摘要
基于经典边界层理论,发展了一类简化的、按边界层厚度描述的速度入流边界条件。基于入流条件,对低速后向台阶流动和超声速压缩拐角流动进行了数值模拟。通过细致比较空间流场、边界层内速度型、表面摩擦阻力和压力分布等特性,对该类型边界条件进行了计算确认。结果表明,所发展的简化边界层厚度速度入流条件提法正确、合理,具有描述方法简单、鲁棒性好、适合工程计算的优点,可显著简化不同流速的管道流动的数值模拟。
Based on the classic theory of boundary layer, a new type of velocity inflow boundary condition （ BC ） that is formulated with the thickness of boundary layer is robust and suitable for engineering calculation. After that it is su proposed, which has properties as simple, ccessfully applied to numerical simulation of flow over a backward- facing step at low speed and a compressive comer at supersonic speed, which validate the new BC by comparing results of the spatial flow field, velocity profiles within boundary layer, skin friction and pressure coefficients. Good results have been obtained, which show that the new BC is true, and suitable for simplifying the simulation of tunnel flows at different flow speed.
出处
《航空计算技术》
2014年第1期5-8,共4页
Aeronautical Computing Technique
基金
国家重点基础研究发展(973)计划项目资助(2009CB723804)
中欧航空科技合作专项项目资助(FP7/2010-266326)
关键词
边界层理论
入流边界条件
后向台阶流动
压缩拐角流动
theory of boundary layer
inflow boundary condition
backward- facing step
supersonic com-pressive comer
