直升机旋翼与机体间气动干扰风洞实验研究  

Wind tunnel experimental study of aerodynamic interactionsbetween a rotor and a body of a co-axial helicopter

作　　者：邓彦敏[1] 胡继忠[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2004年第1期1-4,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：介绍了由风洞实验得到的共轴式直升机在悬停和前飞时旋翼 /机体气动干扰结果 ,并与单旋翼直升机进行了比较 .旋翼对机体的干扰主要表现为 :悬停时机体上产生垂向阻力和俯仰力矩 ;前飞时上述干扰减小 ,但机体的纵向和航向气动特性发生变化 ;分别增大水平尾翼面积和下旋翼桨距 ,旋翼对机体的干扰量增大 ;悬停时 ,机体对旋翼无明显影响 。The results of rotors/fuselage aerodynamic interactions for the coaxial helicopter in hovering and forward flight were presented according wind-tunnel experiment. The presence of the rotor wake creates a significant down load on the fuselage which decreases with increasing advance ratio. The interactions above decreased in forward flight, but yaw moment was generated by fuselage; The interaction of coaxial rotors to fuselage changes when the tail plane area, and lower rotor pitch or advance ratio was changed. The interaction of fuselage to coaxial rotors is different from that of single rotor helicopter, such as: in hovering state, the coaxial helicopter fuselage has no obvious effect on rotors, the fuselage generates beneficial interaction to coaxial rotors when in forward flight and the interaction decreases as the advance ratio increases.

关 键 词：共轴式直升机 旋翼 干扰 前进比 垂向阻力 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]