The turbulent boundary layer control on NACA 0012 airfoil with Mach number ranging from 0.3 to 0.5 by a spanwise array of dielectric barrier discharge (DBD) plasma actuators by hot-film sensor technology is investigated. Due to temperature change mainly caused through heat produced along with plasma will lead to measurement error of shear stress measured by hot-film sensor, the correction method that takes account of the change measured by another sensor is used and works well. In order to achieve the value of shear stress change, we combine computational fluid dynamics computation with experiment to calibrate the hot-film sensor. To test the stability of the hot-film sensor, seven repeated measurements of shear stress at Ma=0.3 are conducted and show that confidence interval of hot-film sensor measurement is from −0.18 to 0.18 Pa and the root mean square is 0.11 Pa giving a relative error 0.5% over all Mach numbers in this experiment. The research on the turbulent boundary layer control with DBD plasma actuators demonstrates that the control makes shear stress increase by about 6% over the three Mach numbers, which is thought to be reliable through comparing it with the relative error 0.5%, and the value is hardly affected by burst frequency and excitation voltage.

研究了通过热膜传感器技术通过介质阻挡放电（DBD）等离子体致动器的翼展阵列对马赫数在0.3到0.5之间的NACA 0012机翼的湍流边界层的控制。由于主要由与等离子体一起产生的热量引起的温度变化将导致由热膜传感器测得的剪切应力的测量误差，因此使用了考虑由另一个传感器测得的变化的校正方法，并且效果很好。为了获得剪切应力变化的值，我们将计算流体动力学计算与实验相结合以校准热膜传感器。为了测试热膜传感器的稳定性，对Ma处的剪切应力进行了七次重复测量进行了= 0.3的试验，结果表明，热膜传感器测量的置信区间为-0.18至0.18 Pa，均方根为0.11 Pa，在该实验中，相对于所有马赫数的相对误差为0.5％。DBD等离子作动器对湍流边界层控制的研究表明，该控制使剪切应力在三个马赫数上增加约6％，与相对误差0.5％相比，这被认为是可靠的，其值为几乎不受突发频率和激励电压的影响。