ACTA AERONAUTICAET ASTRONAUTICA SINICA >
An Efficient Numerical Method for Coupling the RANS Equations with Spalart-Allmaras Turbulence Model Equation
Received date: 2012-10-30
Revised date: 2013-01-04
Online published: 2013-05-23
Supported by
National Natural Science Foundation of China (11172070);Graduates' Innovation Foundation of Fudan University (EYH2126022)
In engineering practice, the system of the one- or two-equation turbulence model together with Reynolds-averaged Navier-Stokes (RANS) equations is decoupled during its solving, which is known as loosely coupled solving. In the process, RANS equations and turbulence model equations are commonly solved separately with different numerical methods, which may easily incur additional numerical dissipation due to inconsistent calculation accuracy. In order to eliminate this dissipation, RANS equations and Spalart-Allmaras model equation are hereby coupled into one strongly coupled system of equations, and an efficient method is developed for its solution. The convective terms are discrete by the Roe scheme, and the time derivative terms are discrete by the LU-SGS (Lower-Upper Symmetric-Gauss-Seidel) method. In order to accelerate the convergence, a three level V-cycle multigrid algorithm is used. Through numerical experiments of the airfoil/wing and oscillating airfoil/wing, the convergence and accuracy of this algorithm are verified, and results show that its accuracy is significantly better than the loosely coupled algorithm, especially in the prediction of drag force.
YANG Xiaoquan , YANG Aiming , SUN Gang . An Efficient Numerical Method for Coupling the RANS Equations with Spalart-Allmaras Turbulence Model Equation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(9) : 2007 -2018 . DOI: 10.7527/S1000-6893.2013.0056
[1] Kunz R F, Lakshminarayana B. Stability of explicit Navier-Stokes procedures using k-ε and k-ω algebraic Reynolds stress turbulence models. Journal of Computational Physics, 1992, 103(1): 141-159.
[2] Liu F, Zhang X. A strongly coupled time-marching method for solving the Navier-Stokes and k-ω turbulence model equations with multigrid. Journal of Computational Physics, 1996, 128(2): 289-300.
[3] Barakos G, Drikakis D. Implicit unfactored implementation of two-equation turbulence models in compressible Navier-Stokes methods. International Journal for Numerical Methods in Fluids, 1998, 28(1): 73-94.
[4] Lee S, Choi D W. On coupling the Reynolds-averaged Navier-Stokes equations with two-equation turbulence model equations. International Journal for Numerical Methods in Fluids, 2006, 50(2): 165-197.
[5] Yang J, Hsieh T, Wang C. Implicit weighted essentially nonoscillatory schemes with antidiffusive flux compressible viscous flows. AIAA Journal, 2009, 47(2): 1435-1444.
[6] Huang J, Lin H, Yang J. Implicit preconditioned WENO scheme for steady viscous flow computation. Journal of Computational Physics, 2009, 228(2): 420-438.
[7] Jahangirian A, Hadidoolabi M. An implicit solution of the unsteady Navier-Stokes equations on unstructured moving grids. ICAS-24, 2004.
[8] Spalart P R, Allmaras S R. A one-equation turbulence model for aerodynamic flows. La Recherche Aerospatiale, 1994, 1(1): 5-21.
[9] Yoon S, Jameson A. A multigrid LU-SSOR scheme for approximate Newton iteration applied to the Euler equations. NASA-CR-179524, 1986.
[10] Roe P L. Approximate Riemann solvers, parameter vectors and difference schemes. Journal of Computational Physics, 1981, 43(2): 357-372.
[11] Harten A, Hyman J M. Self adjusting grid methods for one-dimensional hyperbolic conservation laws. Journal of Computational Physics, 1983, 50(2): 235-269.
[12] van Leer B. Towards the ultimate conservative difference scheme, V. A second order sequel to Godunov's method. Journal of Computational Physics, 1979, 32(1): 101-136.
[13] Yang A M, Yang X Q. Multigrid acceleration and chimera technique for viscous flow past a hovering rotor. Journal of Aircraft, 2011, 48(2): 713-715.
[14] Yang X Q, Yang A M, Weng P F. The mltilgrid method in Euler equation computation about a helicopter rotor in hover. Acta Aerodynamica Sinica, 2009, 27(5): 608-615. (in Chinese) 杨小权, 杨爱明, 翁培锋. 悬停旋翼无黏流场数值模拟中的多重网格方法. 空气动力学学报, 2009, 27(5): 608-615.
[15] Cook P H, McDonald M A, Firmin M C P. Aerofoil RAE 2822 pressure distributions and boundary layer and wake measurements. AGARD-AR-138, 1979.
[16] Schmitt V, Charpin F. Pressure distributions on the ONERA-M6-Wing at transonic mach numbers, experimental data base for computer program assessment. AR-138-B1, 1979.
[17] Landon R H. NACA0012 oscillatory and transient pitching. AGARD-R-702, 1982.
[18] Zwaan R J. Lann wing pitching oscillations, compendium of unsteady aerodynamic measurements. AGARD-R-702, 1985.
[19] Luo H, Joseph D, Rainald L. An accurate, fast, matrix-free implicit method for computing unsteady flows on unstructured grids. Journal of Computational Physics, 2001, 30(2): 137-159.
[20] Yang X Q, Cheng S K, Yang A M, et al. Time spectral method for numerical simulation of unsteady viscous flow over oscillating airfoil and wing. Acta Aeronautica et Astronautica Sinica, 2013, 34(4): 787-797. (in Chinese) 杨小权, 程苏堃, 杨爱明, 等. 基于时间谱方法的振荡翼型和机翼非定常黏性绕流数值模拟. 航空学报, 2013, 34(4): 787-797.
/
〈 | 〉 |