With the advancement of computational power and the integration of GPU acceleration into an increasing number of CFD codes, scale resolving simulations (SRS) have garnered increased interest from researchers and design engineers for turbomachinery application. SRS have demonstrated superior accuracy compared to Reynolds-Averaged Navier-Stokes (RANS) simulations in the prediction of vortices and flow separation, enabling a more precise prediction of the stall inception in axial compressors, leading to an enhanced computation of compressor maps. This paper investigates Zonal Large Eddy Simulations (ZLES) a type of SRS, which employ a RANS-type wall model near solid boundaries, applied to a single rotor in an axial compressor. To compare the results, experimental data provided from the Low Speed Research Compressor of the Chair of Turbomachinery and Flight Propulsion of TU Dresden is used, along with results from Wall-Resolved Large Eddy Simulations (WRLES). In this paper, two distinct operating points at reduced rotational speeds were investigated: one emulating a point on the working line and one operating close to the stall point. To gain an initial understanding of the resolved turbulence the instantaneous flow is compared between simulations. In the next step inflow and outflow of the rotor blade passage is assessed by comparing circumferential and time-averaged axial velocities, together with the relative flow angle. For a more in-depth analysis of the flow, velocity distributions, downstream of the rotor blade and at different passage heights were, together with the reduced turbulent kinetic energy, evaluated. To help assessing which simulation closer matches the experiment integral pressure losses are compared. The paper demonstrates good agreement of ZLES with experimental results for both operating points. In conjunction with low computational costs compared to WRLES the conclusion is drawn that ZLES is a feasible tool for the accurate prediction of rotor blade flow.