论文标题
与混合晶格Boltzmann方法的NACA 0012围绕NACA 0012机翼的流体流量
Fluid flow around NACA 0012 airfoil at low-Reynolds numbers with hybrid lattice Boltzmann method
论文作者
论文摘要
我们使用混合晶格Boltzmann方法（HLBM）模拟了国家航空航空咨询委员会（NACA）0012机翼周围的二维流体流，该委员会将标准的晶格玻尔兹曼方法与非结构化的有限批量配方相结合。该研究的目的是评估计算方法的数值性能和鲁棒性。为此，在提供了一项融合研究以估算该方法的总体准确性之后，我们分析了在雷诺数等于$ 10^3 $的不同攻击角度值的数值解决方案。随后，计算零攻击配置角度最高$ 10^4 $的流场。将网格完善方案应用于重叠网格系统的均匀间隔组件，以进一步提高模型的数值效率。结果证明了HLBM在实心弯曲壁附近实现高精度的能力，从而在基于车身拟合的网格的非晶格玻尔兹曼方法领域提供了可行的替代方案。
We simulate the two-dimensional fluid flow around National Advisory Committee for Aeronautics (NACA) 0012 airfoil using a hybrid lattice Boltzmann method (HLBM), which combines the standard lattice Boltzmann method with an unstructured finite-volume formulation. The aim of the study is to assess the numerical performances and the robustness of the computational method. To this purpose, after providing a convergence study to estimate the overall accuracy of the method, we analyze the numerical solution for different values of the angle of attack at a Reynolds number equal to $10^3$. Subsequently, flow fields at Reynolds numbers up to $10^4$ are computed for a zero angle of attack configuration. A grid refinement scheme is applied to the uniformly spaced component of the overlapping grid system to further enhance the numerical efficiency of the model. The results demonstrate the capability of the HLBM to achieve high accuracy near solid curved walls, thus providing a viable alternative in the realm of off-lattice Boltzmann methods based on body-fitted mesh.
