The present work incorporates the effects of boundary-layer suction in designing airfoils for hybrid laminar flow control application. The overall airfoil shape, the suction velocity distribution, and its location are optimized for minimum total drag while sustaining laminar flow over 80% of the airfoil top surface. Nondominated Sorting Genetic Algorithm II is used with the aerodynamic load computations from XFOILSUC and transition prediction from the improved Van Ingen $e^N$ method. The airfoil is designed for short-range subsonic conditions for three design lift-coefficient scenarios: 1) 0.4, 2) in the range of 0.3–0.7, and 3) in the range of 0.3–0.7 with suction onset at midchord. The optimized airfoil for scenario 3, with suction onset at midchord, results in a thicker airfoil with natural laminar flow (NLF) on the upper surface comparable to NLF airfoils. The total drag reduces by one-third due to the effects of suction. On the other hand, without limiting the suction onset (scenario 2), a thinner airfoil with longer NLF on the bottom surface and lower total drag is obtained. Optimum suction onset location is predicted to be at 30% of the chord. Suction is also observed to improve the drag bucket at off-design conditions.

目前的工作结合了边界层吸力在设计用于混合层流控制应用的翼型中的影响。整体翼型形状、吸入速度分布及其位置经过优化，以实现最小总阻力，同时维持 80% 以上的翼型顶面层流。非支配排序遗传算法 II 与 XFOILSUC 的气动载荷计算和改进的 Van Ingen 的过渡预测一起使用${\mathrm{电子}}^N$方法。翼型设计用于三种设计升力系数场景的短程亚音速条件：1) 0.4, 2) 在 0.3-0.7 的范围内，和 3) 在 0.3-0.7 的范围内，在中弦处开始吸力。场景 3 的优化翼型在中弦处开始吸力，导致上表面具有自然层流 (NLF) 的较厚翼型与 NLF 翼型相当。由于吸力的影响，总阻力减少了三分之一。另一方面，在不限制吸力开始（场景 2）的情况下，获得了更薄的翼型，底面上的 NLF 更长，总阻力更低。预计最佳吸入起始位置为弦的 30%。在非设计条件下，还观察到吸力可以改善拖斗。