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首页> 外文期刊>Journal of Aircraft >Computations from the Fourth Drag Prediction Workshop Using the Edge Solver
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Computations from the Fourth Drag Prediction Workshop Using the Edge Solver

机译：使用边缘求解器从第四次阻力预测研讨会进行计算

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摘要

Results carried out for the 4th AIAA Drag Prediction Workshop with the flow solver Edge are summarized. Simulations have been carried out for wing-body-tail configurations with three horizontal tail incidences and for one tail-off configuration. The computations consist of a grid-refinement study and a downwash study with polar calculations to explore the trimmed condition and delta effects. An investigation of the sensitivity to the grid and turbulence model is carried out from calculations on two sets of unstructured grids with three turbulence models, including the explicit algebraic Reynolds stress model, the k-ω SST model, and the Spalart-Allmaras model. The grid-refinement study, for which the flow is attached, shows rather small differences due to different grids and models. The major difference is obtained from the turbulence models where about 10 drag counts between the highest and lowest drag values are predicted, respectively, by the explicit algebraic Reynolds stress model and the Spalart-Allmaras model. The difference between the two sets of grids is only about two drag counts. The polar calculations in the downwash study also show rather small differences in which the same tendency for the drag prediction is observed as in the grid-refinement study. The largest differences between the solutions are due to different turbulence models and observed at the highest angles of attack, where the flow starts to separate after the shock on the wing.
机译：总结了在第四届AIAA阻力预测研讨会上使用流动求解器Edge进行的结果。已经对具有三个水平尾部入射角和一个尾部尾部构造的机翼-尾部构型进行了仿真。计算包括网格细化研究和带有极性计算的下冲研究，以探索修整条件和增量效应。通过对具有三种湍流模型的两组非结构化网格进行计算，研究了网格和湍流模型的敏感性，其中包括显式代数雷诺应力模型，k-ωSST模型和Spalart-Allmaras模型。附加了流量的网格细化研究显示，由于不同的网格和模型，差异很小。主要区别来自湍流模型，其中显式代数雷诺应力模型和Spalart-Allmaras模型分别预测了最高阻力值和最低阻力值之间的大约10个阻力计数。两组网格之间的差异仅约两个拖动计数。向下冲洗研究中的极地计算也显示出很小的差异，其中观察到的阻力预测趋势与网格细化研究中的趋势相同。解决方案之间的最大差异是由于不同的湍流模型，并且在最高迎角上观察到的，在机翼受到冲击后，气流开始分离。

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  • 来源
    《Journal of Aircraft》 |2013年第5期|1646-1655|共10页
  • 作者

    Peter Eliasson; Shia-Hui Peng; Lars Tysell;

  • 作者单位

    Department of Aeronautics and Systems Technology. Swedish Defence Research Agency (FOI), SE-164 90 Stockholm, Sweden;

    Department of Aeronautics and Systems Technology. Swedish Defence Research Agency (FOI), SE-164 90 Stockholm, Sweden;

    Department of Aeronautics and Systems Technology. Swedish Defence Research Agency (FOI), SE-164 90 Stockholm, Sweden;

  • 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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