倾转旋翼机过渡状态飞行速度对气动性能的影响  

Influence of flight speed in transition state on aerodynamic performance of tiltrotor aircraft

作　　者：史金帅 方昕卓异 张夏阳 赵国庆[1] 王博[1] SHI Jinshuai;FANG Xinzhuoyi;ZHANG Xiayang;ZHAO Guoqing;WANG Bo(National Key Laboratory of Rotorcraft Aeromechanics,NUAA,Nanjing 210016,China)

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,江苏南京210016

出　　处：《飞行力学》2023年第2期1-6,共6页Flight Dynamics

基　　金：国家自然科学基金资助(11872211,12102186);江苏省自然科学基金资助(BK20200433)。

摘　　要：针对倾转半机翼类型的倾转旋翼机,采用计算流体力学方法建立过渡状态的数值计算模型,用于其气动特性计算与分析,研究前飞速度对倾转旋翼机过渡状态气动性能的影响。首先,基于动量源方法建立旋翼气动分析模型,对孤立旋翼进行动压分布计算并与试验结果进行对比,验证建立的动量源方法的有效性;然后,建立全机的气动干扰数值计算模型,对机身采用非结构化网格进行划分;最后,分析过渡状态主要部件竖直方向力及倾转段机翼气动性能随前飞速度的变化规律。结果表明:随倾转角增大,倾转段机翼的升阻比减小明显;在小倾转角度下,虽然倾转段机翼发生了失速,但由于其迎风面积增大且在升力方向上具有一定的投影面积,其升力不会迅速减小。In this paper,the computational fluid dynamics method was used to establish the numerical calculation model of the transition state for the tiltrotor aircraft with tilting half wing,which was used for the calculation and analysis of its aerodynamic characteristics to study the influence of forward flight speed on the aerodynamic performance of the transition state of the tiltrotor aircraft.Firstly,the rotor aerodynamic analysis model was established based on momentum source method and the dynamic pressure distribution of isolated rotor was calculated and compared with the experimental results to verify the validity of the momentum source method.Then,the aerodynamic interference numerical calculation model of the whole aircraft was established,and the fuselage was divided by unstructured grid.Finally,the variation laws of the vertical force of the main components in the transition state and the aerodynamic performance of the tilting wing with the forward flight speed were analyzed.The results show that with the increase of tilting angle,the lift-drag ratio of tilting wing decreases obviously.At the small tilting angle,although the tilting wing has stalled,its lift will not decrease rapidly due to the increase in the windward area and the certain projection area in the lift direction.

关 键 词：倾转半机翼 计算流体力学 动量源方法 过渡状态 前飞速度 

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]