附面层抽吸位置对翼型绕流分离控制的影响

Effects of boundary layer suction location on flow around airfoil separation control

为了深入研究抽吸作用位置对翼型绕流分离控制效果的影响,采用HLLC格式和双时间步长LU-SGS隐式算法对二维可压N-S方程进行数值求解,数值模拟了雷诺数Re为6 000时,NACA0012翼型在上翼面抽吸控制下的翼型绕流流场。研究了抽吸区域位置对翼型流动分离和翼型气动性能的影响。结果表明:同一抽吸系数下,合理的抽吸位置是有效改善翼型气动性能的重要因素,并且不同抽吸位置的作用机制不同。对于以开式分离为特征的NACA0012翼型绕流,其合理抽吸区域位于翼型前缘分离区内。

In order to study the effects of suction locations on the airfoil flow separation control,the two-dimensional compressible Navier-Stokes equations are solved by using HLLC scheme and LUSGS scheme with the dual-time-stepping technique,and the flow field around the NACA0012 airfoil under the upper airfoil surface suction control is simulated numerically when Re is 6000.The effects of different suction zone locations on separation suppressions and aerodynamic performances of airfoil are researched.The computational results show that under the same suction coefficient,the suction zone location is the important factor improving the aerodynamic performances of the airfoil effectively.And the control mechanisms are different when the suction controls act at the different suction locations.For the NACA0012 airfoil with the open separation characteristics,the appropriate location of the suction zone is in the leading-edge separation zone.