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模型的转捩流动计算分析
引用本文:王刚,王光秋,王光秋,单肖文.模型的转捩流动计算分析[J].航空学报,2014,35(1):70-79.
作者姓名:王刚  王光秋  王光秋  单肖文
作者单位:1. 西北工业大学 翼型叶栅空气动力学国家重点实验室, 陕西 西安 710072;
2. 中国商用飞机有限责任公司 北京民用飞机技术研究中心, 北京 102211
基金项目:西北工业大学基础研究基金(NPU-FFR-JC201212)
摘    要: 为了在黏性流动数值模拟中实现边界层转捩的自动预测,将γ-Reθt转捩模型引入到三维非结构混合网格的雷诺平均Navier-Stokes方程求解程序(HUNS3D)。该转捩模型由两个依赖当地变量定义的关于间歇因子和当地化转捩起始动量厚度雷诺数的输运方程组成,其数值求解算法与流场求解程序中湍流模型的求解方法相同。为了考察和验证HUNS3D程序中γ-Reθt转捩模型对航空工程中的常见附面层自由转捩问题的预测精度,对低速平板流动、Aerospatial-A翼型、NLR 7301超临界翼型和NASA Trap wing 高升力构型等典型外形的自由转捩流动进行了计算,并将计算结果与相关试验结果进行了对比分析。算例结果表明:γ-Reθt转捩模型对于转捩位置具有很好的敏感性,能比较准确地预测自然转捩和分离转捩,可以有效提高HUNS3D程序对实际流动的模拟能力和预测精度。

关 键 词:转捩  边界层  间歇因子  湍流模型  湍流度  

Transitional Flow Simulation Based on γ-Reθt Transition Model
WANG Gang,LIU Yi,WANG Guangqiu,SHAN Xiaowen.Transitional Flow Simulation Based on γ-Reθt Transition Model[J].Acta Aeronautica et Astronautica Sinica,2014,35(1):70-79.
Authors:WANG Gang  LIU Yi  WANG Guangqiu  SHAN Xiaowen
Institution:1. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China;
2. Beijing Aeronautical Science and Technology Research Institute, COMAC, Beijing 102211, China
Abstract:In order to predict the boundary layer transition automatically in viscous flow simulation, γ-Reθt transition model is implemented in a hybrid unstructured Reynolds averaged Navier-Stokes flow solver which was originally developed by the authors and named as HUNS3D. The transition model is built on two locally defined transport equations. The first equation is for intermittency and the second for the transition onset criterion based on momentum-thickness Reynolds number. The numerical algorithms for solving the transition model equations are the same as those for solving turbulence model equations. To validate and assess the ability and the accuracy of the HUNS3D's γ-Reθt transition model in predicting the boundary layer transition in typical aeronautical engineering cases, a series of free transitional flows around typical configurations, including flat plate, Aerospatial-A airfoil, NLR 7301 supercritical airfoil and NASA Trap wing high lift configuration, are simulated and the computed results are compared with corresponding experimental data, which demonstrate that the γ-Reθt transition model is very sensitive to the transition onset location and it predicts the natural transition and separation-induced transition accurately. With this transition model, the performance of the HUNS3D code in simulating the engineeringly realistic flow can be greatly enhanced.
Keywords:transition  boundary layer  intermittency  turbulence model  turbulence intensity
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