The intention of the present work is to generate meshes tailored to the boundary layer to improve the flow predictions of wall-modeled large-eddy simulations (WM-LES). To this end, the local reconstruction-method was implemented to measure the boundary layer thickness using the computations of a constant-height grid as a baseline. The NASA Juncture Flow is used as benchmark. WMLES using Alya were conducted for an angle of attack of AoA = 5 0 and Reynolds number based on the crank chord Re c = 2.4 · 10 6 . The errors in the prediction of mean velocity profiles are characterized at two different locations over the aircraft: the upstream region of the fuselage, and the wing-body juncture close to the leading-edge. Better prediction of the flow close to the wall are observed with the tailored mesh with a equilibrium wall-function, especially at the upstream location where the equilibrium hypothesis holds.