含激波的湍流流动高精度大涡数值模拟方法（英文）

发布时间：2018-07-29 11:39

【摘要】：针对采用亚格子模型进行含激波的湍流流动模拟时会面临激波附近的精度损失问题,考虑从通过亚格子模型以及数值模拟方法两方面的改进来实现湍流流动大涡模拟的精度提高。大涡模拟采用了Yee及Sj錸green(2009)提出的高阶低耗散方法。该方法采用自适应的流场探测器以控制计算中所需区域的数值耗散,并考虑对动力学模型采用在激波位置使用Sagaut和Germano(2005)提出的单边亚格子过滤器和(或)直接禁用亚格子项等方法加以改进。对于标准的马赫数1.5和3条件下的激波-湍流干扰问题,上述新方法相较于全区域采用亚格子模型的方法均表现出了相似的精度提升。同时实现的数值精度改进方案采用了Harten的亚单元分辨过程来定位和锐化激波,并在精确激波位置附近的网格点处采用了单边测试滤波。
[Abstract]:When using sub-lattice model to simulate turbulent flow with shock wave, the precision loss near shock wave will be faced. The improvement of sublattice model and numerical simulation method is considered to improve the accuracy of large eddy simulation of turbulent flow. The high order low dissipation method proposed by Yee and Sj rhenium green (2009) is used in large eddy simulation. An adaptive flow field detector is used to control the numerical dissipation of the required region in the calculation. The dynamic model is improved by using the one-sided sub-lattice filter proposed by Sagaut and Germano (2005) and / or directly disabling the sublattice term in the shock position. For the shock and turbulence interference problem under the standard Mach number of 1.5 and 3, the new method presented a similar accuracy improvement compared with the sublattice model in the whole region. At the same time, the numerical accuracy improvement scheme uses the sub-unit resolution process of Harten to locate and sharpen the shock wave, and the one-sided test filter is used at the grid point near the exact shock wave position.
【作者单位】： Center
【基金】：The support of the DOE/SciDAC SAP grant DE-AI02-06ER25796 is acknowledged Financial support from the NASA Aerosciences/RCA program for the second author is gratefully acknowledged Work by the fifth author was performed under the auspices of the U.S.Department of Energy at Lawrence Livermore National Laboratory under Contract DE-AC52-07NA27344
【分类号】：O357.5

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