后缘调整片对桨叶翼型气动特性的影响  

Influence of Trailing Edge Tab on the AerodynamicCharacteristic of Blade Airfoil

作　　者：谢梅莹 习娟[1] XIE Meiying;XI Juan(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2024年第2期22-25,共4页Helicopter Technique

摘　　要：直升机桨叶失速颤振后更容易引起旋翼操纵载荷的突增,为此提出增加桨叶后缘调整片的方案。以直升机常用桨叶翼型为基准翼型,通过求解雷诺平均Navier-Stokes方程模拟翼型气动特性,离散格式采用二阶迎风格式,湍流模型选择Spalart-Allmaras模型,并通过风洞试验结果验证了计算的准确度。分析了后缘调整片弯折角对翼型升力系数、阻力系数、力矩系数、升阻比等气动特性参数的影响。数值结果表明:随着后缘调整片弯折角的增加,翼型的升力系数和升阻比增加,零升攻角和失速攻角减小;在小攻角范围内,后缘调整片对翼型的阻力系数影响不大;后缘调整片弯折角的增加使得翼型的气动中心和焦点后移,但是会增加翼型的低头力矩。The project of adding the trailing edge tabs to the blade was put forward to solve the problem of strong increase of the control high order load caused by the helicopter blade stall flutter.Taking the common helicopter blade airfoil as reference airfoil,aerodynamic characteristics were simulated by solving Navier-Stokes equations.Discrete scheme adopted second order upwind and turbulence model select Spalart-Allmaras model.Results were validated with wind tunnel test data.The effects of the bending angle on the lift coefficient,drag coefficient,pitching moment coefficient and lift-to-drag ratio were analyzed.Simulation results showed that by the increase of the bending angle of the trailing edge tab,lift coefficient and lift-to-drag ratio increased,zero lift angle of attack and stall angle of attack decreased.In the range of small angle of attack,the trailing edge had little effect on the drag coefficient of the airfoil.Increase of the trailing tab edge could move back the aerodynamic center and focus of airfoil,but increase the nose-down pitch moment.

关 键 词：后缘调整片 弯折角 桨叶 翼型 气动特性 

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]