前缘缝翼构型平尾直升机气动特性分析  

Aerodynamic Characteristics of Helicopter with Leading-Edge Slatted Horizontal Tail

作　　者：王鑫磊 李生伟 林长亮 WANG Xinlei;LI Shengwei;LIN Changliang(Harbin Hafei Aviation Industry Co.,Ltd.,Aircraft Design Institute,Harbin,150066,China)

机构地区：[1]哈尔滨哈飞航空工业有限责任公司飞机设计所,哈尔滨150066

出　　处：《南京航空航天大学学报》2020年第2期288-293,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：使用数值模拟方法研究了前缘缝翼翼型气动特性,并将该前缘缝翼翼型应用于直升机平尾,分析了该直升机全机气动特性,最后通过风洞试验对数值模拟结果进行验证。结果表明,前缘缝翼构型平尾能有效改善直升机的纵向静稳定性。Aerodynamic characteristics of the slatted airfoil are investigated by using numerical simulation techniques. The slatted airfoil to a helicopters horizontal tail is applied. The aerodynamic characteristics of the whole helicopter are calculated and analyzed. Then wind tunnel tests are conducted to validate the simulation results. The results show that the horizontal tail with a leading-edge slat can effectively improve the longitudinal static stability of the helicopter.

关 键 词：直升机 前缘缝翼 平尾 风洞试验 纵向静稳定性 

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]