航空学报 > 2014, Vol. 35 Issue (11): 2992-2999   doi: 10.7527/S1000-6893.2013.0522

基于当地流动结构的RANS/LES混合模型

徐晶磊1, 高歌1, 杨焱2   

  1. 1. 北京航空航天大学 能源与动力工程学院 航空发动机气动热力 国家科技重点实验室, 北京 100191;
    2. 中国科学院力学研究所 高温气体动力学国家重点实验室, 北京 100190
  • 收稿日期:2013-11-11 修回日期:2014-01-16 出版日期:2014-11-25 发布日期:2014-02-21
  • 通讯作者: 杨焱,Tel.: 010-82543976 E-mail: yangy@ustc.edu E-mail:yangy@ustc.edu
  • 作者简介:徐晶磊 男, 博士, 讲师, 硕士生导师.主要研究方向: 湍流模型, 计算流体力学. Tel: 010-82317403 E-mail: xujl@buaa.edu.cn; 高歌 男, 教授, 博士生导师.主要研究方向: 湍流, 涡动力学, 旋涡动力装置, 真空能. Tel: 010-82317412 E-mail: gaoge45@gmail.com; 杨焱 男, 博士, 助理研究员.主要研究方向: 计算流体力学. Tel: 010-82543976 E-mail: yangy@ustc.edu
  • 基金资助:

    国家自然科学基金 (11002014)

A RANS/LES Hybrid Model Based on Local Flow Structure

XU Jinglei1, GAO Ge1, YANG Yan2   

  1. 1. National Key Laboratory of Science and Technology on Aero-Engines Aero-thermodynamics, School of Energy and Power Engineering, Beihang University, Beijing 100191, China;
    2. State Key Laboratory of High-temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
  • Received:2013-11-11 Revised:2014-01-16 Online:2014-11-25 Published:2014-02-21
  • Supported by:

    National Natural Science Foundation of China (11002014)

摘要:

针对传统雷诺平均Navier-Stokes/大涡模拟(RANS/LES)混合模型固有的RANS和LES区域衔接难题,借鉴Vreman提出的亚格子(SGS)模型,提取其中描述流动状态的判断函数,利用不可压缩槽道湍流标定模型系数,构造了一个新的RANS/LES混合模型.评估算例包括不可压缩槽道湍流、稳态超声速平板边界层、NACA4412翼型绕流和亚临界雷诺数圆柱绕流.该模型作为壁面模化LES,解决了传统RANS/LES方法中速度型偏离对数律(LLM)的缺陷,且拓宽了原Vreman模型在粗糙网格上的适用性,具有较高精度.该模型同时解决了模化应力折损问题,且对大尺度分离流动的模拟精度相较传统的RANS/LES混合模型如脱体涡模拟(DES)有进一步提升.

关键词: 湍流模型, 混合RANS/LES, 大尺度分离, 大涡模拟, 脱体涡模拟

Abstract:

In order to overcome the inherent deficiency of the traditional Reynolds Averaged Navier-Stokes/large eddy simulation (RANS/LES) hybrid model, i.e., 'the bridging problem of RANS and LES', a discriminating function extracted from Vreman's subgrid-scale (SGS) model, which is used to describe flow regimes, is employed to formulate a new RANS/LES hybrid model. The model coefficients are calibrated by incompressible turbulent channel flows. The test cases include incompressible turbulent channel flows, stable-state supersonic boundary layers over a flat plate, flow past NACA4412 airfoil and flow past a circular cylinder at subcritical Reynolds numbers. This new model is not only able to solve the modeled-stress-depletion problem, but also greatly raises the accuracy when compared with the traditional RANS/LES hybrid approach, such as detached eddy simulation (DES) in predicting large-scale unsteadiness. Furthermore, the model can also solve the log-layer mismatch (LLM) problem when RANS/LES hybrid is employed as wall modeled LES, thus extending the ability of Vreman's LES model in dealing with coarse meshes. The accuracy is greatly improved.

Key words: turbulence model, hybrid RANS/LES, large-scale separation, large eddy simulation, detached eddy simulation

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