空气动力学学报2018，Vol.36Issue(2)：229-237,9.DOI:10.7638/kqdlxxb-2018.0020
超声速/高超声速边界层转捩后期流场的模态分析
Modal analysis of late transition in supersonic/hypersonic boundary layer
摘要
Abstract
Dynamic mode decomposition (DMD) is applied to the analysis of supersonic and hypersonic boundary layer late transitional flow.The primary coherent structures are obtained and modal reconstruction is performed.The relation is studied between the coherent structures,the skin friction and the heat flux.Significant difference can be found between supersonic and hypersonic transitional flow.Streamwise vortex of low-frequency modes plays dominant roles in supersonic transitional flow.These modes contribute to the skin friction and heat flux.In hypersonic boundary layer,there exist modes with several different orders of frequencies,and they're shown as several different branches in DMD frequency spectrum.By the analysis of the modes with the highest energy of each branch,we find that the structures of low-frequency modes are streamwise streaks,while for high frequency modes the structure is two-dimensional disturbance waves.The influence of skin friction and heat flux on the wall is similar to the structure of the modes.关键词
动力模态分解/超声速/高超声速边界层/转捩后期/壁面阻力和热流Key words
dynamic mode decomposition/supersonic/hypersonic boundary layer/late transition/skin friction and heat flux分类
数理科学引用本文复制引用
余明,黄伟希,许春晓..超声速/高超声速边界层转捩后期流场的模态分析[J].空气动力学学报,2018,36(2):229-237,9.基金项目
国家重点研发计划项目(2016YFA0401200) （2016YFA0401200）
