par Matouk, Rabea ;Degrez, Gérard ;Christophe, Julien
Référence International journal of aeroacoustics, 14, page (1049–1070)
Publication A Paraître, 2015-12-11
Article révisé par les pairs
Résumé : Turbulent flows around airfoils are very challenging to simulate accurately because of thecomplex flow phenomena, including leading-edge boundary layer separation, shear layertransition to turbulent behavior, reattachment and trailing-edge vortex shedding. In this paper, theflow around a CD (Controlled-Diffusion) airfoil is studied at a Reynolds number of 160,000using Large-Eddy Simulations (LES). The in-house hybrid spectral/finite element SFELESsolver [1] is used to solve the flow. The aim of this research is to study the unsteady turbulentboundary layer and to predict the corresponding wall-pressure spectrum which will be used forthe noise predictions, to implement and evaluate the new SGS model proposed recently byG. Ghorbaniasl et al. [2] and to study the influence of the LES sub grid-scale models on theresults. Another goal is to calculate the radiated broadband trailing-edge noise by applyingAmiet’s aeroacoustic theory and its extensions [3, 4] using the wall-pressure spectrum for astation near the trailing edge. The sound pressure level and its directivity are computed for thethree SGS models. The aerodynamics and aeroacoustics results are compared with experimentalresults obtained by Moreau and Roger [5] and Moreau et al. [6] as well as other numerical resultsobtained by Christophe [7] using OpenFoam and Wang et al. [8] using a hybrid finitedifferences/spectral solver. The high variability of the leading edge recirculation bubble size withthe SGS model is found. The predicted noise spectra is found insensitive to the choice of the SGSmodel, the difference does not exceed 2 dB for frequencies of interest (100-2000 Hz). This islinked to the insensitivity of the wall-pressure spectra to the choice of the SGS model.

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