The goal of this study is to numerically investigate the aerodynamic characteristics of an advanced rotorcraft airfoil. A rotorcraft main rotor in the advancing side encounters high-speed flow, whereas, in the retreating side, the rotor needs to avoid dynamic stall for high-thrust or high-speed-forward maneuvers. Consequently, a high drag-divergence Mach number is preferred for the advancing side, and a high lift with good dynamics stall characteristics is critical for the retreating side. The VR-12 airfoil, which satisfies such challenging conditions, was recently developed and has been successfully applied to advanced helicopters. Therefore, the VR-12 airfoil is chosen in the current numerical study. Unsteady Reynolds averaged Navier-Stokes (URANS) simulation is performed with the Spalart-Allmaras turbulence model. Fully-turbulent flow condition is used. The pressure profiles along with integral quantities, including the aerodynamic lift, drag, and moment, are compared with wind tunnel experiments and CFL3D numerical analysis data. Good agreement was achieved across angles of attack for the airfoil.