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Comparison of Numerical Methods Evaluating Airfoil Aerodynamic Characteristics at Low Reynolds Number

机译：低雷诺数下评估翼型气动特性数值方法的比较

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摘要

The flowfields around the NACA 0012 airfoil at Reynolds numbers 1 × 10~4, 3 × 10~4, and 5 × 10~4 are studied, and the predictability of aerodynamic characteristics derived from various numerical methods is examined. Two-dimensional laminar simulation, two-dimensional Reynolds-averaged Navier-Stokes simulation using the Baldwin-Lomax turbulence model, and three-dimensional implicit large-eddy simulation are employed in this study. The two-dimensional laminar and three-dimensional implicit large-eddy simulations accurately predict the separation point, and capture the characteristics of a separation bubble for each Reynolds number and each angle of attack. Nonlinearity in the lift curve is also captured in the results of the two-dimensional laminar and three-dimensional implicit large-eddy simulations. The two-dimensional Reynolds-averaged Navier-Stokes simulation using the Baldwin-Lomax turbulence model predicts the separation point nearer the trailing edge than does the two-dimensional laminar and three-dimensional implicit large-eddy simulations, and the separation bubble is not captured for any Reynolds number and angle of attack by this method. Nonlinearity of the lift curve does not appear in the results of the two-dimensional Reynolds-averaged Navier-Stokes simulation using the Baldwin-Lomax turbulence model. The two-dimensional laminar simulation can predict airfoil aerodynamic characteristics qualitatively, and it can be used as an appropriate numerical method at lower Reynolds numbers. The three-dimensional-implicit-large-eddy-simulation technique can be employed when more accurate qualitative characteristics are needed.
机译：研究了雷诺数分别为1×10〜4、3×10〜4和5×10〜4的NACA 0012机翼周围的流场，并研究了通过各种数值方法得出的空气动力学特性的可预测性。本研究采用二维层流模拟，使用Baldwin-Lomax湍流模型的二维雷诺平均Navier-Stokes模拟以及三维隐式大涡模拟。二维层流和三维隐式大涡模拟可准确预测分离点，并针对每个雷诺数和每个迎角捕获分离泡的特征。二维层流和三维隐式大涡模拟的结果也记录了升力曲线中的非线性。使用Baldwin-Lomax湍流模型的二维雷诺平均Navier-Stokes仿真比二维层流和三维隐式大涡流仿真预测分离点更靠近后缘，并且没有捕获到分离气泡用此方法计算任何雷诺数和攻角。使用Baldwin-Lomax湍流模型对二维雷诺平均Navier-Stokes模拟的结果中未出现升力曲线的非线性。二维层流模拟可以定性地预测翼型的空气动力学特性，并且可以在较低的雷诺数下用作合适的数值方法。当需要更精确的定性特征时，可以采用三维内隐大涡模拟技术。

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  • 来源
    《Journal of Aircraft》 |2015年第1期|296-306|共11页
  • 作者

    DongHwi Lee; Taku Nonomura; Akira Oyama; Kozo Fujii;

  • 作者单位

    University of Tokyo, Sagamihara, Kanagawa 252-5210, Japan;

    Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252-5210, Japan;

    Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252-5210, Japan;

    Japan Aerospace Exploration Agency, Sagamihara, Kanagawa 252-5210, Japan;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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