Computational fluid dynamics predictions of a helicopter in hover remain a challenge due to the tight interaction between the complex wake system and the rotor. This work focuses on model-scale hover predictions using a Reynolds averaged Navier-Stokes model supplemented with an approximate en envelope method transition model. These simulations are performed to evaluate the ability of the model to predict natural laminar-turbulent transition and its impact on rotor performance. The predicted transition locations and rotor figure of merit are compared with experimental measurements obtained from a joint U.S. Army/NASA hover test campaign conducted at NASA Langley Research Center. Figure of merit predictions obtained with and without the transition model align well with experiments with natural and forced transition, respectively. The predicted transition locations are also in good agreement with experiments for most of the thrust conditions. This study suggests that the present modeling approach is reasonably accurate for predicting transition on rotor blades, but also identifies areas for potential improvements.