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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第11期1852-1857,共6页
Journal of Aerospace Power
