Turbulent Boundary Layer in a 3-Element High-Lift Wing: Coherent Structures Identification

A large eddy simulation (LES) of the flow past a 30P30N high-lift three-element wing is performed at the angle of attack \(AoA = 9^\circ \) and a Reynolds number of \(Re = 750,000\) , based on the nested chord. Results are validated against experimental data available in the literature, proving their reliability. The present work is focused on the boundary layer development along the main suction side, including the analysis of the evolution of the thickness, the friction Reynolds number, the shape factor and the Clauser pressure-gradient parameter, as well as the Reynolds stresses at given chord locations. Finally, a proper orthogonal decomposition (POD) is performed, which allows visualizing the main turbulent coherent structures present in a turbulent boundary layer.