激波/平板湍流边界层干扰的数值模拟

李志强; 李正强; 闫文辉

激波/平板湍流边界层干扰的数值模拟

北京航空航天大学航空发动机气动热力重点实验室, 北京 100083

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出版历程
- 收稿日期: 2007-05-28
- 修回日期: 2007-09-25
- 刊出日期: 2008-06-28

Numerical simulation of shock wave/flat-plate turbulent boundary-layer interaction

National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 采用理性GAO-YONG可压缩湍流模型,模拟了激波/平板湍流边界层干扰现象,结果表明:计算所得到的壁面压力分布、摩阻系数分布和速度型分布均与实验值吻合很好,并且比较准确地预报出了入射斜激波与平板湍流边界层干扰所引起的边界层分离点和再附点等流动特性.由此表明GAO-YONG可压缩湍流模型能够准确地用来模拟激波/平板湍流边界层的干扰流动.
- 航空、航天推进系统 /
- 平板可压缩流 /
- 激波/湍流边界层干扰 /
- GAO-YONG可压缩湍流模型
Abstract: Rational Gao-Yong compressible turbulence model was used to simulate numerically the shock wave/flat-plate turbulent boundary layer interactions.The results show that the computational results of the pressure distribution along the wall surface,skin-friction coefficient distribution along the wall and the velocity profile distribution along x-coordinate are consistent with the experimental results.And the computational results predict well the flow characteristics of flat-plate turbulent boundary layer separation induced by incident shock wave.Hence,it is shown that when the Gao-Yong compressible turbulence model is applied to simulate the shock wave/turbulent boundary layer interaction,the detailed flow characteristics of shock flows can be well predicted.
- aerospace propulsion system /
- flat compressible fluid /
- shock/turbulent boundary-layer interaction /
- GAO-YONG turbulence mode

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参考文献(15)

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