翼型亚音速风洞实验研究  

Study on Experiment of Airfoil Profile in Subsonic Wind Tunnel

作　　者：廉大超 李仁府[2] 

机构地区：[1]华中科技大学中欧清洁与可再生能源学院,湖北武汉430074 [2]华中科技大学航空航天研究中心,湖北武汉430074

出　　处：《能源与节能》2017年第10期174-175,共2页Energy and Energy Conservation

摘　　要：翼型的空气动力学特性影响着风力发电机的性能和载荷。通过压力传感器在亚音速风洞中对NACA64418进行了稳态与动态俯仰的实验研究。结果显示,随着攻角的增加,稳定情况下的升力系数由于失速的原因在攻角超过一定值后不再增加,但是对于俯仰的非稳态情况下的升力系数在相同的攻角下可以达到更大值,并且在非稳态下,升力系数与攻角的关系曲线呈现出逆时针方向的迟滞环。The aerodynamic characteristics of airfoil profile affect the performance and loading of a wind turbine. This paper carried out experimental research on the steady state and dynamic state pitching of NACA64418 in the subsonic wind tunnel by the pressure sensor. The results showed that with the increase in angle of attack, lift coefficient in the steady condition stoped increasing due to stalling while reached higher values in the unsteady（pitching） case for the same angels of attack. And curves on relations between lift coefficient and angle of attack presented a counterclockwise hysteresis loop in the unsteady（pitching） case.

关 键 词：翼型 风洞实验 压力传感器 升力系数 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]