基于CFD方法的直升机旋翼/尾桨非定常气动干扰计算  

Calculations of unsteady aerodynamic interaction between main-rotor and tail-rotor of helicopters based on CFD method

作　　者：樊枫[1] 徐国华[1] 史勇杰[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210016

出　　处：《航空动力学报》2014年第11期2633-2642,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(11302103);航空科学基金(20135752055)

摘　　要：采用CFD方法针对直升机旋翼/尾桨气动干扰问题进行了数值计算研究.建立了一个适用于旋翼/尾桨干扰气动力计算的方法.在该方法中,控制方程采用三维非定常雷诺平均Navier-Stokes(RANS)方程,网格系统使用嵌套网格技术以计及旋翼和尾桨的相对运动.基于所建立的方法,分别计算研究了悬停状态、低速前飞状态以及巡航平飞状态时干扰状态的旋翼和尾桨气动力,并深入分析了尾桨旋转方向对干扰特性的影响.计算结果表明:旋翼对尾桨的气动干扰在各计算状态都存在,且干扰影响不总是负面的,这取决于飞行状态;而尾桨对旋翼的干扰作用则在悬停状态时较为明显,但在前飞状态时可忽略不计;尾桨旋转方向对尾桨气动力的影响较大,合理地选择尾桨的旋转方向可以改善其气动特性.Numerical calculation research was performed for helicopter main-rotor/tailrotor interaction by using the CFD method.A computational method was established for aerodynamic interactions of main-rotor/tail-rotor configuration,wherein the three-dimensional unsteady Reynolds-averaged Navier-Stokes（RANS）equations were used as the control equations,and overset grid technique was employed to simulate the relative motion between the main-rotor and tail-rotor.Based on the developed method,the aerodynamic characteristics of main-rotor/tail rotor interaction in hover,low-speed forward flight and cruising state were calculated,and the influence of the tail-rotor rotation direction on the interaction characteristics was analyzed.The results indicate that the interference influence of main-rotor on tailrotor is obvious in all calculation states,but not always negative,depending on the flight condition.The interference influence of tail-rotor on main-rotor is relatively obvious in hover,but negligible in forward flight condition.In addition,the tail-rotor rotation direction has a significant effect on the aerodynamic force of tail-rotor,so reasonable selection of the tailrotor rotation direction can improve the aerodynamics of tail-rotor.

关 键 词：旋翼 尾桨 气动干扰 非定常载荷 直升机 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]