增升减阻是航空领域的重要课题，其关键在于降低机翼小迎角巡航状态下的摩擦阻力及抑制大迎角下的流动分离。脉冲直流介质阻挡放电（DBD）等离子体激励是一种新型的流动控制方法，其能基于有限的能耗实现显著的湍流摩擦减阻效果，同时具有系统结构简单、响应快、频带宽等优势。面向机翼大迎角流动分离控制的需求，采用脉冲直流激励方法进行了试验研究。首先，对脉冲直流DBD的放电波形、诱导体积力及冲击波特性进行了综合测试；在此基础上，基于NACA 0015翼型的平直翼模型开展了风洞试验，探究激励电压、激励频率、激励位置及来流速度等关键参数对流动分离控制效果的影响规律。结果表明脉冲直流DBD能同时产生体积力和冲击效应，有效抑制机翼大迎角下的流动分离，使模型最大升力系数提高7.17%，失速迎角增大2°，并使失速后的升力系数变化更为平缓。激励电压越高、来流速度越小，激励相对于流场的强度越大，流动控制效果越好；存在最佳激励频率100 Hz，与分离剪切层的脱落频率相吻合，流动控制效果最好；激励位置应布置于机翼前缘，避免其造成的扰动被分离区淹没以提高流动控制效果，实现对流动分离的有效抑制。

Lift enhancement and drag reduction are critical objectives in aeronautics， focusing particularly on minimizing skin-friction drag at low angles of attack during cruise and suppressing flow separation at high angles of attack. Pulsed Direct Current Dielectric Barrier Discharge （pulsed DC DBD） plasma actuation emerges as a novel flow control technique. It achieves significant turbulent friction drag reduction with limited energy consumption， while offering advantages such as simple system architecture， rapid response， and a wide frequency bandwidth. Targeting the control of airfoil flow separation at high angles of attack， an experimental investigation was conducted using the pulsed DC excitation method. Initially， comprehensive measurements of the discharge waveform， induced body force， and shock wave characteristics of the Pulsed-DC DBD were performed. Building on this， wind tunnel experiments were carried out on a straight wing model based on the NACA 0015 airfoil to investigate the influence of key parameters—including excitation voltage， pulse frequency， actuator placement， and free-stream velocity—on the effectiveness of flow separation control. Results indicate that the pulsed DC DBD simultaneously generates both a body force and a shock wave effect， which effectively suppresses flow separation at high angles of attack. This leads to a 7.17% increase in the maximum lift coefficient， a 2° extension of the stall angle， and a more gradual decline in the lift coefficient post-stall. Higher excitation voltages and lower free-stream velocities enhance the relative strength of the actuation compared to the flow field， resulting in improved control effectiveness. An optimal excitation frequency of 100 Hz was identified， which coincides with the shedding frequency of the separated shear layer and yields the best control performance. The actuator should be positioned at the leading edge to prevent its induced perturbations from being overwhelmed by the separation zone， thereby maximizing flow control effectiveness and achieving robust suppression of flow separation.