直升机动态失速研究  

Helicopter Dynamic Stall Study

作　　者：陈文轩[1] 

机构地区：[1]中国直升机设计研究所,景德镇333001

出　　处：《直升机技术》2008年第3期4-18,共15页Helicopter Technique

摘　　要：本文简要介绍了旋翼和翼型的动态失速特性、动态失速主动和被动控制、旋翼综合法预测使用的一些动态失速模拟方法。UH-60A直升机飞行试验11029飞行是一个典型的旋翼动态失速实例,表演出旋翼后行桨叶上出现高攻角引起的动态失速,而前行桨叶上则出现因为激波诱导前缘分离引起的动态失速。翼型的动态失速特性方面介绍了典型的动态失速迟滞回线(攻角正弦变化和锯齿变化)、缩减频率和雷诺数对翼型动态失速特性的影响等。动态失速主动控制介绍可动前缘翼型的情况,被动控制则是使用前缘涡发生器的情况。This paper describes rotor and airfoil dynamic stall characteristics,dynamic stall active and Passive Control,and dynamic stall numerical simulation in rotor comprehensive analysis.UH-60A helicopter 11029 flight is a representative example of rotor dynamic stall.The rotor blades can encounter dynamic stall on the retreating blade because of high angle of attack,and on the advancing blade because of shock induced leading-edge separation.On airfoil dynamic stall characteristics,shows typical lift,drag-and pitching moment hysteresis loops with sin-wave and saw-tooth incidence variation,and the influence of reduce frequency and Reynolds number on airfoil dynamic stall characteristics.describes the airfoil with Nose-Droop Control dynamic stall active Control,and the airfoil with Leading Edge VOrtex Generators on dynamic stall Passive Control.

关 键 词：动态失速 直升机 旋翼 翼型 

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]