倾转旋翼机小速度前飞的尾迹涡演化及其对平尾的影响  

Wakes of Tilt-Rotor Aircraft in Small Forward Velocity Flight and Its Effects on Horizontal Tail

作　　者：朱文庆 仲唯贵[1] 张威[1,2] ZHU Wenqing;ZHONG Weigui;ZHANG Wei(AVIC Helicopter Research and Development Institute,Jingdezheng 333000,China;National Key Laboratory of Rotorcraft Aeromechanics,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]中国直升机设计研究所,景德镇333000 [2]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：《南京航空航天大学学报》2022年第2期203-210,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：采用基于运动嵌套网格的CFD方法计算了倾转旋翼机直升机状态和过渡状态下的流场,研究了在小速度前飞下的尾迹涡演化和其对平尾气动力的影响。直升机状态下,前飞速度≤4 m/s时,旋翼尾迹主要在机翼附近,与机翼干扰形成喷泉效应,但对平尾无影响。随着前飞速度增大,喷泉效应与自由来流的综合作用形成喷泉涡,喷泉涡产生于机翼上表面,呈流向涡形式向下游输运,从平尾上方通过。前飞速度进一步增大(≥16 m/s),产生于桨盘边缘的旋翼尾迹侧缘涡开始增强,从平尾侧边通过,并在平尾附近的流动中占据主导地位。喷泉涡和侧缘涡均在平尾处产生上洗流动,使平尾产生低头力矩。从直升机状态到固定翼状态,旋翼尾迹侧缘涡逐渐减弱,对平尾的影响也减弱。The CFD method with moving overset grid scheme is used to simulate the flow-field of a tilt-rotor aircraft during helicopter mode and conversion mode in small forward velocity flight.The wakes from different flight conditions are investigated and their effects on the horizontal tail are explored.In helicopter mode,when the aircraft is in hover or small forward velocity flight(≤4 m/s),the rotor wakes,which form fountain flow effects due to the presence of wing,focus in the vicinity of wing and have few effects on the horizontal tail.With the increase of forward velocity,a pair of stream-wise vortexes called fountain vortexes,which dominates the flow around the horizontal tail,is formed by the interaction between the fountain flow and the freestream.When the forward velocity is further enlarged(≥16 m/s),the edge vortexes of rotor wakes move downstream and have significant effects on the horizontal tail.The fountain vortexes are generated from the upper surface of wing;the edge vortexes are from the edge of rotor disc.Although their production mechanisms are different,both the fountain vortexes and edge vortexes cause an upwash near the horizontal tail,and therefore a pitch down moment for the aircraft.In addition,the edge vortexes of rotor wakes are weakened and the pitch down moment is reduced,with the flight condition changing from helicopter mode to fixed-wing mode.

关 键 词：倾转旋翼机 旋翼尾迹涡 平尾俯仰力矩 气动干扰 

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]