高超声速计算中的气体动理学格式  

Gas kinetic scheme in hypersonic flow simulation

作　　者：徐昆[1] 陈松泽[1] 

机构地区：[1]香港科技大学数学系

出　　处：《航空学报》2015年第1期135-146,共12页Acta Aeronautica et Astronautica Sinica

基　　金：香港研资局基金(621011;620813);高温气体动力学国家重点实验室开放基金(2013KF03);北京大学湍流与复杂系统国家重点实验室资助~~

摘　　要：回顾了高超声速连续流部分的计算流体力学(CFD)方法,总结了近些年兴起的气体动理学格式。阐述了该格式的构造机制,强调了将物理规律直接用于构造数值方法的思路。结合一些应用实例,例如激波相互作用、激波边界层相互作用以及边界层分离等高超声速问题,说明了这种构造思路给数值模拟带来的优点。从高超声速的发展历程来看,气体动理学格式的构造过程包含了更基础的物理规律,而且具有多尺度的特性。这些特性有助于研究复杂的高超声速问题。介观或者微观角度直接构造数值方法的发展趋势为高超声速计算工具指出了可能的发展方向。For hypersonic flow simulation, a review of computation fluid dynamics （CFD） and a summary of gas kinetic scheme are presented in this paper. The mechanism underlying the construction of gas kinetic scheme is clarified by comparing it with the traditional CFD method. The importance of direct modeling and the implementation of the physical laws in a discretized space are emphasized. Through some classical hypersonic applications in recent years, such as the shock/shock interaction, shock wave/boundary layer interaction, and hypersonic boundary layer separation problems, the advantages of the methodology are also demonstrated. As a trend of CFD, the gas kinetic scheme includes more fundamental physical laws in its algorithm construction, and the multiple scale nature makes the kinetic scheme feasible for the hypersonic applications. The principle of direct modeling and the methodology of constructing numerical schemes from mesoscopic or microscopic flow dynamics would benefit the development of reliable flow solvers, especially for the high speed flow.

关 键 词：高超声速 气体动理学格式 滑移边界条件 激波相互作用 激波边界层干扰 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程] O354.4[理学—流体力学]