共轴式直升机桨毂阻力特性与减阻试验  

Drag Characteristics and Reduction Test for Hub of Coaxial-rotor Helicopter

作　　者：龙海斌[1] 吴裕平[1] LONG Haibin;WU Yuping(General Configuration and Aerodynamic Design Department,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所总体气动研究室

出　　处：《航空工程进展》2020年第1期103-108,131,共7页Advances in Aeronautical Science and Engineering

摘　　要：共轴式直升机桨毂阻力占全机废阻的50%以上,因此有必要对桨毂阻力特性和减阻设计进行研究。通过对某共轴式直升机桨毂模型、减阻方案及减阻方案加装涡流发生器进行风洞试验,研究轴式直升机桨毂的阻力特性,验证减阻方案及减阻方案加装涡流发生器的减阻效果。结果表明:桨毂支臂方位角、转速和攻角变化对桨毂及其减阻方案的阻力影响很小;上下桨毂整流罩与中间轴整流罩之间的缝隙对阻力影响比较大;减阻方案可以降低约33%的桨毂阻力,而加装涡流发生器的减阻效果并不明显。The drag of coaxial helicopter hub accounts is more than 50%of the total helicopter's waste drag,so it is necessary to research the drag characteristics and reduction design of the hub.Wind tunnel test is carried out for a coaxial helicopter hub model,drag reduction scheme and drag reduction scheme with vortex generator.The drag characteristics of coaxial helicopter hub is researched.The drag reduction effect of the drag reduction scheme and drag reduction scheme with vortex generator are verified.The results show that the azimuth,rotation speed and attack angle have little influence on the drag of hub and its drag reduction scheme,the gap between the upper and lower hub fairings and the shaft fairing has a relatively large impact on drag,the drag reduction scheme can reduce the drag by about 33%,and the drag effect of the vortex generator is not obvious.

关 键 词：共轴式直升机 桨毂 阻力 减阻 涡流发生器 风洞试验 

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]