尾梁边条对直升机气动性能影响试验研究

Experimental Study on Influence of Tail Boom Strake on Helicopter Aerodynamic Performance

为克服旋翼产生的反扭矩,目前直升机上主要采用单旋翼带尾桨、双旋翼等布局方案,同时发展了尾梁环量控制及尾梁边条技术。本文应用旋翼/机身组合模型风洞试验方法,探究了尾梁边条对直升机悬停及前飞性能的影响。重点研究了悬停及不同前飞速度下,不同长度和不同安装角度尾梁边条对直升机气动性能的影响。试验结果表明,悬停状态尾梁边条可通过提供侧向力来增加机身扭矩,能够帮助尾桨卸载从而减少尾桨功率消耗。而前飞状态尾梁边条对直升机气动性能基本没有影响。

In order to overcome the counter-torque caused by the rotor,the helicopter mainly adopts the single-rotor with tail rotor and double-rotor.At the same time,the technology of tail boom circulation control and tail boom strake has been developed.Rotor/fuselage model wind tunnel test was conducted to investigate the effect of the tail boom strake on the performance of helicopter hovering and forward flight.Particularly,focus on the influence of tail boom strakes with different length and installation angles on aerodynamic performance of the helicopter in hover and forward flight.The test results show that the tail boom strake can provide lateral force and increasing the fuselage torque in hovering,which can help tail rotor offload and reduce the power consumption of the tail rotor.In the forward flight,the tail boom strake has no effect on the aerodynamic performance of helicopter.