An overset-mesh approach for large-Eddy simulation of high-Reynolds number aerofoil flow

Abstract

ABSTRACTWall-resolved large-eddy simulations are carried out in order to explore the use of an overset nested-grid approach for computing high-Reynolds number turbulent aerofoil flows. By lowering the computational grid density as the distance from solid surfaces increases, a saving in computing resources may be realised. The configuration consists of a wing section having a NACA0012 aerofoil geometry, at a freestream Mach number of 0.3 and chord-based Reynolds number of , which duplicate experimental conditions. Two angles of attack are considered, namely 0.0 and 9.86. Because of the limited amount of experimental data available at the aerofoil Reynolds number, well-resolved solutions are obtained without employing the nested-grid technique and are then used to validate the overset methodology. All results are obtained with a high-fidelity numerical method, using high-order interpolation to maintain spatial accuracy with the overset systems. A comprehensive, detailed comparison is made between solutions obtained with a single-block grid topology, and those generated on nested overset-mesh systems. The quantities considered, consist of time-mean and fluctuation velocity profiles, as well as turbulent kinetic energy spectra. It is shown that comparable results may be obtained with a resource saving of 52–65% by utilising the nested-grid approach.