  This contribution relates to the simulation of the flow around the tip of a
helicopter rotor blade in hovering flight conditions. We here propose a new
methodology of framework adaptation, using a comprehensive rotor code and
high-fidelity numerical simulations. We construct an equivalent fixed-wing
configuration from a rotating blade, in which centrifugal and Coriolis forces
are neglected. The effect of this approximation on the solution is analysed.
The method is validated by a detailed comparison with wind tunnel data from the
literature, concerning aerodynamic properties and tip vortex roll-up. This
validation also includes variations of the pitch angle and rotational speed, up
to transonic tip velocities. Compared to previously published methods of
framework adaptation, the new hybrid method is found to reproduce more
accurately the flow around a rotating blade tip.
