Strong tip vortices generated by hovering rotors contribute to induced aerodynamic losses. Blade-tip jet injection offers a means of modifying the tip-vortex system and the associated aerodynamic loads. In this study, a computational model of a hovering rotor was developed using the multiple reference frame (MRF) approach and validated against the experimental measurements of the Caradonna–Tung rotor. At a representative high-tip-speed condition, the effects of jet velocities equal to one, two, and three times the blade-tip speed, as well as the effect of jet-orifice diameter, were investigated in terms of rotor thrust, torque, and tip-vortex structure. The results indicate that a jet velocity of 200 m/s (twice the blade-tip speed) yields the greatest thrust increase among the investigated jet-velocity cases: thrust increases by 5.43%, accompanied by a 4.17% increase in torque. Increasing the orifice diameter within the investigated range further increases both thrust and torque. Flow-field visualizations suggest that jet-induced momentum injection modifies tip-vortex coherence, wake organization, and local flow structures. These findings demonstrate the potential of distributed blade-tip injection for controlling hovering-rotor aerodynamics while highlighting the accompanying torque penalty.