用GAO-YONG湍流模式对翼型跨音粘流的数值模拟

Numerical simulation of airfoil transonic viscous flow using GAO-YONG turbulence model

应用GAO-YONG可压缩湍流模式,数值模拟了NACA0012,RAE2822翼型的定常跨音速粘流算例.对流项采用三阶ROE格式,扩散项采用二阶中心格式,用多步Runge-Kutta显式时间推进法求解空间离散后的控制方程.计算结果很好地预测了翼型表面的压力系数的分布、激波的位置、马赫数等值线的分布等情况,并且对翼型表面激波与边界层相互干扰以及层流向湍流的转捩问题进行了分析计算.计算结果与实验值符合很好,表明GAO-YONG可压缩湍流模式应用合适的计算方法能够高精度模拟翼型跨音粘性流动问题,并且基于GAO-YONG可压缩湍流模式各向异性湍流粘性的机理,提供了一种预测转捩起始位置的判别方法.

Numerical simulation of transonic viscous flow around NACA0012 airfoil and RAE2822 airfoil based on Gao-Yong compressible turbulence model were presented. The convection term and the diffusion term were discretized by the third-order ROE scheme and the second-order center difference（CD） scheme respectively. The Runge-Kutta time marching method was applied to solve the space discrete control equations. The calculations accurately predict distribution of pressure coefficient on the airfoil surface, location of shock wave and distribution of contour of the Mach number. Shock-wave/boundary layer interaction and translation from the laminar flow to the turbulence flow on the airfoil surface were analyzed. The numerical results agree with the experimental data very well. The results demonstrate that Gao-Yong compressible turbulence model has a powerful capability to accurately simulate transonic viscous flow around the airfoil. A method for forecasting location of translation based on theory of orthotropic turbulence viscosity in the Gao-Yong compressible turbulence model was presented.