Large-Eddy Simulation of Supersonic Flat-Plate Boundary Layers Using the Monotonically Integrated Large-Eddy Simulation (MILES) Technique
Large-Eddy Simulation of Supersonic Flat-Plate Boundary Layers Using the Monotonically Integrated Large-Eddy Simulation (MILES) Technique
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使用单调积分大涡模拟 (MILES) 技术对超音速平板边界层进行大涡模拟
DOI：
10.1115/1.1516578
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发表时间：
2002
影响因子：
2
通讯作者：
A. Zheltovodov
中科院分区：
文献类型：
--
作者：
Hong Yan;D. Knight;A. Zheltovodov
采用单调积分大涡模拟（MILES）技术，对不同马赫数（M =2.88和4）下，雷诺数为2× 104的超声速平板边界层进行了数值模拟。采用隐式亚网格尺度（SGS）模型封闭Favre滤波的可压缩Navier-Stokes（NS）方程。在非结构化四面体网格上，采用时间和空间上均具有二阶精度的有限体积法求解Navier-Stokes方程。通过模拟绝热和等温两种情况预测了传热系数
A supersonic flat-plate boundary layer at a Reynolds number of 2×10 4 based on the inflow boundary layer thickness is investigated at different Mach numbers (M =2.88 and 4) using the monotonically integrated large-eddy simulation (MILES) technique. The inherent numerical dissipation is taken as an implicit subgrid scales (SGS) model to close the Favre-filtered compressible Navier-Stokes (NS) equations. A finite volume method with second-order accuracy in time and space is implemented for the solution of the Navier-Stokes equations on an unstructured grid of tetrahedra. The heat transfer coefficient is predicted by simulating both adiabatic and isothermal cases