摘要
针对可压缩湍流流动,构建了1种动力混合RANS/LES模式。运用该模式模拟了超声速后向台阶流动,结果再现了二维后向台阶剪切层的拟序结构,计算得到了统计平均的压力分布,回流区长度与实验结果符合较好。与定系数的一般混合RNAS/LES模拟结果的对比表明,动力混合RANS/LES模式在对流场拟序结构的捕捉、流动时均压力分布方面表现较优。
Dynamic hybrid RANS （ Reynolds - Averaged Navler - Stokes ）/LES （ Large Eddy Simulation ） model is set up for compressible turbulent flow. Supersonic flow over back - facing step is simulated by above model, and the simulations reproduce the coherent structure for two - dimension back - facing step in shear layer regions. Statistical average of pressure distribution is calculated, and the simulations agree well with experimental results for the length of circumfluence. Comparing to general hybrid RNAS/LES model of determined coefficient, the model has the adventages in capturing coherent structure of flowffied and time averaged pressure distribution.
出处
《航空发动机》
2007年第2期49-52,34,共5页
Aeroengine
