The aim of the present work is to control the dynamic stall of a pitching NACA0012 airfoil and improve its aerodynamic performance by using a synthetic jet in a low Reynolds number compressible flow for use in prospective applications, such as flights on Mars and in the stratosphere. A recently developed variable correction-based immersed boundary method is employed to predict the complex flow fields. A sinusoidal function is selected to fulfill the periodic jet. Compared with the situation without control, the use of a synthetic jet can obtain a significant improvement of the aerodynamic performance of the pitching airfoil. Based on the numerical results, adjusting the phase angle to trigger the suction time of the synthetic jet at a large angle of attack can obtain the best lift increment and drag reduction. Additionally, in a small variation range, a larger jet momentum coefficient can produce better aerodynamic performance. However, when the jet momentum coefficient increases up to some fixed value, the enhancement is weakened. Furthermore, placing the jet at the leading edge is more conducive to improving the aerodynamic performance. Finally, the higher the Mach number, the worse the control effect of the synthetic jet.

本工作的目的是通过使用低雷诺数可压缩流中的合成射流来控制俯仰NACA0012机翼的动态失速并改善其空气动力学性能，以用于未来应用，例如火星和平流层中的飞行。最近开发的基于变量校正的沉浸边界方法被用来预测复杂的流场。选择正弦函数来满足周期性射流。与不受控制的情况相比，使用合成射流可以显着改善俯仰翼型的空气动力学性能。根据数值结果，调整相位角以在大迎角下触发合成射流的吸入时间可以获得最佳升程增量和减阻效果。另外，在较小的变化范围内，较大的喷气动量系数可以产生更好的空气动力学性能。但是，当射流动量系数增加到某个固定值时，增强作用减弱。此外，将射流放置在前缘更有利于改善空气动力学性能。最后，马赫数越高，合成射流的控制效果越差。