| 扩压器进气道内流及激波／边界层干扰的数值研究 |
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| 引用本文： | 刘仪,刘斌.扩压器进气道内流及激波／边界层干扰的数值研究[J].空气动力学学报,1997,15(2):256-260. |
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| 作者姓名： | 刘仪 刘斌 |
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| 作者单位： | 西安交通大学!西安，710049，西安交通大学!西安，710049，西安交通大学!西安，710049 |
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| 摘 要： | 应用隐式矢通量分理解差分格式结合改进的Ｂａｌｄｗｉｎ－Ｌｏｍａｘ湍流模型直接求解时间平均Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程组，对扩压器跨声流动进行了数值计算，准确地捕获了激波，预测了由于强激波作用引起的湍流边界层分离现象，与实验数据比较，结果令人满意。数值实验表明：该方法具有精度高、稳定性好、计算量少、收敛快等优点，计算结果可用于高速飞行器气动特性的研究 。
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| 关 键 词： | 扩压器 激波 边界层 分离 数值方法 航空发动机 |
Numerical Analysis of Transonic Diffuser Flow and Shock/Turbulent Boundary-Layer Interaction |
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| Liu Yi ,Liu Bin, Xiang Yimin.Numerical Analysis of Transonic Diffuser Flow and Shock/Turbulent Boundary-Layer Interaction[J].Acta Aerodynamica Sinica,1997,15(2):256-260. |
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| Authors: | Liu Yi Liu Bin Xiang Yimin |
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| Abstract: | An implicit flux vector splitting scheme, companying with the modified Baldwin-Lomax turbulence model,has been provided to solve the time-average Navier-Stokes equations directly. In the calculation of two-dimensional transonic diffuser, shock wav e is exactly captured, boundary-layer separation induced by shock is also predicted.The results are satis-fied.Numerical calculations detnonstrate clearly that it has obvious super-iorities in aspects of accuracy, robutness, calculation time and convergence.The resulting data can be employed to analyzing of high-speed vehicles aerodynamic characteristics. |
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| Keywords: | diffuser numerical simulation shock waye boundary-layer separation |
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