The leading edge slat can increase the flow energy of airfoil suction surface, and Microtab can hinder the flow of pressure surface. In order to combine the advantages of two passive flow control methods, this paper creatively proposed to combine the leading edge slat with Microtab to simulate the S809 airfoil, which slat had the contour characteristics of S809 airfoil. The transition SST turbulence model was applied to estimate the aerodynamic characteristics of the S809 airfoil. According to research, the flow control approach of the leading edge slat combined with Microtab could effectively restrain the flow separation and ameliorate the aerodynamic characteristics of the S809 airfoil. For Case-12, when the airfoil angle of attack was 16.22°, the boundary layer flow separation was restrained completely, C_l was increased to 3.06 from 1.79 and increased by 171% compared with clear airfoil. Research shown that the position of slat, the position and height of the Microtab were significant factors for the aerodynamic characteristics of the S809 airfoil. Microtab position at 0.95c and height at 0.03c performed the best effect to inhibit flow separation and improve lift coefficients.

前缘板条可以增加翼型吸力面的流动能，Microtab可以阻碍压力面的流动。为了结合两种被动流动控制方法的优点，本文创造性地提出将前缘缝翼与Microtab结合起来模拟S809翼型，该缝翼具有S809翼型的轮廓特征。采用过渡 SST 湍流模型估计 S809 翼型的气动特性。研究表明，前缘缝翼结合Microtab的流动控制方法可以有效抑制流动分离，改善S809翼型的气动特性。对于Case-12，当翼型攻角为16.22°时，边界层流动分离被完全抑制，C _l从 1.79 增加到 3.06，与透明翼型相比增加了 171%。研究表明，缝翼位置、Microtab 位置和高度是影响 S809 翼型气动特性的重要因素。在0.95C和高度为0.03 Microtab位置Ç进行抑制流动分离的最佳效果，提高升力系数。