NACA4412翼型低速绕流数值计算中湍流模型对比

doi:10.7527/S1000-6893.2017.721515

Abstract

Abstract:

Numerical simulation of the flow around the NACA4412 airfoil is implemented based on Spalart-Allmaras (S-A), SST k-ω and Gao-Yong turbulence models. In our procedures, convection terms and diffusion terms are calculated using Roe scheme and center difference scheme respectively. The Runge-Kutta time marching method is employed to solve space discrete control equations. The flow relaxation effect at the NACA4412 airfoil trailing edge is analyzed with the models. The pressure distribution on the wall surface, velocity profile distribution and Reynolds stress distribution obtained with the three models are compared. The numerical results obtained using the three turbulence models agree with the experimental data well in general. SST k-ω turbulence model gets the best flow details and lift coefficient. The Gao-Yong turbulence model can simulate most accurately for mean velocity profiles and Reynolds shear stress.

Key words: turbulence model, computational fluid dynamics, numerical simulation, flow around airfoil, relaxation effect

CLC Number:

V211.3

YAN Wenhui, XUE Ranran. Comparison of turbulence models for numerical simulation of low-speed flow around NACA4412 airfoil[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(S1): 721515-721515.

References

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Comparison of turbulence models for numerical simulation of low-speed flow around NACA4412 airfoil

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