence structure for the acoustic spectrum of a rapid-distortion theory (RDT)-based model of trailing-edge noise. RDT models are based on an appropriate asymptotic limit of the Linearized Euler Equations and apply when the interaction time of the turbulence with the surface edge discontinuity is small compared to the eddy turnover time. When an arbitrary transversely sheared jet mean flow convects a finite region of nonhomogeneous turbulence, the acoustic spectrum of the pressure field scattered by the trailing-edge depends on (among other things) the upstream turbulence via the Fourier transform of the correlation function, R22 (where subscript 2 refers to a co-ordinate surface normal to the plate). We show that the length and time scale parameters that govern the spatial and temporal de-correlation of R22 can be found using formal optimization methods to avoid any uncertainty in their selection by hand-tuning. We assess various optimization methods that are broadly categorized into an ‘evolutionary’ and ‘non-evolutionary’ paradigm. That is, we optimize the acoustic spectrum using the Multi-Start algorithm, Particle Swarm Optimization and the Multi-Population Adaptive Inflationary Differential Evolution Algorithm. The optimization is based upon different objective functions for the acoustic spectrum and/or turbulence structure. We show that this approach, while resulting in the total modest increase in computation time (on average 2 h), gives excellent prediction over most frequencies (within 2–4 dB) where the trailing-edge noise associated amplification in sound exists.

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Jet-installation noise and near-field characteristics of jet–surface interaction

Cited by 35 publications

References 50 publications

An experimental investigation into model-scale installed jet–pylon–wing noise

An experimental investigation into model-scale installed jet–pylon–wing noise

Applications of the Multilayer Porous Medium Modeling Approach for Noise Mitigation

Assessment of Optimization Methods for Aeroacoustic Prediction of Trailing-Edge Interaction Noise in Axisymmetric Jets

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