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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%。
Hypersonic vehicle flow fields are usually accompanied by shock / boundary layer interference (SWBLI), which causes the flow separation will lead to reduced inlet performance. In this paper, we use the Turbulent Separation Vortex (DES) method and the finite volume discretization method to study the SWBLI-induced separation bubble in the flow field with Mach-7, and the simulation results clearly show that the separation bubble from generation to full development Process, revealing the mechanism of separation of bubbles. The micro-vortex generator (MVG) array is used to control the influence of the parameters such as flow field structure, wall static pressure, wall shear force and total pressure loss on the control effect of SWBLI. The results show that the MVG array can significantly change the boundary layer of hypersonic fluid, resulting in the decrease of separation bubble size, the decrease of separation shock intensity, and the increase of flow velocity gradient in the separation bubble and its downstream fluid. The total pressure loss can be reduced by 1.9%.