Helicopter rotors generate helical vortex systems that emerge at the blade tips, impacting both the aerodynamic and aeroacoustic performance of the rotor. Vortex properties are of significant interest, as previous research indicates they are influenced by the vortex Reynolds number. Studies of blade tip vortices at high Reynolds numbers are challenging for both numerical approaches and full-scale experiments; therefore, the High Pressure Wind Tunnel Göttingen (HDG) is employed. The HDG was used to conduct measurements on a rotor scale model in a hyperbaric environment in order to obtain vortex Reynolds numbers similar to a full-scale helicopter rotor. The results are compared to analytical vortex models to determine vortex characteristics such as position and core size when varying the Reynolds number. The findings demonstrate that the trajectory of the rotor tip vortices changes with the Reynolds number. Forced blade boundary layer transition showed an overall greater effect on the vortex trajectories than changing the Reynolds number in the range studied. Additionally, it is shown that in the range studied, \(2.0 \cdot 10 ^4 \le Re_v \le 15.9 \cdot 10^4\) , the core radius growth with respect to vortex age decreases as the Reynolds number increases.