摘要
为了研究后缘旋转圆柱的控制效果,采用数值仿真方法对NACA4415翼型后缘圆柱旋转气动特性进行了仿真,分析了后缘旋转圆柱对翼型气动特性的控制效果,并揭示其流动机理。结果表明,圆柱旋转将使模型升力系数、升阻比、最大升力系数增加,俯仰力矩系数减小,且随着转速比的增大,气动力的变化规律更为显著,但变化幅度逐渐减小。以上气动特性的变化主要是后缘圆柱旋转对上翼面气流的引射作用和对下翼面的阻挡作用造成的。与前缘圆柱旋转的控制方式相比,后缘圆柱旋转控制具有显著增大翼载和实现俯仰控制等优点,具有更为广阔的应用前景。
In order to study the control effects of the rotating cylinder in trailing edge, numerical simulations are conducted with the NACA4415 airfoil with rotating cylinders in the trailing. The effects of the rotating cylinder in trai- ling edge on airfoil aerodynamics characteristic were analyzed and the flow mechanism was revealed. The results show that compared with the airfoil, the drag coefficient, cruise lift coefficient and maximum lift coefficient of the rotating cylinders model increase and the pitching moment coefficient decrease. The rotating cylinder control in trailing edge can increase the wing loading and control pitching moment, which makes this control method utility.
出处
《计算机仿真》
北大核心
2017年第12期18-21,54,共5页
Computer Simulation
关键词
低速翼型
后缘旋转圆柱
增升
俯仰力矩
数值仿真
Low - speed airfoil
Rotating cylinder in trailing edge
Lift augmentation
Pitching moment
Numerical simulation
