基于DDB的二维/轴对称三波交汇流场数值模拟  

Numerical simulation based on DDB fitting for 2D/axisymmetric triple shocks

作　　者：吴晴[1] 钟易成[1] 余少志[1] 胡骏[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《空气动力学学报》2010年第6期683-688,共6页Acta Aerodynamica Sinica

摘　　要：采用运动间断边界拟合算法,在运动网格下求解二维与轴对称欧拉方程组,对脱体激波、锥面波、三波交汇等多种稳态波系进行数值模拟,精确得到了多种典型激波形状、波后流场及波系结构。本文提出的运动间断边界拟合算法,系基于经典计算流体力学方法、R-H运动间断条件、运动边界条件和Delaunay背景网格技术,由指定的网格块边界拟合待求激波,并以网格分块方式解决多道波相交问题。通过引入轴对称形式欧拉方程组,直接将此算法推广至轴对称流动领域,并精确拟合了锥面波相交问题。算法精度高,易于在CFD程序基础上实现,可用于超声速飞行器进气道压缩面、唇口设计以及乘波体设计。The various steady shocks including bow shock,conic shock and triple shocks are simulated by dynamic discontinues-boundary fitting algorithm with moving grids,which solves 2D/axisymmetric Euler equations for unstructured mesh.Several typical supersonic shock flow have been simulated,and the shocks in flow all have been accurately gotten.The dynamic discontinuities boundary fitting algorithm is present in this paper,which is based on classic CFD simulation,R-H dynamic discontinued relations,dynamic boundary conditions and Delaunay graph mapping.The Initial grid boundary is moving and fitting for shock,and the shocks-fitting is computed with several grid blocks and boundaries.Conic shock and conic triple shocks can be fitted exactly by solving axisymmetric Euler equations using this algorithm.The dynamic discontinuities boundary fitting algorithm can be used for the design of supersonic waverider,inlet＇s pressure surface and lips,which may be developed easily in any CFD codes.

关 键 词：运动间断边界拟合 激波拟合法 轴对称流动 三波交汇 计算流体力学 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]