In the present study, numerical simulations of the pressure-sensitive paint (PSP) rotor in hover were conducted using a Reynolds-averaged Navier-Stokes computational fluid dynamics (CFD) flow solver based on unstructured mixed meshes. In the simulations, an improved laminar-turbulent transition model gamma - Re-theta t - CF+ was adopted for the prediction of laminar-turbulent onset phenomena involving crossflow-induced transition and flow separation. To capture vortices with high resolution, an improved scheme ESWENO-P was utilized for computing inviscid fluxes on Cartesian meshes. The predicted results such as transition onset locations and rotor aerodynamic performances in terms of thrust coefficient, torque coefficient, and figure of merit were compared with the experimental data. The effects of the fuselage and facility wall on PSP rotor performance in hover were also investigated.