Meshing and numerical techniques are investigated to resolve the vortical structures of an S-76 rotor in hover in an efficient manner. The methodology employs a quarter domain Cartesian background mesh with periodic boundary conditions to reduce the computational costs in simulating all four blades of the rotor. Mesh clustering of the background grid is performed where the strong tip vortex is expected, and overset vortex tracking grids are added to further resolve the near-field evolution of the tip vortex. A compressible, structured, overset RANS based solver (OVERTURNS) is used in this study, and simulations were performed for a swept-tapered tip at a tip Mach number of 0.65 and a collective pitch angle of 9.25°. To minimize the numerical error, a fifth-order Compact-Reconstruction Weighted Essentially Non-Oscillatory (CRWENO) is employed. A first-order temporal ac- curate scheme is applied to avoid excessive development of small eddies around the tip vortex and severe breakdown of far rotor wake. For turbulence closure, Spalart-Allmaras one-equation model with the rotational correction terms (SA-R) and Spalart-Allmaras De- layed Detached Eddy Simulation (SA-DDES) with modified parameters are tested. The performance parameters are examined, and the vortical structures are analyzed in detail, such as the tip vortex trajectory, swirl and axial velocity profiles, and Eddy viscosity. It was observed that while the vortex tracking grids, mesh clustering techniques, and use of SA-DDES do not significantly affect the predicted eficiency of the rotor, they vastly improve the quality of the wake structure trailed behind the rotor blades. © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.