Large Eddy Simulation of a Supersonic Compression Corner Part I
Large Eddy Simulation of a Supersonic Compression Corner Part I
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超音速压缩角的大涡模拟第一部分
DOI：
10.2514/6.2000-398
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发表时间：
2000
期刊：
影响因子：
--
通讯作者：
A. Zheltovodov
中科院分区：
文献类型：
--
作者：
G. Urbin;D. Knight;A. Zheltovodov
本文对马赫数为3的绝热湍流边界层与25 ′压缩角激波系的相互作用进行了大涡模拟研究。过滤的可压缩Navier-Stokes方程求解的三维非结构网格的四面体细胞使用有限体积制剂。入流条件是由再密封-再引入方法产生的。亚网格尺度运动采用单调积分大涡模拟（MILES）方法。入射激波在主激波冲击点上游引起边界层分离，在分离附近形成二次激波。流场结构的定性数据。
A preliminary LES study of the interaction of a Mach 3 adiabatic turbulent boundary layer with the shock system generated by a 25’ compression corners is presented. The filtered compressible Navier-Stokes equations are solved on a three-dimensional unstructured grid of tetrahedral cells using a finite volume formulation. The inflow conditions are produced by a resealing-reintroducing method. The subgrid scale motions are modeled using the Monotone Integrated Large Eddy Simulation (MILES) method. The incident shock causes separation of the boundary layer upstream of the point of impingement of the primary shock, with a secondary shock forming near the separation. Qualitative data on the flowfield structure are presented.