Abstract
The lattice Boltzmann method (LBM) is an important numerical algorithm for computational fluid dynamics. This study designs a two-layer parallel model for the Sunway TaihuLight supercomputer SW26010 many-core processor, which implements LBM algorithms and performs optimization. Numerical experiments with different problem sizes proved that the proposed model has better parallel performance and scalability than before. In this study, we performed numerical simulations of the flows around the two-dimensional (2D) NACA0012 airfoil, and the results of a series of flows around the different angles of attack were obtained. The results of the pressure coefficient and lift coefficient were in good agreement with those in the literature.
Highlights
With the development of the supercomputer theory and computer hardware technology, numerical computation has become an important technical mechanism in scientific work
In the SW26010 heterogeneous many-core processor, each CG contains one management processing element (MPE) and one operational core array, which consists of 64 computing processing elements (CPEs), an array controller, and a secondary instruction operational core array, which consists of 64 CPEs, an array controller, and a secondary instruction cache
The neighboring grid point is discretely stored in the MPEs memory and cannot be transferred to the CPEs memory by direct memory access (DMA) at one time; it leads to multiple accesses to the MPEs memory and a higher time cost
Summary
With the development of the supercomputer theory and computer hardware technology, numerical computation has become an important technical mechanism in scientific work. Among the many numerical methods in the CFD field, the lattice Boltzmann method (LBM) [1,2] is a numerical simulation method with great potential It is derived from a lattice gas automaton, which is based on the microscopic thermal motion in fluid molecules. The numerical simulation of the two-dimensional (2D) airfoil simplifies the complexity of wind tunnel experiments and obtains better experimental results. It is the primary means of designing various high-lift airfoil types. This series of airfoils has been used in the aviation field for many years and has good aerodynamics performance In this series, NACA0012 has become the actual standard for numerical method research and verification owing to its symmetry and appropriate relative thickness
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