摘要
在翼型上表面的恢复区内采用修改后的Ｓｔｒａｔｆｏｒｄ理想的压力分布，然后应用Ｗｅｂｅｒ已知压力分布求解翼型外形的理论设计出一套在低雷诺数时的新翼型。本文进行了雷诺数为Ｒｅ＝５．６×１０５时的实验研究．其结果表明，翼型失速攻角α＝３４°，升力系数ｃｙ＝１．８０．用该翼型对带升力面的动力系统进行设计时，可提高系统的工作效率。
The recovery region on the upper surface of the airfoil can be located by using the modification stratford pressure distribution in thesis.Then according to Weber’s theory with given pressure distribution we are able to design a shape of the airfoil at low Reynold numbers.The test results indicate maximum lift coefficient C y =1.80,stall angle of attack α cr =34° for Reynold number Re =5.6×10 5.Using the airfoil to design new power systems with surface lift can raise the work efficiency of the power systems.
出处
《空气动力学学报》
CSCD
北大核心
1998年第3期363-367,共5页
Acta Aerodynamica Sinica
关键词
雷诺数
风力机
翼型
升力系数
实验
Reynold number
wind turbine
airfoil
lift coefficient
