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针对带后缘襟翼的智能旋翼直升机典型襟翼参数对翼型动态失速特性的影响进行了研究。建立了带后缘襟翼的桨叶动态失速模型,考虑了襟翼与桨叶之间的缝隙和襟翼在运动过程中相对桨叶的凸起,采用计算流体力学(CFD)方法,研究了不同襟翼转轴位置和襟翼与桨叶的缝隙情况下的翼型动态失速特性,探讨了后缘襟翼激励幅值、时长和起始时刻对升力和俯仰力矩系数的影响。研究结果表明:后缘襟翼能够较好地改善翼型动态失速时的气流环境,并减缓动态失速发生;襟翼激励最优幅值在25°附近,最优激励范围在方位角为240°～360°之间;襟翼转轴后移导致襟翼运动时产生的凸起会使襟翼控制效果减弱;襟翼与桨叶的缝隙会影响翼型动态失速特性,但是缝隙的长度(弦长的2%以内)对襟翼控制效果的影响很小。
The influence of typical flap parameters of intelligent rotor helicopter with trailing edge flaps on the dynamic stall characteristics of airfoil is studied. The dynamic stall model of the blade with trailing edge flap was established. Considering the gap between the blade and the blade and the relative blade protrusion during the movement of the blade, CFD method was used to study The dynamic characteristics of the airfoil with different flap shaft positions and flap and blade clearances are discussed. The influence of the trailing edge flap excitation amplitude, duration and initial moment on the lift and pitch moment coefficients is discussed. The results show that the trailing edge flaps can improve the airflow environment and reduce the dynamic stall when the airfoils dynamic stall. The optimum amplitude of the flap excitation is around 25 ° and the optimum excitation range is about 240 ° ~ 360 °. The raised flaps caused by the flaps moving backward can weaken the control effect of the flaps. The flaps of the flaps and the blades affect the dynamic stall characteristics of the airfoils. However, the length of the gap Of the 2%) on the flap control effect is small.