Microtab对翼型跨音速抖振始发特性的影响

研究了microtab对翼型跨音速抖振始发特性的影响。采用SST湍流模型对RANS方程进行封闭，以NACA0012翼型为对象，用CFD方法计算了在其后缘附近安装microtab后，翼型的跨音速流场。对比分析了在翼型后缘附近的上表面、下表面单独安装和上下表面对称安装microtab后，对翼型跨音速抖振始发特性的影响，并研究了microtab的高度和弦向安装位置对跨音速抖振边界的控制作用。结果表明：在翼型后缘附近的上表面加装microtab能够提高抖振始发攻角，并且随着microtab高度的增加，抖振始发攻角有增大的趋势。在翼型后缘附近的下表面加装microtab能够提高抖振始发时的升力系数，且抖振始发时的升力系数随着microtab高度的增加而增大。microtab的弦向安装位置的变化对于抖振始发攻角影响较小，但是对抖振始发时的升力系数有明显的影响。   

Effect of Microtab on an Airfoil Transonic Buffet Onset

The effect of microtab on an airfoil transonic buffet onset was investigated. A CFD simulation using Reynolds-averaged Navier–Stokes methods with SST turbulence was conducted to determine the transonic flow around the NACA0012 airfoil with a microtab which is installed perpendicular to the airfoil surface in the vicinity of the trailing edge. The influence of different installing schemes of microtab (a tap is installed on airfoil upper surface, a tap is installed on airfoil lower surface, two taps were symmetrically installed on airfoil upper and lower surfaces) on transonic buffet onset were analyzed and compared. Subsequently, a sensitivity research was conducted to determine the effect of the height and chord wise position of the microtab on transonic buffet onset. The results indicate that the improvement of the buffet onset angle is achieved by installing the microtab on the upper (suction) surface of the airfoil. Furthermore, the buffet onset angle of attack tends to be improved as the height of microtab increases. However, the improvement of the lift coefficient at buffet onset is attained by installing the microtab on the lower (pressure) surface of the airfoil. Similarly, the lift coefficient at buffet onset can be improved with the increasing of microtab height. The variation of microtab chord wise position has little effect on the buffet onset angle, but it has obvious influence upon the lift coefficient at buffet onset.