三维可压缩Boltzmann模型及其在低Mach数湍流中的应用

国岛雄一; 梶岛岳夫

doi:10.21656/1000-0887.370556

三维可压缩Boltzmann模型及其在低Mach数湍流中的应用

doi: 10.21656/1000-0887.370556

大阪大学机械工程系学院, 大阪吹田山田丘 2-1 565-0871,日本

详细信息

作者简介:
国岛雄一，E-mail: kunishima@fluid.mech.eng.osaka

中图分类号: O35; O422
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- 被引次数: 0
出版历程
- 收稿日期: 2016-11-08
- 修回日期: 2016-11-28
- 刊出日期: 2016-12-15

D Compressible Lattice Boltzmann Model and Its Appliaction to Low Mach Number Turbulent Flow

Department of Mechanical Engineering, Osaka University, 2-1 Yamadaoka, Suita, Osaka 565-0871, Japan

摘要

摘要: 改进了有限差分格子Boltzmann方法（FDLBM），以直接数值模拟气动噪声.基于LB求解器特性，采用动力学方程中的恒定对流速度以实施高阶迎风差分，提高了声波和湍流的分辨率.通过建立一个新的三维粒子模型，计算得到了任意比热容的三维可压缩Navier-Stokes系统.此外，利用Bhatnagar-Gross-Krook（BGK）碰撞算子，通过引入热流量修正，实现了Prandtl数的可变性.在激波管内弱声波以及伴随有温度梯度的Taylor-Couette层流的验证计算中，提出的新方法结果良好.此外也对NACA0012翼型绕流进行了三维模拟.其中，Reynolds数、Mach数和攻角分别取2×10⁵，8.75×10^-2以及9°.计算发现，在机翼前缘附近的分离气流位置，以及表面压力波动强度的Mach数依赖性方面，数值计算结果与实验结果相吻合.
- 有限差分格子Boltzmann方法 /
- 低Mach数流动 /
- 湍流
Abstract: We intend to improve the finite-difference lattice Boltzmann method (FDLBM) for the use of direct numerical simulation of aerodynamic sound.Using a feature of the LB-based solver, the constant advection velocity in the kinetic equation enables easy implementation of higher-order upwind difference schemes, resulting in high resolutions for sound waves as well as turbulent flow. We release a new particle model which recovers the compressible Navier-Stokes system with flexible specific heat ratio in the 3D space. In addition, we introduce a heat flux modification, which enables us to set Prandtl number freely under the Bhatnagar-Gross-Krook(BGK) collision operator. Our new method performs well in validation problems of weak acoustic waves in a shock tube, and laminar Taylor-Couette flow with a temperature gradient. We conduct a 3D simulation of flow around the NACA0012 aerofoil. The Reynolds number, Mach number and angle of attack are 2×10⁵, 8.75×10^－2 and 9° respectively. Our results are in good agreement with the experimental data about the position of the separation bubble near the leading edge and the Mach number dependence of the surface pressure fluctuation intensity.
- finite-difference lattice Boltzmann method /
- low Mach number flow /
- turbulent flow

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参考文献(13)

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