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首页> 外文期刊>Modern Physics Letters, B. Condensed Matter Physics, Statistical Physics, Applied Physics >NUMERICAL SIMULATION OF UNSTEADY FLOW FIELD AROUND HELICOPTER IN FORWARD FLIGHT USING A PARALLEL DYNAMIC OVERSET UNSTRUCTURED GRIDS METHOD
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NUMERICAL SIMULATION OF UNSTEADY FLOW FIELD AROUND HELICOPTER IN FORWARD FLIGHT USING A PARALLEL DYNAMIC OVERSET UNSTRUCTURED GRIDS METHOD

机译：并行动态重叠非结构网格法数值模拟飞机前方飞行中的非定常流场。

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摘要

A parallel Navier-Stokes solver based on dynamic overset unstructured grids method is presented to si mulate the unsteady turbulent flow field around helicopter in forward flight. The grid method has the advantages of unstructured grid and Chimera grid and is suitable to deal with multiple bodies in relatively moving. Unsteady Navier-Stokes equations are solved on overset unstructured grids by an explicit dual time-stepping, finite volume method. Preconditioning method applied to inner iteration of the dual-time stepping is used to speed up the convergence of numerical simulation. The Spalart- Allmaras one-equation turbulence model is used to evaluate the turbulent viscosity. Parallel computation is based on the dynamic domain decomposition method in overset unstructured grids system at each physical time step. A generic helicopter Robin with a four-blade rotor in forward flight is considered to validate the method presented in this paper. Numerical simulation results show that the parallel dynamic overset unstructured grids method is very ef ficient for the simulation of helicopter flow field and the results are reliable.
机译：提出了一种基于动态过顶非结构化网格方法的并行Navier-Stokes求解器，以模拟直升飞机周围直升机的非定常湍流场。网格法具有非结构化网格和Chimera网格的优点，适用于在相对运动中处理多个物体。通过显式的双重时间步长有限体积方法，在非结构化超集网格上求解非定常Navier-Stokes方程。应用于二次时间步长内迭代的预处理方法可加快数值模拟的收敛速度。 Spalart-Allmaras一方程湍流模型用于评估湍流粘度。并行计算基于动态非结构化网格系统中每个物理时间步的动态域分解方法。考虑到四翼旋翼正转的通用直升机Robin可以验证本文提出的方法。数值模拟结果表明，并行动态过冲非结构化网格方法对于直升机流场的模拟非常有效，结果可靠。

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