The efficiency of stationary air blowing/suction into the turbulent boundary layer of the NACA 0012 airfoil through permeable sections located at the adjacent sides of the wing in the vicinity of its trailing edge is studied numerically and experimentally. The flow rates in these sections are varied in the intervals 0 ÷ 9.33·10⁻⁴ and 0 ÷ 8.48·10⁻⁴, respectively. The studies are carried out at the Reynolds number Re_c = 0.7·10⁶ in the range of angles of attack α = − 6 ÷ 6°. The efficiency of the control method is estimated from the results of measurements using the original method proposed by Jones, based on traversing the wake behind the airfoil, and a modification of this method, as well as by using the results of numerical simulations. The necessity of the Jones formula modification is demonstrated to be particularly important in the case with individual suction and blowing because mass transfer through the surface changes the momentum transferred from the undisturbed external flow to the boundary layer.

通过位于机翼后缘附近相邻侧的可渗透部分将固定空气吹入/吸入 NACA 0012 机翼的湍流边界层的效率进行了数值和实验研究。这些部分中的流速分别以0÷9.33·10 ^-4和0÷8.48·10 ^-4的间隔变化。这些研究是在雷诺数进行重新_Ç = 0.7·10 ⁶中的攻角范围α= − 6 ÷ 6°。控制方法的效率是根据使用琼斯提出的原始方法的测量结果来估计的，该方法基于遍历机翼后面的尾流，以及该方法的修改，以及使用数值模拟的结果。琼斯公式修正的必要性被证明在单独吸入和吹气的情况下特别重要，因为通过表面的质量传递改变了从不受干扰的外部流传递到边界层的动量。