Experimentally investigation is conducted on the control of post-stall airfoil aerodynamics using a vortex-generator type plasma actuator (VG-PA), in burst mode (BM) at a Reynolds number Re of 0.77 × 10⁵. The VG-PA has two sawtooth-shaped electrodes that are separated by a dielectric layer and are arranged with opposite saw-teeth pointing at each other, resulting in a spanwise periodic change in electrode gap. The dependence of the lift coefficient $C_L$ of a NACA 0015 airfoil on the non-dimensional burst frequency $F^{+}$ (= $f_{b}c$/$U_{\infty }$, where c and $U_{\infty }$ are the airfoil chord length and the freestream velocity, respectively) and duty cycle (DC) is investigated systematically; 144 combinations of $F^{+}$ (= 0.3-9.0) and DC (= 1%-100%) are examined. Under steady actuation ($\mathit{DC}=100$%), the stall angle-of-attack α is postponed from 13° to 18° and the maximum $C_L$ exceeds that of no control by 9%. Given the same applied voltage $V_a$, this α is postponed to 16° under the optimum BM parameters ($F^{+}=0.6$, $\mathit{DC}=5$%), but its maximum $C_L$ exceeds that of no control by 27.5%. Furthermore, its consumption of power is only 5% of that under the steady actuation. Careful examination of the flow structure generated by the VG-PA as well as the perturbed airfoil wake unveils distinct mechanisms behind the lift enhancement under the steady and BM actuations. While the former depends on the direct injection of large momentum and vorticity, the latter is linked to the spanwise vortices periodically-induced by the VG-PA.

实验研究了使用涡流发生器型等离子体致动器（VG-PA）在爆破模式（BM）下以雷诺数Re为0.77×10 ^5来控制失速后翼型的空气动力学特性。VG-PA具有两个锯齿形电极，这些电极由介电层隔开，并以彼此相对的锯齿指向彼此排列，从而导致电极间隙沿翼展方向周期性变化。升力系数的依赖性$C_{\mathrm{大号}}$ NACA 0015机翼对无量纲爆裂频率的影响 $F^{+}$ （= $F_{b}C$/${ü}_{\infty }$，其中c和${ü}_{\infty }$系统地研究了翼型弦长和自由流速度）和占空比（DC）; 144个组合$F^{+}$（＝ 0.3-9.0）和DC（＝ 1％-100％）被检查。在稳定驱动下（$\mathit{直流电}=100$％），失速攻角α从13°推迟到18°，最大$C_{\mathrm{大号}}$超过无控制者的9％。给定相同的施加电压$V_{\mathrm{一种}}$，在最佳BM参数下，该α被推迟到16°（$F^{+}=0.6$， $\mathit{直流电}=5$％），但最大值 $C_{\mathrm{大号}}$超出无控制者27.5％。此外，其功率消耗仅为稳定驱动下的5％。仔细检查由VG-PA产生的流动结构以及扰动的翼型尾流，揭示了在稳定和BM驱动下升力增强背后的独特机制。前者取决于直接注入大的动量和涡度，而后者则与VG-PA周期性引起的翼展涡旋有关。