The static aeroelastic behaviours of a flat-plate forward-swept wing model in the vicinity of static divergence are investigated by numerical simulations and wind tunnel tests. A medium fidelity model based on the vortex lattice method (VLM) and nonlinear structural analysis is proposed to calculate the displacements of the wing structure with large deformation. Follower forces effect and geometric nonlinearity are considered to calculate the deformation of the wing by finite element method (FEM). In the wind tunnel tests, the divergence dynamic pressure is predicted by the Southwell method, and the static aeroelastic displacement is measured by a photogrammetric method. The results obtained by the medium fidelity model calculations show reasonable agreement with wind tunnel test results. A high fidelity model based on coupled computational fluid dynamics (CFD) and computational structural dynamics (CSD) predicts better results of the wing tip displacement when the freestream dynamic pressure is approaching the divergence dynamic pressure.

中文翻译：

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前掠翼模型静态气动弹性行为的实验和数值研究

通过数值模拟和风洞试验研究了平板前掠翼模型在静态发散附近的静态气动弹性行为。提出了一种基于涡格法(VLM)和非线性结构分析的中等保真模型来计算大变形机翼结构的位移。采用有限元法（FEM）计算机翼变形时考虑了从动力效应和几何非线性。在风洞试验中，发散动压采用Southwell法预测，静气弹位移采用摄影测量法测量。中等保真度模型计算获得的结果与风洞试验结果显示出合理的一致性。