Direct numerical simulation of supersonic turbulent boundary layer over a compression ramp
Direct numerical simulation of supersonic turbulent boundary layer over a compression ramp
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DOI：
10.2514/1.27021
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发表时间：
2007-04-01
期刊：
影响因子：
2.5
通讯作者：
Martin, M. P.
中科院分区：
文献类型：
--
作者：
Wu, M.;Martin, M. P.
对Mach 2.9和Re-theta 2300下24度压缩坡道结构的激波和湍流边界层相互作用进行了直接数值模拟。采用了一种改进的加权非振荡格式。直接数值模拟结果与Bookey等人[Bookey， P. B., Wyckham， C., Smits， A. J., and Martin， M. P.，“STBLI在DNS/LES可达雷诺数下的新实验数据”，AIAA Paper No. 2005-309, Jan. 2005]在相同流动条件下的实验结果进行了比较。在实验不确定度范围内预测了上游边界层、平均壁面压力分布、分离泡大小和相互作用下游的速度分布。研究了整个相互作用区域的平均和波动特性的变化。从壁面压力信号和自由流质量通量测量中推断激波的低频运动。
A direct numerical simulation of shock wave and turbulent boundary layer interaction for a 24 deg compression ramp configuration at Mach 2.9 and Re-theta 2300 is performed. A modified weighted, essentially nonoscillatory scheme is used. The direct numerical simulation results are compared with the experiments of Bookey et al. [Bookey, P. B., Wyckham, C., Smits, A. J., and Martin, M. P., "New Experimental Data of STBLI at DNS/LES Accessible Reynolds Numbers," AIAA Paper No. 2005-309, Jan. 2005] at the same flow conditions. The upstream boundary layer, the mean wall-pressure distribution, the size of the separation bubble, and the velocity profile downstream of the interaction are predicted within the experimental uncertainty. The change of the mean and fluctuating properties throughout the interaction region is studied. The low frequency motion of the shock is inferred from the wall-pressure signal and freestream mass-flux measurement.