低雷诺数下翼型绕流的格子Boltzmann方法数值模拟
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摘要
文章采用混合格子Boltzmann方法模拟NACA0012翼型流场分离,该方法是将标准格子Boltzmann方法与非结构化有限体积方程相结合的一种方法。首先,分析不同网格分辨率下的计算精度;然后,分析了在雷诺数等于103的情况下不同攻角下翼型的气动特性;最后,计算了不同雷诺数下攻角为0°时的翼型流场。结果证明,混合格子Boltzmann方法在固体壁面有较高的计算精度,可以准确地评估翼型绕流流场。
In this paper, hybridlattice Boltzmann method is used to simulate NACA0012 airfoil flow field separation. Hybrid lattice Boltzmann method combines standard lattice Boltzmann method with unstructured finite volume formulation. This paper first analyzes the calculation accuracy under different grid resolutions, and then analyzes the aerodynamic characteristics of the airfoil under different angles of attack when the Reynolds number is equal to 103. Finally, the airfoil flow field with different angle of attack at 0 ° with different Reynolds numbers was calculated. The results show that the hybridlattice Boltzmann method has a high calculation accuracy at wall boundary and can accurately evaluate the flow field around the airfoil.
In this paper, hybridlattice Boltzmann method is used to simulate NACA0012 airfoil flow field separation. Hybrid lattice Boltzmann method combines standard lattice Boltzmann method with unstructured finite volume formulation. This paper first analyzes the calculation accuracy under different grid resolutions, and then analyzes the aerodynamic characteristics of the airfoil under different angles of attack when the Reynolds number is equal to 103. Finally, the airfoil flow field with different angle of attack at 0 ° with different Reynolds numbers was calculated. The results show that the hybridlattice Boltzmann method has a high calculation accuracy at wall boundary and can accurately evaluate the flow field around the airfoil.
引文
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[12]Khalid M,Akhtar I.Characteristics of flow past a symmetric airfoil at low Reynolds number:A nonlinear perspective[J].International Mechanical Engineering Congress and Exposition,2012(7):167-175.
[2]何雅玲,李庆,王勇,等.格子Boltzmann方法的工程热物理应用[J].科学通报,2009,54(18):2638-2656.
[3]Higuera F J,Succi S,Benzi R.Lattice gas dynamics with enhanced collisions[J].Europhysics Letters(EPL),1989,9(4):345-349.
[4]Nannelli F,Succi S.The lattice Boltzmann equation on irregular lattices[J].Journal of Statistical Physics,1992,68(3-4):401-407.
[5]Di Ilio G,Chiappini D,Ubertini S,et al.Hybrid lattice Boltzmann method on overlapping grids[J].Physical Review E,2017,95(1):309-313.
[6]Ubertini S,Bella G,Succi S.Lattice Boltzmann method on unstructured grids:Further developments[J].Physical Review E,2003,68(1):701-716.
[7]Lagrava D,Malaspinas O,Latt J,et al.Advances in multidomain lattice Boltzmann grid refinement[J].Journal of Computational Physics,2012,231(14):82-93.
[8]Filippova O,Hnel D.Grid refinement for lattice-BGKmodels[J].Journal of Computational Physics,1998,147(1):219-228.
[9]Kurtulus D F.On the unsteady behavior of the flow around NACA0012 airfoil with steady external conditions at Re=1 000[J].International Journal of Micro Air Vehicles,2015,7(3):301-326.
[10]Huang R F,Wu J Y,Jeng J H,et al.Surface flow and vortex shedding of an impulsively started wing[J].Journal of Fluid Mechanics,2001(441):265-292.
[11]Liu Y,Li K,Zhang J,et al.Numerical bifurcation analysis of static stall of airfoil and dynamic stall under unsteady perturbation[J].Communications in Nonlinear Science and Numerical Simulation,2012,17(8):3427-3434.
[12]Khalid M,Akhtar I.Characteristics of flow past a symmetric airfoil at low Reynolds number:A nonlinear perspective[J].International Mechanical Engineering Congress and Exposition,2012(7):167-175.