旋翼翼型动态风洞试验技术研究  

Research on dynamic wind tunnel test technology of rotor airfoil

作　　者：张卫国 李国强 李栋[1] 车兵辉[3] 顾艺[3] 吴霖鑫[3] ZHANG Weiguo;LI Guoqiang;LI Dong;CHE Binghui;GU Yi;WU Linxin(School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]国防科技大学空天科学学院,长沙410073 [3]中国空气动力研究与发展中心低速空气动力研究所,绵阳621000

出　　处：《实验流体力学》2023年第2期78-93,共16页Journal of Experiments in Fluid Mechanics

基　　金：预研专用技术项目(30103010304);预研共用技术项目(50906030601);预研综合研究项目(JK20211A020092)。

摘　　要：旋翼翼型的设计优化及性能确定亟须建立并发展翼型动态风洞试验技术。通过动力学仿真与结构优化设计,基于FL–11低速风洞研制出旋翼翼型两自由度动态试验装置,可实现俯仰/沉浮单自由或两自由度耦合运动,最高振荡频率达到5 Hz;基于FL–20连续式跨声速风洞研制出旋翼翼型高频高速动态试验装置,最高振荡频率达到17 Hz,试验最高雷诺数为5×106,模拟参数包线满足真实直升机参数要求;基于FL–14低速风洞研制出大尺度旋翼翼型动态试验装置,翼型模型弦长为800 mm,试验最高雷诺数达到4×106。完善了旋翼翼型动态试验精准测试相关技术,并开展了验证性试验,试验数据规律合理、量值可靠,表明试验系统及相关测试技术具有较高的可靠性,可为旋翼翼型动态气动特性试验评估提供重要的设备平台和技术支撑。It is urgent to establish and develop the dynamic wind tunnel test technology for rotor airfoil design optimization and performance determination.Through dynamic simulation and structural optimization design,based on the FL–11 low-speed wind tunnel,a two degree of freedom dynamic test device for rotor airfoil is developed.It can not only complete the single degree of freedom dynamic motion of pitch and plunge,but also realize the coupling operation of pitch/plunge,with the highest oscillation frequency of 5 Hz.Based on the FL–20 continuous transonic wind tunnel,a set of high-frequency and high-speed oscillation test device for rotor airfoil is developed,with the maximum pitch oscillation frequency exceeding 17 Hz and the maximum test Reynolds number exceeding 5×106.The simulated parameter envelope meets the parameter requirements of the real helicopter.A large-scale rotor airfoil dynamic test device is developed based on the FL–14 low-speed wind tunnel,with the airfoil model chord length of 800 mm and the maximum test Reynolds number of 4×106.The accurate measuring and testing technique of the rotor airfoil dynamic test is developed,and the verification test is carried out.The results show that the dynamic test data of the rotor airfoil are reasonable and reliable,which indicates that the test system and related test technology have high reliability.It can provide important technical support for the research of rotor airfoil dynamic stall.

关 键 词：旋翼 翼型 动态 风洞试验 沉浮振荡 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程] V211.752