共轴高速直升机反流区翼型设计及减阻机理  

Design of coaxial high-speed helicopter airfoil in reverse flow region and its drag reduction mechanism

作　　者：王雪鹤 柴春硕 邢世龙 樊枫[1] 黄水林[1] WANG Xuehe;CHAI Chunshuo;XING Shilong;FAN Feng;HUANG Shuilin(China Helicopter Research and Development Institute,Jingdezhen 333000,China)

机构地区：[1]中国直升机设计研究所,景德镇333000

出　　处：《航空学报》2024年第9期287-302,共16页Acta Aeronautica et Astronautica Sinica

基　　金：共用技术项目(50906010501)。

摘　　要：高速化是未来直升机的发展趋势之一。针对共轴高速直升机旋翼大反流区特点,开展了反流区翼型设计研究。首先分析了旋翼根部双钝头翼型在高速飞行状态下的绕流特点和减阻机理,然后针对旋翼反流区的工作环境,提出了一种“吸力面气动前缘半径大、中后部平坦”的双钝头翼型设计思路。相比于标准椭圆翼型,该翼型改善了顺/反流状态流动分离问题,在维持顺流状态低阻特性的同时,反流状态马赫数0.1减阻可达10%以上。以该翼型为基准,开展考虑吸力面流动特征的混合反设计/优化设计。优化翼型维持了反流状态的低阻特性,且顺流状态升阻特性显著提升。Higher speed is the development tendency of helicopters in the future.Considering the wide region reverse flow of coaxial high-speed helicopters,a design of the airfoil in reverse flow region is proposed.Firstly,the flow char-acteristics surrounding the blunt trailing edge airfoil and the drag reduction mechanism deployed in the root of the rotor in high-speed forward flight are analyzed.Then,a blunt trailing edge airfoil characterized by large radius in the leading edge and smooth in the middle and rear parts of the suction surface is developed,in consideration of the reverse flow environment of the rotor.Compared with the standard elliptic airfoil,the modified airfoil improves the flow separation in both reverse flow and forward flow,with the drag coefficient decreasing more than 10%at Mach number 0.1 in the re-verse flow.Based on the modified airfoil,airfoil hybrid inverse design and design optimization are carried out consider-ing the flow characteristics in the suction surface.Results indicate that the optimized airfoil maintains low drag coeffi-cient in the reverse flow,and the lift-drag characteristic is promoted in the forward flow observably.

关 键 词：共轴 高速直升机 翼型设计 减阻 流动分离 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]