NS-DBD激励控制非细长三角翼前缘涡仿真研究

通过在三角翼前缘施加纳秒脉冲介质阻挡放电（NS-DBD）激励唯象学模型，进行了47°后掠角钝前缘三角翼流动控制的仿真。分析了不同迎角下升力和阻力系数的变化、流场结构的变化、以及激励诱导旋涡的演化过程。研究表明:施加无量纲激励频率F+=1.44的NS-DBD激励后，可明显提高三角翼失速前后的升力系数；同时阻力系数也有所增加，变化趋势与实验结果一致。激励在前缘分离剪切层处诱导产生流向涡，改变了前缘剪切层结构，使其向内卷吸；激励后时均流场形成了明显的负压峰值，前缘涡附着线外移，吸力面回流区减小。 

Numerical investigation on leading-edge vortex control fornon-slender delta wing by nanosecond pulsedielectric barrier discharge actuation

Through applying phenomenological model of nanosecond pulse dielectric barrier discharge（NS-DBD） actuation to the leading edge of delta wing, the flow control simulation was conducted over a 47° blunt-edged delta wing. The variations of lift coefficients and drag coefficients at different attack angles, as well as the evolutions of flow structure and induced vortex, were analyzed. The results show that, if ignited at the reduced frequency of F+=1.44, the actuation can obviously improve the lift coefficients before and after stall, and the drag coefficients also increased, and kept consistent with the experimental results. Chordwise vortex induced by every actuation could change the structure of the leading-edge separated shear layer and cause it to curl inwards. There were obvious negative pressure peak values on the wings upper surface for the time-averaged flow field with actuation. Also, the flow reattachment was promoted and the region of backflow was reduced under NS-DBD actuation.