In the present paper a comparison of two different LES predictions was carried out for the flow around an unswept wing with leading-edge stall. The configuration is associated with the COSTWING initiative in which the flow around a NACA-4415 airfoil is studied experimentally for the high-lift case and beyond. As a first step towards the investigation of separated turbulent flows, simulations based on two different LES codes were performed for a fixed set of parameters defined by a low Reynolds number Re c = 20,000 and a high angle of attack α = 18°. Both are second-order accurate finitevolume methods but differ with respect to the grid configurations applied. The first is written for arbitrary non-orthogonal (colocated) block-structured grids (LESOCC), whereas the second uses a non-uniform Cartesian (staggered) grid arrangement with a special interpolation technique near curvilinear boundaries (MGLET). The predicted results are compared in detail considering the averaged flow field, several important integral parameters, and finally higher-order statistics. At large a very good agreement of both LES data is found. Smaller deviations occurring especially with respect to higher-order moments are discussed and evaluated.