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首页> 外文期刊>Transactions of the Japan society for aeronautical and space sciences >CFD-Aided Evaluation of Reynolds Number Scaling Effect Accounting for Static Model Deformation
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CFD-Aided Evaluation of Reynolds Number Scaling Effect Accounting for Static Model Deformation

机译：静态模型变形的CFD辅助雷诺数尺度效应评估

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摘要

A static aeroelasticity analysis is accomplished for an ONERA-M5 wind tunnel calibration model. The Reynolds- averaged Navier-Stokes (RANS) solution obtained using the cell-wise relaxation implicit discontinuous Galerkin (DG) computational fluid dynamics (CFD) solver is fed into the structural analysis method to iteratively determine the aerodynamic equilibrium configuration of the wind tunnel model. For the freestream conditions of M = 0.84, a = -1.0°, Re = 4 × 10~6, P_0 = 220 kPa and T_0 = 274 K, the aerodynamic equilibrium shape is successfully obtained within three iterations. The maximum deformation of 3.11 mm appears at the wing tip of the wind tunnel model, and the resulting change in aerodynamic force produces a nose-down effect. A detailed examination reveals that the deformation mostly causes pure bending which reduces the effective angle of attack for the present swept wing. Moreover, we attempt to split the change in aerodynamic coefficients into that due to the model deformation effect and that due to the Reynolds (Re) number effect. By comparing the computed results for Re = 1 x 106 and Re = 4 x 106, it is indicated that an increase in lift coefficient due to the Re number effect is totally offset by the model deformation effect. It is also shown that the amount of drag reduction can be overestimated due to the model deformation effect. In addition, a CFD-aided data correction method utilizing the wind tunnel data is discussed.
机译：对ONERA-M5风洞校准模型进行了静态气动弹性分析。使用基于单元松弛的隐式不连续伽勒金（DG）计算流体力学（CFD）解算器获得的雷诺平均Navier-Stokes（RANS）解输入结构分析方法中，以迭代方式确定风洞模型的空气动力学平衡构型。对于M = 0.84，a = -1.0°，Re = 4×10〜6，P_0 = 220 kPa和T_0 = 274 K的自由流条件，在三个迭代中成功获得了空气动力学平衡形状。 3.11毫米的最大变形出现在风洞模型的机翼尖端，并且由此产生的空气动力变化产生了机头向下的效果。详细检查发现，变形主要导致纯弯曲，从而减小了当前后掠翼的有效迎角。此外，我们尝试将空气动力学系数的变化分为模型变形效应和雷诺数（Re）效应。通过比较Re = 1 x 106和Re = 4 x 106的计算结果，可以看出，由于Re数效应引起的升力系数的增加被模型变形效应完全抵消了。还表明，由于模型变形效应，减阻量可能会被高估。另外，讨论了利用风洞数据的CFD辅助数据校正方法。

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