基于双微楔的高超声速激波与边界层干扰控制研究

发布时间：2018-05-18 01:07

本文选题：流体力学 + 高超声速　；参考：《兵工学报》2016年09期

【摘要】：高超声速飞行器在流场中通常会伴随激波与边界层干扰(SWBLI),其引发的流动分离将导致进气道性能下降。采用分离涡模型结合有限体积离散方法、自适应网格加密技术,对来流马赫数为7.0流场中SWBLI诱导的流动分离进行数值模拟,并基于边界层流向速度、压力梯度、形状因子、总压损失等参数讨论了不同微楔高度的控制效果,分析双微楔的控制机理。研究结果表明:双微楔产生的两对流向涡对之间的相互诱导促进了各自流向涡对之间的卷吸作用,使得双微楔对分离气泡的消除效果优于单只微楔;流动总压损失系数随着微楔阵列高度的增加呈先减小、后增加的趋势;综合讨论流向涡强度与形状阻力的影响,高度为35%分离气泡厚度的双微楔控制效果最好,分离气泡局部可减小至回流消失,边界层形状因子峰值降低86%,总压损失降低1.9%.
[Abstract]:Hypersonic vehicle is usually accompanied by shock wave and boundary layer interference in the flow field. Using the separation vortex model and the finite volume discrete method, adaptive mesh encryption technique is used to simulate the flow separation induced by SWBLI in the flow field with Mach number of 7.0. The flow separation is based on the flow velocity, pressure gradient and shape factor of the boundary layer. The control effect of different micro wedge height is discussed and the control mechanism of double micro wedge is analyzed. The results show that the mutual induction between the two pairs of flow vortex pairs produced by the double microwedge promotes the entrainment between the two pairs of vortex pairs, which makes the elimination effect of the separation bubble of the double microwedge pair better than that of the single microwedge pair. The total pressure loss coefficient of the flow decreases first and then increases with the increase of the height of the micro wedge array, and the effect of flow vortex strength and shape resistance is discussed synthetically, and the control effect of double micro wedge with the height of 35% separation bubble thickness is the best. The local separation bubble can be reduced until the circumfluence disappears, the peak value of the boundary layer shape factor decreases 86% and the total pressure loss decreases 1.9%.
【作者单位】：南京理工大学瞬态物理国家重点实验室;
【基金】：总装备部预先研究项目(9140C300206150C30143) 江苏省普通高校研究生创新计划项目(KYZZ15_0134)
【分类号】：O354.5

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