Trailing Edge Noise Modelling of Flow over NACA Airfoils Informed by LES

Abid, Hussain Ali; Markesteijn, Anton P.; Karabasov, Sergey A.

doi:10.2514/6.2021-2233

Cited by 8 publications

(2 citation statements)

References 34 publications

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“…This strategy was then used to develop a new and more accurate model based on Amiet's theory [45][46][47], which considers the frequency dependency and the pressure/velocity gradient spectrum. Through another study, Abid et al [108] developed a number of semi-analytical TE noise simulations of a NACA 0012 airfoil at three AoA and two Reynolds numbers by using the WM-LES [109][110][111][112] approach and a revised turbulence anisotropy model. As a modification, they enhanced the previously published TNO-type model [105] that they created using the XFOIL and RANS flow solutions.…”

Section: Empirical/semi-empirical Approachesmentioning

confidence: 99%

Recent Advances in Airfoil Self-Noise Passive Reduction

Amirsalari,

Rocha

2023

Aerospace

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Airflow-induced noise prediction and reduction is one of the priorities for both the energy and aviation industries. This review paper provides valuable insights into flow-induced noise computation, prediction, and optimization methods with state-of-the-art efforts in passive noise reduction on airfoils, blades, and wings. This review covers the combination of several approaches in this field, including analytical, numerical, empirical, semi-empirical, artificial intelligence, and optimization methods. Under passive noise reduction techniques, leading and trailing edge treatments, porous materials, controlled diffusion airfoils, morphing wings, surface treatments, and other unique geometries that researchers developed are among the design modification methods discussed here. This work highlights the benefits of incorporating multiple techniques to achieve the best results concerning the desired application and design. In addition, this work provides an overview of the advantages and disadvantages of each tool, with a particular emphasis on the possible challenges when implementing them. The methods and techniques discussed herein will help increase the acoustic efficiency of aerial structures, making them a beneficial resource for researchers, engineers, and other professionals working in aviation noise reduction.

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Section: Empirical/semi-empirical Approachesmentioning

confidence: 99%

Recent Advances in Airfoil Self-Noise Passive Reduction

Amirsalari,

Rocha

2023

Aerospace

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“…The solver utilizes a GPU-optimized method for solving the hyperbolic part of the Navier-Stokes equations using the asynchronous time stepping at the optimal CFL number corresponding to a minimum dispersion and dissipation error [17,19]. The CABARET method for jet flow and noise calculations was validated in [20][21][22][23] and for airfoil flows in [24,25].…”

Section: Introductionmentioning

confidence: 99%

Jet Installation Noise Modelling Informed by GPU LES

Abid

Markesteijn

Gryazev

et al. 2022

28th AIAA/CEAS Aeroacoustics 2022 Conference

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Jet installation beneath a wing significantly enhances jet noise at low frequencies, and its physical mechanism must be comprehended to develop efficient noise reduction solutions. A numerical investigation on the jet-installation noise is performed using Wall Modelled Large Eddy Simulation (WMLES) performed using the high-resolution CABARET method accelerated on Graphics Processing Units. To simulate jet installation, a flat plate is put outside of the jet's plume, causing a rise in noise levels due to the scattering of near-field hydrodynamic waves at the trailing edge of the plate. The configuration adopted in this work replicates a series of experiments performed at the University of Bristol, against which the numerical results are validated. The numerical simulation is performed for Mach numbers of 0.5 and 0.9, and the influence of the selected noise reduction technique, i.e., the usage of chevron nozzles in comparison with the baseline round nozzle, on the jet-installation is studied by modelling SMC006 chevron nozzle. The properties of jet-hydrodynamic pressure variations and their effect on nozzle type and Mach number are investigated. Far-field noise spectra from the isolated and installed jet cases, obtained through the Ffowcs-Williams Hawkings method, are compared at different polar angles. In addition, a hybrid semi-analytical hydrodynamic-edge scattering prediction model is implemented following the model of Lyu and Dowling [1] to analyse jet-installation noise, using inputs obtained directly from the LES calculation. The implemented model is found to capture the correct physics at peak jet installation frequencies and can be used as a robust prediction tool for jet-installation noise optimisation in the future.

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Jet Installation Noise Modelling for Round and Chevron Jets

Abid,

Markesteijn,

Karabasov

et al. 2024

Flow Turbulence Combust

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Wall-Modelled Large Eddy Simulations (LES) are conducted using a high-resolution CABARET method, accelerated on Graphics Processing Units (GPUs), for a canonical configuration that includes a flat plate within the linear hydrodynamic region of a single-stream jet. This configuration was previously investigated through experiments at the University of Bristol. The simulations investigate jets at acoustic Mach numbers of 0.5 and 0.9, focusing on two types of nozzle geometries: round and chevron nozzles. These nozzles are scaled-down versions (3:1 scale) of NASA’s SMC000 and SMC006 nozzles. The parameters from the LES, including flow and noise solutions, are validated by comparison with experimental data. Notably, the mean flow velocity and turbulence distribution are compared with NASA’s PIV measurements. Additionally, the near-field and far-field pressure spectra are evaluated in comparison with data from the Bristol experiments. For far-field noise predictions, a range of techniques are employed, ranging from the Ffowcs Williams–Hawkings (FW–H) method in both permeable and impermeable control surface formulations, to the trailing edge scattering model by Lyu and Dowling, which is based on the Amiet trailing edge noise theory. The permeable control surface FW–H solution, incorporating all jet mixing and installation noise sources, is within 2 dB of the experimental data across most frequencies and observer angles for all considered jet cases. Moreover, the impermeable control surface FW–H solution, accounting for some quadrupole noise contributions, proves adequate for accurate noise spectra predictions across all frequencies at larger observer angles. The implemented edge-scattering model successfully captures the mechanism of low-frequency sound amplification, dominant at low frequencies and high observer angles. Furthermore, this mechanism is shown to be effectively consistent for both $$M=0.5$$ M = 0.5 and $$M=0.9$$ M = 0.9 , and for jets from both round and chevron nozzles.

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Trailing Edge Noise Modelling of Flow over NACA Airfoils Informed by LES

Cited by 8 publications

References 34 publications

Recent Advances in Airfoil Self-Noise Passive Reduction

Recent Advances in Airfoil Self-Noise Passive Reduction

Jet Installation Noise Modelling Informed by GPU LES

Jet Installation Noise Modelling for Round and Chevron Jets

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