Large eddy simulation of flow over NACA4412 airfoil at the critical angle of attack

Abstract

The flow characteristics over NACA4412 airfoil near stall are investigated using large eddy simulation (LES) at the Reynolds number of 1,640,000 based on the chord length (c) and free stream velocity (u_inf). This flow is challenging to simulate because it contains thin turbulent boundary layer, separation near the trailing edge, and wake. Various flow characteristics are presented at the critical angle of attack of 12deg., and the results are compared with those from Wadcocks experiment. Moreover, the flow phenomena at a few more angles of attack before and after stall are presented.