带先进桨尖的模型旋翼悬停噪声计算与试验  

Numerical Calculations and Test Research on Aeroacoustics Characteristics of Model Rotors with Advanced Blade Tip in Hover

作　　者：曹亚雄 樊枫 林永峰 袁明川 

机构地区：[1]中航工业直升机设计研究所,景德镇333001

出　　处：《南京航空航天大学学报》2016年第2期180-185,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为进行旋翼噪声水平对比,在全消声室开展了3副不同下反角桨尖模型旋翼噪声试验研究,完成了悬停状态下不同总距和不同观测点上的噪声测量试验,获得了多组噪声数据。数值计算方面,以RANS方程为主控方程求解旋翼流场气动信息,在获取精确声源信息的基础上,基于FW-H方程进行噪声计算和分析。在相同的状态下,计算结果与试验结果显示出较好的一致性,表明了本文数值方法的准确性。最后,根据试验结果,对比分析了不同下反角桨尖对旋翼气动噪声特性的影响规律。For the comparison of sound level, experimental investigation on the aeroacoustic characteris- tics of three sets of model rotors under different tips with anhedral angles in hover is conducted in the anechoic chamber. The noise information on rotors at distinct collective pitch angles and observation points is collected. In aspect of numerical simulation, RANS control equations are solved to get the de- tailed flow-field aerodynamic information of rotor, and the aeroacoustic information is calculated based on FW-H equation. In the same conditions, test results and simulation results are in good agreement, which validates the feasibility of the presented numerical method. Finally, based upon the test results, comparisons of aeroacoustic characteristics among the model rotors with different blade tips are made.

关 键 词：气动噪声 下反桨尖 悬停试验 数值模拟 旋翼 

分 类 号：V216.5[航空宇航科学与技术—航空宇航推进理论与工程]