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首页> 美国政府科技报告 >Parallel Implicit Multigrid Method for Direct Numerical Simulation of Time-Dependent Compressible Turbulent Flow Around Flight Vehicles
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Parallel Implicit Multigrid Method for Direct Numerical Simulation of Time-Dependent Compressible Turbulent Flow Around Flight Vehicles

机译：并行隐式多重网格法在飞行器周围时变可压缩湍流直接数值模拟中的应用

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摘要

An oblique transition process of a flat-plate boundary layer at a free-stream Mach number of M (infinity)=4.5 and a Reynolds number of 10000 based on free-stream velocity and inflow displacement thickness is simulated as the validation of the code. Four transitional stages are observed: the linear and weakly nonlinear growth, the appearance of staggered A-vortex patterns, the evolution of A-vortex into hairpin vortex, and the breakdown of hairpin vortical structures. The evolution of averaged quantities, such as the skin-friction coefficient, the mean velocity profile, the boundary layer thickness are all computed and found agreed very well with theoretic and experimental results. For complex geometry, 2D and 3D numerical grid generation method are used to generate high-quality meshes. Subsonic flow around 2D NACA 0012 airfoil and 3D Delta wing with a large angle of attack are investigated with large eddy simulation. Flow separations and large eddy structures are observed and the interactions between vortical structures are studied.

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