中文摘要：

采用数值模拟的方法研究了旋转圆柱对NACA0015翼型气动特性的影响，着重分析了前缘旋转圆柱转速比和缝隙大小对翼型升阻特性的作用规律以及不同安装位置的高速旋转圆柱结合简单襟翼偏转下的翼型气动力特性。结果表明，高速旋转的圆柱代替翼型前缘可以有效地抑制翼型背风区的流动分离，延缓边界层的发展从而改善翼型气动特性。前缘旋转圆柱理想的转速比在4附近，缝隙在2．5mm至1．5mm之间可以满足使用要求。简单襟翼结合前、后缘高速旋转圆柱情况下翼型的气动力特性可以比拟精心设计的多段翼型。旋转圆柱具有增升减阻效果显著，需要主动输入的能量极少等优点，是一种具有良好应用前景的边界层流动控制技术。

英文摘要：

Moving surface boundary layer control technique appears quite promising for en- hancing the airfoils aerodynamics prominently with little energy input. Numerical simulations are conducted on the NACA0015 airfoil with rotating cylinders. The ratio of cylinder surface speed to the freestream speed as well as the gap between the cylinder and the fixed section are analyzed. The results show that the high speed leading-edge rotating cylinder is effective on delaying the flow separation on the upper surface of the airfoil and retarding the boundary-layer development. The proper rotating speed ratio for the cylinder is around 4 and the appropriate gap distance is a- bout 2.5mm to 1.5ram. Moreover, results suggest that, integrated with the high speed leading- edge and trailing-edge rotating cylinders, the aerodynamic performances of the symmetrical airfoil with simple flap can be comparative to those careful designed multi-element airfoils.