Embedded large eddy simulation of transitional flow over NACA0012 aerofoil. (February 2021)

• Record Type: Journal Article
• Authors: Lin, Yujing; Wang, Jian; Savill, Mark
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 235:Number 2(2021)
• Page Start: 189
• Page End: 204
• Publication Date: 2021-02
• Subjects: Embedded large eddy simulation -- computational aerodynamics -- computational aeroacoustics -- airframe noise -- RANS-LES interface; Aeronautics -- Periodicals; Astronautics -- Periodicals; Airplanes -- Design and construction -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1177/0954410020939797
• Languages: English
• ISSNs: 0954-4100

Abstract

An 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 efficiency.