This paper describes the implementation and linearization of a state-space free-vortex wake model with a near-wake vortex lattice model as applied to a helicopter rotor. Following a detailed mathematical description, the wake model is implemented for a UH-60-like rotor and tested in multiple flight conditions including hover, forward flight, and vortex ring state (VRS), and for simple control inputs. The model is verified against a Viscous Vortex Particle Method (VVPM) and accuracy improvements with respect to a state-space free-vortex wake model with tip vortex dynamics only are assessed. Periodic solutions to the wake model are found by time marching the coupled rotor and vortex wake dynamics for the operating conditions mentioned above. Next, linearized harmonic decomposition models are obtained and validated against nonlinear simulations, and linearized models are obtained via system identification. Order reduction methods are explored to guide the development of linearized wake models that provide increased runtime performance compared to the nonlinear and linearized harmonic decomposition wake models while guaranteeing satisfactory prediction of the periodic response of the wake.