高马赫数低雷诺数真实气体效应对流动分离与再附的影响

发布时间：2018-04-09 22:04

本文选题：真实气体效应　切入点：数值模拟　出处：《中国空气动力研究与发展中心》2015年硕士论文

【摘要】：随着时代和技术的进步,高超声速飞行器正由既定路线飞行(如：飞船返回舱、航天飞机、弹道导弹等)向高机动的方向发展,这使得飞行器的外形越来越复杂。在气动控制舵面、进气道拐角等关键部位出现激波边界层干扰、激波与激波相互作用、分离／再附等复杂流动现象,这将改变局部压力、摩阻与热流分布,其中对热流的影响尤其重要。再附点附近将会出现严重的气动加热现象,其热流峰值的大小和位置都是热防护系统设计中的关键设计参数。设计高机动性复杂外形高超声速飞行器面临的一个重要问题是如何合理的设计气动舵面,这对飞行器的有效控制及稳定性十分关键。飞行器在做高超声速飞行时,由于马赫数很高,强烈的激波压缩或粘性阻滞减速使得气体具有很高的温度,气体分子的内自由度将被激发,将发生离解、电离等化学反应,出现显著的高温真实气体效应。真实气体效应不仅会对飞行器的整体气动特性、热环境产生重要影响,同时也会显著的影响复杂外形导致的流动分离／再附等局部复杂流动现象。因此在设计高超声速飞行器气动舵面等重要部件时应当充分考虑真实气体效应的影响。论文共分为六章。第一章是引言,介绍了研究背景和意义,概述了国内外真实气体效应数值模拟研究以及真实气体效应对局部复杂流动影响研究的概况,简述了本文的研究内容。第二章和第三章介绍了本文求解平衡流及化学非平衡流的数值方法。第四章通过典型算例对建立的数值模拟程序进行了验证。第五章对带舵偏的升力体外形开展了不同气体模型、不同条件下的数值模拟研究,分析了真实气体效应对舵面附近局部流动分离及整体气动性能的影响情况和机理。第六章总结了本文的工作和得到的结论,并对下一步工作进行了展望。
[Abstract]:With the development of times and technology, the hypersonic vehicle is developing from the fixed route (such as the spacecraft return module, space shuttle, ballistic missile etc.) to the direction of high maneuverability, which makes the shape of the aircraft more and more complex.In the aerodynamic control rudder surface, the inlet corner and other key parts appear shock wave boundary layer interference, shock wave and shock wave interaction, separation / reattachment and other complex flow phenomena, which will change the local pressure, friction and heat flow distribution.The effect on heat flux is especially important.There will be a serious aerodynamic heating phenomenon near the reattachment point. The magnitude and position of the peak heat flux are the key design parameters in the design of the thermal protection system.An important problem in the design of hypersonic aircraft with high maneuverability and complex shape is how to reasonably design the aerodynamic rudder surface, which is very important for the effective control and stability of the aircraft.In the hypersonic flight of an aircraft, due to the high Mach number, the intense shock compression or viscous deceleration makes the gas have a very high temperature, the internal degree of freedom of the gas molecule will be excited, and chemical reactions such as dissociation and ionization will take place.There is a significant real gas effect at high temperature.The real gas effect will not only have an important impact on the overall aerodynamic characteristics and thermal environment of the aircraft, but also have a significant impact on the local complex flow phenomena such as flow separation / reattachment caused by complex shapes.Therefore, the influence of real gas effect should be fully considered in the design of important components such as the aerodynamic rudder surface of hypersonic vehicle.The thesis is divided into six chapters.The first chapter is the introduction, which introduces the background and significance of the research, summarizes the numerical simulation of the real gas effect and the effect of the real gas effect on the local complex flow at home and abroad, and briefly describes the research content of this paper.In the second and third chapters, the numerical methods for solving equilibrium and chemical nonequilibrium flows are introduced.In chapter 4, the numerical simulation program is verified by a typical example.In chapter 5, different gas models and numerical simulation under different conditions are carried out for the shape of lift body with rudder deviation, and the effect and mechanism of real gas effect on local flow separation and overall aerodynamic performance near rudder surface are analyzed.The sixth chapter summarizes the work and conclusions of this paper, and looks forward to the next work.
【学位授予单位】：中国空气动力研究与发展中心
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V211

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