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Computations of Turbulent Flow over a Sharp Fin at Mach 5

机译：5马赫锐翅片上湍流的计算

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摘要

Reynolds-averaged Navier-Stokes simulations were carried out for sharp fin-induced shock wave/turbulent boundary-layer interactions at Mach 5. Calculations were executed for two fin angles of attack, with each case employing four turbulence models. The computational results were compared with vetted experimental data. For all the cases considered, the calculations replicated the experimentally observed flow structure, which is primarily determined by inviscid, rotational flow effects. Predictions of parameters dominated by viscous effects tended to be less accurate. The predictions of the different turbulence models were qualitatively consistent, but the predicted peak skin friction and wall heat flux varied by as much as a factor of two between the models. The discrepancies between computation and experiment are believed to be a result of large-scale unsteadiness and three dimensionality, which are not captured well by conventional turbulence models.
机译：对由马赫数为5的尖锐鳍引起的激波/湍流边界层相互作用进行了雷诺平均Navier-Stokes模拟。计算了两个鳍迎角，每种情况下使用四个湍流模型。计算结果与经过审核的实验数据进行了比较。对于所有考虑的情况，计算结果都重复了实验观察到的流动结构，这主要是由无粘性的旋转流动效应决定的。以粘性效应为主的参数预测往往不太准确。不同湍流模型的预测在质量上是一致的，但是在模型之间，预测的峰值皮肤摩擦和壁热通量相差多达两倍。据信，计算和实验之间的差异是大规模不稳定和三维的结果，而常规湍流模型无法很好地捕获这些差异。

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  • 来源
    《Journal of Thermophysics and Heat Transfer》 |2016年第2期|394-402|共9页
  • 作者

    Leger Timothy; Bisek Nicholas; Poggie Jonathan;

  • 作者单位

    US Air Force, Res Lab, Ohio Aerosp Inst, Wright Patterson AFB, OH 45433 USA;

    US Air Force, Res Lab, Hyperson Sci Branch, Wright Patterson AFB, OH 45433 USA;

    US Air Force, Res Lab, Hyperson Sci Branch, Wright Patterson AFB, OH 45433 USA|Purdue Univ, Sch Aeronaut & Astronaut, W Lafayette, IN 47907 USA;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);美国《生物学医学文摘》(MEDLINE);
  • 原文格式 PDF
  • 正文语种 eng
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