锯齿状桨尖旋翼悬停气动特性试验研究

从仿生学角度出发，结合旋翼空气动力学特点，设计了一种全新的具有后缘锯齿桨尖的模型旋翼。定性分析了锯齿桨尖的桨尖涡，以及对旋翼气动性能、振动特性、气动噪声的影响。在旋臂机上分别对矩形、尖削、后缘锯齿桨尖的模型旋翼进行了悬停气动特性试验。试验结果表明，锯齿桨尖旋翼的悬停效率有显著提高，振动及噪声水平比另两种旋翼有明显降低。试验验证了分割离散桨尖涡思想的正确性和可行性。进一步的试验研究正在开展中。

An experiment of hover performance with new shape blade tip

A zigzag blade tip was designed according to the owl wings. The principle of the zigzag blade tip was qualitatively analyzed. For the purpose of comparison, we designed another model rotor with taped tip blades. The experiment had been done on the whirling beam devices, rectangular blade tip rotor attending the experiments as well. The test data indicated that the rotor hover performance was improved prominently because of the using of the zigzag blade tip. Reduction of vibration and noise was inspiring at the same time. Consequently, the correctness and possibility of the new idea of dividing and scattering blade tip vortex were proved.