TRIP2．0软件湍流模块的开发与确认

基于TRIP2.0_SOLVER数值模拟软件,开发了湍流模型方法库,目前该CFD软件中集成的湍流模型主要包括B-L代数湍流模型、SA一方程模型和SST两方程模型.为了考核不同的湍流模型工程适用性,本文采用对接网格技术,通过有限体积法数值离散三维任意坐标系下的RANS方程组,应用LU分解、MUSCL差分格式和低雷诺数SA和SST两种湍流模型,数值模拟了二维NLR-7301两段翼型和三维DLR-F6翼身组合体的绕流流场,计算与试验比较的内容包括了表面的压力系数分布、典型站位的速度型和气动特性曲线等内容.通过计算与试验的比较,在本文的计算范围内,采用两种湍流模型均可以得到与试验结果相吻合的压力分布和升力曲线,但在边界层内的速度型、粘性阻力和力矩特性等方面,不同的湍流模型具有明显的差异.

Development and Validation of Turbulence Models of TRIP2.0

Based on CFD codeTRIP2.0_SOLVER,engineering turbulence models have been developed,which include Baldwin-Lomax algebraic model,low Reynolds number Spalart-Allmaras one equation models and Menter SST two equation model.In order to validate various turbulence models involved,adopting finite volume methods to discrete Reynolds averaged Navier-Stokes equation in arbitrary coordinates,LU-SGS and MUSCL difference scheme to solving the discrete equations,two-element NLR-7301 airfoil and DLR-F6 wing-body configuration are simulated in present paper.Pressure distribution,velocity profiles and aerodynamics characters are compared between test data and numerical results.In the scope of this paper,lift coefficients and pressure distribution,obtained with SA and SST models,are in good consistency with test data,whereas velocity in boundary layer,skin friction and moment characters show disagreement between various turbulence models and test data.