悬停旋翼桨叶表面压力测量方法  

Surface Pressure Measurement Technology of Hovering Rotor Blade

作　　者：廖会生 黄建萍[1] 李新民[1] 陈卫星[1] 江露生 LIAO Huisheng;HUANG Jianping;LI Xinmin;CHEN Weixing;JIANG Lusheng(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2022年第2期43-47,共5页Helicopter Technique

摘　　要：使用桨叶表面布置毛细管的方式,对4.2 m直径直升机旋翼模型悬停试验中的桨叶表面压力进行测量,获得大量试验数据;同时采用数值计算的方式消除离心力对试验数据的影响;最终通过理论计算(CFD)与试验数据的对比分析,验证了理论计算的有效性,确定毛细管测桨叶表面压力的方式稳定可靠。With the method of capillary arrangement on the surface of the blade,the surface pressure of rotor blade in hovering test was measured,which helicopter rotor model was 4.2 meter diameter.A lot of experimental data were obtained.Then the influence of centrifugal force on the test data was eliminated by numerical calculation.Finally,by validating the theoretical calculation and experimental data,the way to determine the pressure on the surface of the measuring blade was stable and reliable.

关 键 词：旋翼 悬停试验 表面压力 毛细管 CFD 

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]