摘要
以嵌边法为出口边界条件试算了亚、超声速平板边界层扰动波的演化、超声速流中涡的传播、亚声速平板边界层尾缘扰动的演化等,以验证嵌边法作为出流条件在可压缩流中的有效性。然后,探讨了嵌边法有关参数的选取问题。
For numerical simulations of compressible flows, characteristic boundary conditions are usually used to ensure that the disturbances pass through the boundary without causing reflections. However, sometimes, they do not yield satisfactory results for unsteady flows. On the other hand, ＂fringe method＂, also called ＂buffer zone method＂, has been proved to be effective in guarantee non-reflection for incompressible flows. Its main idea is that a fringe, or buffer zone, is added to the original computational domain, in which the governing equations are modified, such that disturbances are almost totally damped in propagating through this buffer zone, so there will be no disturbance to be reflected at the exit of the buffer zone. In this paper, by applying the ＂fringe method＂ to several unsteady compressible flows, such as the evolution of disturbances in subsonic and supersonic boundary layers, vortex convection in a supersonic flow, and the scattering of T-S waves at the trailing edge of a subsonic boundary layers on a fiat plate, we showed that the fringe method is also effective in compressible flows. We proposed the criteria for the effectiveness of the method, and also discussed the effects of the parameters in the fringe method.
出处
《空气动力学学报》
EI
CSCD
北大核心
2006年第3期289-294,共6页
Acta Aerodynamica Sinica
基金
国家自然科学基金(资助号90205021)
全国博士学位论文作者专项资助(资助号200328)
南开大学
天津大学刘徽应用数学中心资助项目
关键词
直接数值模拟
嵌边法
边界条件
可压缩流
direct numerical simulation
fringe method
boundary condition
compressible flow
