基于双微楔的高超声速激波与边界层干扰控制研究

doi:10.3969/j.issn.1000-1093.2016.09.011

兵工学报 ›› 2016, Vol. 37 ›› Issue (9): 1624-1632.doi: 10.3969/j.issn.1000-1093.2016.09.011

基于双微楔的高超声速激波与边界层干扰控制研究

董祥瑞，陈耀慧，董刚，刘怡昕

(南京理工大学瞬态物理国家重点实验室, 江苏南京 290014)

收稿日期:2015-06-11 修回日期:2015-06-11 上线日期:2016-11-04
通讯作者: 董祥瑞 E-mail:dongxr1154@126.com
作者简介:董祥瑞(1991—)，女，博士研究生
基金资助:
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)

Research on Control of Hypersonic Shock Wave/boundary Layer Interactions by Double Micro-ramps

DONG Xiang-rui， CHEN Yao-hui， DONG Gang， LIU Yi-xin

(National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China)

Received:2015-06-11 Revised:2015-06-11 Online:2016-11-04
Contact: DONG Xiang-rui E-mail:dongxr1154@126.com

摘要/Abstract

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%.

关键词: 流体力学, 高超声速, 激波与边界层干扰, 微楔涡流发生器, 流动分离控制, 流向涡

Abstract: Shock wave/boundary layer interaction (SWBLI) is a ubiquitous phenomenon encountered in hypersonic flow field, and a flow separation induced by SWBLI leads to the performance degradation of hypersonic inlet. Detached-eddy simulation model and finite volume method are used with adaptive mesh refinement to simulate the flow separation controlled by micro-ramps, which is induced by SWBLIs in hypersonic flow for Ma=7. The control effect of micro-ramps on flow separation is discussed based on flow velocity, pressure gradient, transformed form factor and total pressure loss, and the control mechanism of double micro-ramps is investigated. The research results indicate that the reciprocal induction between streamwise vortex pairs generated by two micro-ramps accelerates the entrainment of vortex pairs generated by each micro-ramp, consequently the effect of two micro-ramps for eliminating the separation bubble is better than that of a single micro-ramp. As the height of micro-ramps decrease, the total pressure loss shows a trend of first decrease and then increase. The effects of streamwise vortex intensity and form resistance are synthetically discussed. The micro-ramps with 35%δ′ in height (separation bubble thickness) have the best effect on controlling the separation bubble, by which the separation bubble is decreased to disappear the reversed flow, and the peak of transformed form factor and the total pressure loss are reduced by about 86% and 1.9%, respectively.

Key words: fluid mechanics, hypersonic flow, shock wave/boundary layer interaction, micro-ramp, flow separation control, streamwise vortex

中图分类号:

O354.4

董祥瑞，陈耀慧，董刚，刘怡昕. 基于双微楔的高超声速激波与边界层干扰控制研究[J]. 兵工学报, 2016, 37(9): 1624-1632.

DONG Xiang-rui， CHEN Yao-hui， DONG Gang， LIU Yi-xin. Research on Control of Hypersonic Shock Wave/boundary Layer Interactions by Double Micro-ramps[J]. Acta Armamentarii, 2016, 37(9): 1624-1632.

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基于双微楔的高超声速激波与边界层干扰控制研究

Research on Control of Hypersonic Shock Wave/boundary Layer Interactions by Double Micro-ramps

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