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Re=1×10~6的条件下,在S809翼型前缘设置微小圆柱,分别研究了静止及振动的微小圆柱对S809翼型气动性能的影响。数值模拟的结果表明:S809翼型前缘适当位置设置静止及一定振动方式的微小圆柱均能明显降低阻力系数、减小或抑制流动分离区的大小、改善流场状况;在翼型前缘点吸力面正上方6%弦长处,设置直径为2%弦长的静止圆柱可以完全抑制翼型的流动分离;当圆柱直径变小时,静止微小圆柱控制流动分离的效果变差,但此时给圆柱一定规律的振动后,又可以达到较好的流动分离控制效果。
In the condition of Re = 1 × 10 ~ 6, the tiny cylinder is set on the leading edge of S809 airfoil, and the effects of static and vibrating micro cylinder on aerodynamic performance of S809 airfoil are studied respectively. The results of numerical simulation show that the setting of a small cylinder of static and certain vibration modes in the proper position of the leading edge of S809 airfoil can obviously reduce the drag coefficient and reduce or inhibit the size of the flow separation zone and improve the flow field conditions. The 6% chord length directly above the suction surface can restrain the airfoil flow separation completely when the diameter is 2% of the chord length. When the diameter of the cylinder becomes smaller, the effect of static micro cylinder control flow separation becomes worse, but at this time, A certain regular vibration, but also can achieve better flow separation control.