共轴式双旋翼悬停流场的水洞PIV测量  

PIV measurement of water tunnel for the flow field of a hovering coaxial-rotor

作　　者：于世美[1] 邓彦敏[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《航空动力学报》2007年第11期1852-1857,共6页Journal of Aerospace Power

摘　　要：采用粒子图像测速(PIV)技术,对共轴式双旋翼在悬停状态下的流场进行水洞实验,测量得到旋翼流场的涡量和速度分布,桨尖涡的结构和脱落轨迹等直观整体的图像,研究了共轴式双旋翼悬停流场的气动干扰特性.为了比较,对单旋翼也进行测量.实验结果为直升机的气动计算和合理设计提供了可靠的实验依据.Particle Image Velocimetry （PIV） technique was applied to water tunnel experiment for the flow field of hovering coaxial-rotor. Vortex contours and velocity distribution of the rotor flow fields, configuration and trajectory of the tip vortex were measured. The aerodynamic interference characteristics of hovering coaxial-rotor flow fields were also investigated. A single rotor was also measured for comparison purpose. The experimental results provide reliable reference for aerodynamic calculation and reasonable design of helicopter.

关 键 词：航空 航天推进系统 共轴式直升机 旋翼流场 尾迹 水洞实验 粒子图像测速(PIV) 

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] V211.7