LES of practical aeronautical flows at stall conditions

The present study aims to examine the performance wall-modeled LES in flows over realistic aircraft geometry using the state-of-the-art methodologies for low-dissipation LES and standard equilibrium wall model, particularly for prediction of massive flow separation encountered at high angles of attack. Simulations of two aircraft geometries at high angles of attack are considered: a high lift JAXA standard model (Re_c = 1.93M; AIAA Papers 2010-0684, 2008-0350 by Yokokawa et al.) and the NASA Common Research model (Re_c = 11M; Boyet, CEAS Aero. J., 2018). Wall-modeled LES calculations are conducted using equilibrium wall models and the static-coefficient subgrid-scale eddy-viscosity model of Vreman. Predictions of global forces and surface pressure distributions by two low-dissipation LES codes are shown to be in reasonable agreement with experimental measurements. All calculations presented were performed in less than 120 hours using < 3K Intel CPU cores, demonstrating that wall modeled LES for external aerodynamics is becoming increasingly affordable.