A modification to the existing hardening function is proposed to reduce the mesh sensitivity of the plastic strain at peak stress.

为了克服峰值塑性应变的网格敏感性，对现有强化函数进行修正。

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The method presented has the feature that the trailing wing edge is aligned with the grid line through modification of the distribution of the mesh points on the wing surface.

本方法的特色是改进了机翼表面网格点的分布，使机翼后缘与网格线一致。

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It improves triangle quality and vertex position distribution by performing a series of adaptive local modification operations on the mesh.

该算法通过对原始网格进行一系列自适应的局部修改操作，改进网格中三角形的质量和顶点位置分布。

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