中文摘要：

通过旋翼台试验和数值模拟方法对具有China Laboratory of Rotorcraft（CLOR）桨尖旋翼的悬停气动性能进行研究。为进行对比研究,共设计完成3副模型旋翼,分别为参考的矩形桨叶、常后掠桨尖的桨叶以及具有CLOR桨尖气动外形的桨叶。在模型旋翼台上进行这3副模型旋翼在不同转速、不同桨叶安装角条件下的旋翼拉力和扭矩测量;数值计算是采用一个基于Narier-Stokes方程/自由尾迹分析/全位势方程的旋翼流场求解的混合计算流体力学（CFD）方法进行的,计算结果与试验结果显示出较好的一致性。在此基础上,数值模拟了在旋翼试验台上很难开展的高速旋转试验状态。最后,根据试验和数值结果,对比分析具有CLOR新型桨尖旋翼与矩形桨尖以及常后掠桨尖旋翼的悬停气动性能,得出关于非常规气动外形桨尖对旋翼气动特性的影响机理,初步体现了CLOR桨尖旋翼具有良好的悬停性能。

英文摘要：

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 aerody namic characteristics are obtained and the advantages of good aerodynamic performance of the rotor with a CLOR blade-tip in hover are initially demonstrated.