高速直升机旋翼反流区桨叶剖面翼型气动特性CFD分析  

CFD Analysis on Aerodynamic Characteristics of Blade Profiles in Reverse Flow Region of High Speed Helicopter Rotor

作　　者：袁明川[1] 杨永飞[1] 林永峰[1] 

机构地区：[1]中国直升机设计研究所 直升机旋翼动力学重点实验室,江西景德镇333001

出　　处：《直升机技术》2015年第1期1-5,12,共6页Helicopter Technique

基　　金：863项目-先进直升机技术(课题编号:2012AA112201)

摘　　要：随着直升机飞行速度的提升,旋翼的反流区域逐渐增大。以某直升机旋翼模型为例,利用CFD方法对旋翼反流区桨叶不同剖面翼型的气动特性进行了分析,得到旋翼桨叶不同剖面翼型的气动力、压力系数和周围流场变化情况,对它们的流动机理进行了简单的探究。通过对比分析,得到了反流区桨叶剖面气动特性的一些规律。同时初步研究了翼型后缘钝化处理对改善反流特性的影响。The reverse flow region of rotor expands while the speed of helicopter increases. Taking a helicopter model rotor as example,the aerodynamic characteristics of reverse flow region was researched in CFD simulating method. The simulation obtained aerodynamic forces,pressure coefficients and flow fields of different profiles of the rotor blade,the fluid principle was investigated. The general trends were found for the aerodynamic characteristics of these profiles in reverse flow region after comprehensive comparisons and analysis. Simultaneously,a preliminary research on using blunt trailing edge to improve the aerodynamic characteristics of aerofoil in reverse flow condition has investigated.

关 键 词：高速直升机 反流区 翼型 CFD 后缘钝化 

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]