Lin, YujingWang, JianSavill, Mark2020-08-142020-08-142020-07-06Lin Y, Wang J, Savill M. (2020) Embedded large eddy simulation of transitional flow over NACA0012 aerofoil. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Volume 235, Issue 2, February 2021, pp.189-2040954-4100https://doi.org/10.1177/0954410020939797https://dspace.lib.cranfield.ac.uk/handle/1826/15686An accurate computation of near-field unsteady turbulent flow around aerofoil is of outstanding importance for aerofoil trailing edge noise source prediction, which is a representative of main contributor to airframe noise and fan noise in modern commercial aircraft. In this study, an embedded large eddy simulation (ELES) is fully implemented in a separation-induced transitional flow over NACA0012 aerofoil at a moderate Reynolds number. It aims to evaluate the performance of the ELES method in aerodynamics simulation for wall-bounded aerospace flow in terms of accuracy, computational cost and complexity of implementation. Some good practice is presented including the special treatments at RANS-LES interface to provide more realistic turbulence generation in LES inflow. A comprehensive validation of the ELES results is performed by comparing with the experimental data and the wall-resolved large eddy simulation results. It is concluded that the ELES method could provide sufficient accuracy in the transitional flow simulations around aerofoil. It is proved to be a promising alternative to the pure LES for industrial flow applications involving wall boundary layer due to its significant computational efficiencyenAttribution-NonCommercial 4.0 Internationalhttp://creativecommons.org/licenses/by-nc/4.0/RANS-LES interfaceairframe noisecomputational aeroacoustics,computational aerodynamicsEmbedded large eddy simulationArticle