桨叶负扭转对旋翼性能影响的研究  

Study of the Influence on Main Rotor Performance by Different Blade Twist

作　　者：张青竹 张德平 Zhang Qingzhu;Zhang Deping(Harbin Aircraft Industry Group Co.,Ltd.,Harbin 150066,China)

机构地区：[1]航空工业哈尔滨飞机工业集团有限责任公司,黑龙江哈尔滨150066

出　　处：《科学技术创新》2022年第23期11-14,共4页Scientific and Technological Innovation

摘　　要：为研究桨叶负扭转对直升机旋翼性能的影响,本文对桨叶扭转为-10°、-12°、-14°、-16°和-18°的五种旋翼进行悬停、平飞、自转的性能计算。计算表明:在悬停状态、大拉力系数时,桨叶负扭转大的旋翼具有更高的悬停效率;大速度平飞时,旋翼平飞升阻比随桨叶负扭转的增加而增大,旋翼型阻功率随桨叶负扭转的增加而减小;桨叶负扭转小的旋翼具有更好的自转升阻比。另外,桨叶负扭转对旋翼的失速限制影响不明显。To study the influence on main rotor performance by different blade twist,calculated performance of five rotors with-10°、-12°、-14°、-16°and-18°blade twist,at hovering,level flight and autorotation.When hovering with large Ct,rotor with larger blade twist gains better FM;Along with lager blade twist when level flight at high speed,the L/D gets larger and the profile power gets smaller;Main rotor with small blade twist gains better L/D at autorotation.In addition,the stall limit regime is not influenced by blade twist obviously.

关 键 词：直升机 旋翼 负扭转 性能 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]