Snel失速模型在旋翼非线性挥舞运动中的应用  

The Application of Snel Dynamic Stall Model in Nonlinear Flap Motion

作　　者：刘洁[1] 陈蕾[1] 张峰[1] 

机构地区：[1]空军航空大学,吉林长春130022

出　　处：《直升机技术》2015年第3期1-5,10,共6页Helicopter Technique

基　　金：吉林省科技发展计划项目(201403007ZG)

摘　　要：首先通过对旋翼桨叶叶素的受力分析,建立了适用于大入流角和大挥舞角的非线性旋翼桨叶挥舞方程。为了使所建立的挥舞方程具有更好的通用性,首次将Snel失速模型应用于直升机旋翼失速状态下升力系数的确定问题,并通过对特定翼型进行仿真试验,验证了Snel失速模型在旋翼问题研究中的有效性。试验表明该模型具有很好的准确性,且由于该模型中不含任何试验参数,实用性强。In this paper, the nonlinear flapping equation for the large inflow angles and flap angles was established by analyzing the aerodynamics of the blade elements. In order to get a more general flap equation, the Snel stall model was first applied to determine the lift coefficient of helicopter rotor. What＇ s more, a simulation experiment for specific airfoils was conducted to verify the effectiveness of the Snel stall model in field of the helicopter. The result showed that the model contains no parameters compared with other stall model, which was more convenient for practical application, and it also showed good accuracy and strong praccability.

关 键 词：旋翼桨叶 挥舞运动 非线性 Snel失速模型 

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]