Mesh-Resolved Airfoil Simulations Using Finite Volume and Discontinuous Galerkin Solvers
Mesh-Resolved Airfoil Simulations Using Finite Volume and Discontinuous Galerkin Solvers
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使用有限体积和不连续伽辽金求解器进行网格解析翼型仿真
DOI：
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发表时间：
2016
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通讯作者：
Zhi Yang
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文献类型：
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作者：
Michael J. Brazell;D. Mavriplis;Zhi Yang
使用传统的二阶精确有限体积非结构化网格求解器和高阶不连续伽辽金求解器来模拟 NACA 0012 翼型上的湍流。使用一系列标准化高密度网格，可以获得网格解析的解决方案。通过求解由负 Spalart-Allmaras 湍流模型封闭的雷诺平均纳维-斯托克斯方程来模拟流动。本例的流动条件为α=10、M=0.15、Re=6×106。为多个网格和离散阶提供了升力、阻力、俯仰力矩、压力和表面摩擦系数，并与众所周知的求解器的其他模拟结果进行比较。当前的模拟给出了与这些基准求解器非常相似的结果，指向完全网格解析的模拟，并提供这些离散化的正确和一致实现的验证证据。使用高阶不连续伽辽金离散化获得的结果显示出使用更少的精度更高的精度...
A traditional second-order accurate finite volume unstructured mesh solver and a high-order discontinuous Galerkin solver are used to simulate turbulent flow over a NACA 0012 airfoil. Using a family of standardized high-density grids, mesh-resolved solutions are obtained. The flow is simulated by solving the Reynolds-averaged Navier–Stokes equations closed by the negative Spalart–Allmaras turbulence model. The flow conditions for this case are α=10, M=0.15, and Re=6×106. Lift, drag, pitching moment, pressure, and skin friction coefficients are provided for multiple grids and discretization orders and are compared against other simulation results from well known solvers. The current simulations give very similar results to these benchmark solvers, pointing toward fully mesh-resolved simulations and providing verification evidence of correct and consistent implementation of these discretizations. Results obtained using the high-order discontinuous Galerkin discretizations show higher accuracy using fewer de...