Abstract: In order to further improve the performance of the bump inlet， a phenomenological simulation method was used to study the effects of the plasma jet on the bump-induced flow field under supersonic conditions. The effectiveness of the plasma synthetic jet control method was verified， and the influence of parameters such as the slit width of the actuator on its control effect was obtained. It is found that in the supersonic flow field， the induced shock formed by the plasma synthetic jet gradually develops from a symmetrical bow shock to an oblique compression wave. For an actuator with a slit width of 2mm， the effective time of the action of the plasma synthetic jet is a quarter cycle. During this time， it can suppress the shock surface induced by the bump， promote the bump to remove the boundary layer， and bring the separation point ahead of time， weaken the separation intensity， and make the boundary layer fuller. The parametric research on the slit width of the actuator shows that as the slit width increases， the jet outlet pressure increases， the action time increases， and the control effect of the jet on the bump displacement within the effective control time is enhanced. Jets in the wide range of slits explored can reduce the wall resistance by up to 3.2%.

Key words: Three-dimensional surface bump;Plasma synthetic jet;Phenomenological simulation;Separation;Flow control

摘要： 为进一步提升鼓包进气道性能，通过唯象仿真方法，对超声速条件下等离子体合成射流对鼓包诱导流场控制效果展开了研究，验证了等离子体合成射流控制方法的有效性，并获得了激励器缝宽等参数对其控制效果的影响规律。研究发现：在超声速流场中，等离子体合成射流形成的诱导激波由对称的弓形激波逐渐发展为斜压缩波。对于缝宽为2mm的激励器，等离子体合成射流作用的有效时间为1/4周期，在该时间内能够对鼓包诱导曲面激波起到抑制作用，促进鼓包排移边界层同时带来分离区分离点提前、分离强度减弱、使鼓包表面边界层更加饱满等影响。对于激励器缝宽的参数化研究表明，随着缝宽的增大，射流出口压力增大、作用时间延长、在有效控制时间内射流对鼓包排移的控制效果有所增强，在探究的缝宽范围内射流最多可降低壁面3.2%阻力。

关键词: 三维壁面鼓包;等离子体合成射流;唯象仿真;分离;流动控制