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首页> 外文期刊>Aerospace science and technology >Supercritical wing design based on airfoil optimization and 2.75D transformation
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Supercritical wing design based on airfoil optimization and 2.75D transformation

机译：基于机翼优化和2.75D变换的超临界机翼设计

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An optimization design method for a supercritical wing is developed in this paper based on a pressure distribution transformation between the airfoil and wing. This transformation takes the stream-wise variation of the local sweep angle and the local curvature of a tapered swept wing into account. With this method, the desired pressure distribution of the wing, which is critical to its supercritical characteristics, as well as the constraints and objectives, can be mapped onto a 2D airfoil. When the airfoil is optimized, the desired performances and the pressure distributions can be well realized on a 3D wing. Test cases based on the RAE2822 airfoil and on the common research model are used to validate the CFD tool and the transformation. A supercritical wing is then designed using this method. Comparisons between the results from the proposed method, an optimization based on the traditional transformation and a fully 3D wing optimization are conducted. These comparisons show that the proposed method, by essentially performing 2D optimization, greatly improves the design efficiency. Moreover, the more accurate transformation helps make the optimization more reliable and engineering applicable. (C) 2016 Elsevier Masson SAS. All rights reserved.
机译：基于翼型与机翼之间的压力分布转换，提出了一种超临界机翼的优化设计方法。这种转换考虑了局部后掠角和锥形后掠翼的局部曲率的沿流向变化。通过这种方法，可以将对机翼的超临界特性至关重要的所需机翼压力分布以及约束和目标映射到二维机翼上。当优化翼型时，可以在3D机翼上很好地实现所需的性能和压力分布。基于RAE2822机翼和通用研究模型的测试用例用于验证CFD工具和转换。然后使用这种方法设计超临界机翼。比较了所提出的方法，基于传统变换的优化和完全3D机翼优化的结果。这些比较表明，所提出的方法通过实质上执行2D优化，大大提高了设计效率。此外，更准确的转换有助于使优化更可靠并在工程上适用。 （C）2016 Elsevier Masson SAS。版权所有。

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