蔡林峰, 李昊歌, 赵文文, 陈伟芳. 简化三方程转捩模型在高超声速流动中的应用[J]. 空气动力学学报, 2019, 37(6): 945-949. DOI: 10.7638/kqdlxxb-2017.0172
引用本文: 蔡林峰, 李昊歌, 赵文文, 陈伟芳. 简化三方程转捩模型在高超声速流动中的应用[J]. 空气动力学学报, 2019, 37(6): 945-949. DOI: 10.7638/kqdlxxb-2017.0172
CAI Linfeng, LI Haoge, ZHAO Wenwen, CHEN Weifang. Application of simplified three-equation transition model in hypersonic flow[J]. ACTA AERODYNAMICA SINICA, 2019, 37(6): 945-949. DOI: 10.7638/kqdlxxb-2017.0172
Citation: CAI Linfeng, LI Haoge, ZHAO Wenwen, CHEN Weifang. Application of simplified three-equation transition model in hypersonic flow[J]. ACTA AERODYNAMICA SINICA, 2019, 37(6): 945-949. DOI: 10.7638/kqdlxxb-2017.0172

简化三方程转捩模型在高超声速流动中的应用

Application of simplified three-equation transition model in hypersonic flow

  • 摘要: 在雷诺平均方法的基础上,通过耦合k-ω SST湍流模型和间歇因子转捩模型,引入湍流模型和转捩模型的可压缩修正方法,对高超声速平板、双楔、尖锥三类模型边界层转捩流动开展了数值模拟研究。与实验结果的对比分析表明基于压力梯度表征参数Tw=RTΩ/ω的简化三方程转捩模型,能够准确捕捉高超声速平板边界层流动的转捩起始位置、转捩区域长度以及湍流区壁面热流。而对于双楔、尖锥模型,改进前的简化三方程转捩模型由于受到流动可压缩效应的影响,边界层转捩后湍流区的壁面热流模拟预测结果明显高于实验值。在添加模型可压缩修正方法后,转捩区域长度和湍流区壁面热流模拟结果得到有效改善,与实验值吻合较好。可见,简化三方程转捩模型在添加可压缩修正方法后具备准确模拟预测高超声速边界层流动转捩的潜力。

     

    Abstract: On the basis of the RANS model, the numerical simulation study of hypersonic boundary-layer transitional flow was carried out on a flat-plate, a double wedge, and a cone by modifying k-ω SST turbulence model and the intermittency transition model with compressibility correction. Based on the comparison with experimental result, it is shown that the simplified three-equation transition model based on the pressure gradient characterization parameter Tw=RTΩ/ω can correctly catch the transition onset location, the length of transition region, and the turbulent zone heat flux on the wall for the flat-plate hypersonic boundary-layer flow. For the double wedge and cone case, the wall heat flux in turbulent zone calculated by the simplified three-equation transition model is much higher than the experimental data due to the flow compression effects. However, it can agree well with the experimental data after adding compressibility correction to the model. The simplified three-equation transition model with appropriate compressibility correction has potential to simulate hypersonic boundary-layer transitional flow correctly.

     

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