翼型激波-湍流边界层干扰分析

Analysis of shock wave-turbulent boundary layer interaction on airfoil

文章对来流马赫数0.729、攻角2.31°的超临界跨音速翼型RAE2822进行了隐式大涡模拟(implicit large eddy simulation,ILES);对翼型上表面的激波-湍流边界层干扰进行了研究,并对湍流的统计特征进行了分析,主要分析了干扰过程中流向速度脉动的均方根、雷诺应力,以及湍动能的生成、耗散及分配机制。结果表明,激波的出现对于速度脉动和雷诺应力的幅值及峰值位置有显著的影响,而且干扰过程中产生了大量湍动能,湍动能的主要耗散区仍在近壁,湍动能的分配机制并非生成-耗散相互平衡,而是一种更为复杂的平衡关系。

An implicit large eddy simulation(ILES)of the shock wave-turbulent boundary layer interaction flow on a RAE2822 supercritical airfoil at the free stream Mach number of 0.729 and angle of attack of 2.31 degrees is made.The shock wave-turbulent boundary layer interaction on the upper surface of the airfoil is studied,and the statistical characteristics of the turbulence are analyzed.The root-mean-square of the velocity fluctuation,Reynolds stress,turbulent kinetic energy production,dissipation and distribution mechanisms are mainly analyzed during the disturbance process.The results show that the occurrence of shock waves has a significant effect on the amplitude and peak position of the velocity fluctuation and Reynolds stress and a large amount of turbulent kinetic energy generates during the disturbance process,and the main dissipative region of turbulent kinetic energy is still near the wall.The distribution mechanism is not a generation-dissipation balance but a complex balance.