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基于可压缩Navier-Stokes方程,采用大涡模拟方法与高精度混合WENO/TCD格式,对Ma=1.4的超声速平面射流初始流场进行了数值研究.数值结果清晰地描述了超声速平面射流初始流场的结构特征,包括主涡环与激波结构以及它们演变过程.因主涡环内存在涡导激波对,激波与涡相互作用加速射流剪切层失稳,使剪切层首次卷起形成小涡的位置出现在涡导激波对后,此与亚声速射流情况不同.小涡串卷起成后,相继与涡导激波对相互作用,使激波出现明显的变形并加速主涡环失稳.
Based on the compressible Navier-Stokes equation, the initial flow field of supersonic planar jet with Ma = 1.4 is studied by LES and WENO / TCD. The numerical results clearly describe the initial flow field of supersonic planar jet Including the main vortex ring and the shock wave structure and their evolution process.Due to the existence of the vortex shock pair in the main vortex ring, the interaction between the shock wave and the vortex accelerates the shear layer instability and makes the shear layer roll up for the first time The formation of small vortex occurs after the vortex induced shock wave pair, which is different from that of the subsonic jet. After the small vortex coil is rolled up, it interacts with the vortex induced shock wave pair one after another, causing the shock to appear obvious deformation and accelerating Vortex ring instability.