超声速空气介质自由扩散混合流涡的演化
Vortex evolution in supersonic air free diffused mixing layers
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摘要: 在不同谐波扰动促发方式下,观察二维超声速空气/空气自由扩散混合流中涡的形成及演化.考虑含空气组分扩散效应的可压缩Navier-Stokes方程,对流项采用3阶迎风紧致格式离散,输运项采用6阶对称紧致格式离散,非定常时间推进采用3阶紧致存储显式Runge-Kutta方法.在无相差情形下,获得了大尺度基频涡结构的饱和、一次对并、二次对并、三涡对并等现象.在Mac=0.3低对流Mach数下,基频涡较饱满,但流向尺度较小.受空气真实气体特性影响,在Mac=0.8高对流Mach数下未发现涡/小激波结构.Abstract: The vortex formation and evolution in a supersonic air/air free diffused plane mixing layer were investigated numerically by forcing four different harmonic disturbances without phase differences.The two-dimensional compressible Navier-Stokes equations including the diffusion effect of air components were solved by using a high accuracy finite difference method.The convective terms and transport terms were discretized by a third-order upwind compact scheme and a sixth-order symmetric compact scheme,respectively.The unsteady time marching method is a third-order compact storage explicit Runge-Kutta algorithm.Some phenomena of large-scale primary vortex growing and interacting were revealed,such as saturating,paring once and twice,and triple-vortex pairing.For low convective Mach number of Mac=0.3,primary vortices are fatter,but their streamwise lengths are shorter.Under the influence of air real-gas characteristics,the vortex-shocklet structure is not discovered in the case of high convective Mach number of Mac=0.8.
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Key words:
- compressible plane mixing layer /
- vortex pairing /
- harmonic disturbance /
- compact scheme /
- air
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