高超声速激波/边界层干扰及MVG阵列流动控制研究

高超声速飞行器流场中通常会伴随激波/边界层干扰(SWBLI),其引发的流动分离将导致进气道性能下降。该文采用湍流分离涡(DES)方法、结合有限体积离散方法对来流马赫数为7流场中SWBLI诱导的分离气泡进行数值研究,模拟结果清晰地显示了分离气泡从产生到充分发展的具体过程,揭示了分离气泡的产生机理。利用微型涡流发生器(MVG)阵列对其进行控制,讨论了流场结构、壁面静压力、壁面剪切力及总压损失等参数变化对SWBLI控制效果的影响。结果表明:MVG阵列可显著改变高超声速流体边界层,使得分离气泡尺寸减小,分离激波强度减弱,分离气泡内及其下游流体的流向速度梯度增加,总压损失降低可达1.9%。

STUDIES ON HYPERSONIC SHOCK WAVE/BOUNDARY LAYER INTERACTIONS AND FLOW CONTROL BASED ON MVG ARRAY

Shock wave/boundary layer interaction (SWBLI) is a ubiquitous phenomenon encountered in hypersonic flow fields, and the flow separation it induces leads to performance degradation of hypersonic inlets. In this paper, the separation bubble which is induced by SWBLI in hypersonic flow (Ma=7) is simulated using DES (detached eddy simulation) and the finite volume method. The generation mechanism and development process of separation bubbles are revealed. The separation bubble was also controlled by an MVG array, and the flow field structures, wall pressure, wall shear stress, and the loss of total pressure when one is used are all discussed. The results indicate that an MVG array can suppress the separation bubble which is induced by hypersonic SWBLI; the strength of separation shock is weakened as the size of the separation bubble decreases; the streamwise velocity gradients of the separation bubble and its downstream are increased; the reduction of the loss of total pressure can reach 1.9%.