抛物线后掠桨尖旋翼悬停气动特性试验及理论分析研究  

Theoretical and Experimental Research on the Aerodynamic Characteristics of the Rotor with the Parabola Sweepback Blade-tip in Hover

作　　者：林永峰[1] 陈平剑[1] 招启军[2] 

机构地区：[1]中国直升机设计研究所,景德镇333001 [2]南京航空航天大学,南京210016

出　　处：《直升机技术》2008年第3期69-73,共5页Helicopter Technique

摘　　要：对一种新型桨尖旋翼开展了悬停状态气动特性的试验和理论分析研究。该旋翼桨叶截面选择OA翼型配置,桨尖为抛物线后掠加下反形式。首先,在旋翼台上测量了该旋翼在不同总距条件下的桨叶表面压强分布,并与数值计算的结果进行了对比。为进一步分析旋翼桨尖形式对悬停气动特性的影响,本文还计算了带不同下反角桨尖形式旋翼在相同工作状态下的桨叶表面压力分布。综合试验及理论分析结果,得到了一些有意义的结论。The theoretical and experimental researches on the aerodynamic characteristics of the rotor with advanced blade tip-shape in hover were conducted.The shape of the blade-tip is Parabola sweepback and anhedral,and the blade airfoil configure was composed of OA type airfoil in different spanwise location respectively.The coefficients of the surface pressure in several blade sections under the condition of different collective angles were measured on the model rotor test rig.In order to investigate the effect of the rotor blade-tip on its aerodynamic characteristic in hover,the surface pressure distribution and the performance of the rotor with different anhedral blade-tip were calculated.Then the numerical results were compared with the experimental results,and the some meaningful conclusions about the influence of the blade-tip shape on the aerodynamic performance in hover were obtained.

关 键 词：直升机 旋翼 悬停 气动特性 气动试验 新型桨尖 

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]