Abstract: The aerodynamic performance of the rotor with a China Laboratory of Rotorcraft（CLOR）blade-tip in hover is researched through a rotor test rig test and numerical simulation. For the purpose of comparison, three types of model rotors have been designed, i.e., the reference rectangular platform blade, constant swept blade-tip blade and unconventional aerodynamic shape rotor with a CLOR blade-tip. The lift and torque on the three rotors at different rotation speeds and pitch angles are measured. Numerical simulation is carried out with a hybrid computational fluid dynamics（CFD）method for solving the rotor flowfield based on a Navier-Stokes solver, a fullpotential solver and free wake analysis. The computational results show good agreement with the test results. By means of the present method, the aerodynamic characteristics of a rotor under conditions of higher speed rotation, which are very difficult to obtain experimentally on the rotor test rig, are simulated. Finally, based upon the test and numerical results, comparisons of aerodynamic performance between a rotor with CLOR and rotors with rectangular and constant swept blade-tip have been made, as a result, certain conclusions about the mechanism of the effect of unconventional aerodynamic shape blade-tip on the rotor aerodynamic characteristics are obtained and the advantages of good aerodynamic performance of the rotor with a CLOR blade-tip in hover are initially demonstrated.

Key words: aerodynamic performance, rotors, blade-tip with a new shape, helicopter, numerical simulation