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通过求解Euler方程获得运动翼段的非定常流场,并用CUDA语言对流场求解器进行GPU并行计算.使用ARMA(auto-regressive-moving-average)模型对非定常气动力进行辨识,由系统辨识模型得到的结果与全阶CFD计算结果十分吻合.基于降阶气动模型与结构的耦合,计算了具有S型颤振边界的气动弹性标准算例-Isogai Wing的跨音速颤振.本文给出的方法可以在保证气动弹性计算精度的前提下大幅提高计算效率.
The Euler equation is used to obtain the unsteady flow field of the moving wing segment, and the CUDA language is used to compute the GPU parallelism in the flow field solver. The unsteady aerodynamic force is identified by ARMA (auto-regressive-moving-average) The results obtained by the model are in good agreement with the results of the full-order CFD calculation. Based on the coupling between the reduced-order aerodynamic model and the structure, the transonic flutter of the Sogai Wing with the S-type flutter boundary is calculated. The method can greatly improve the computational efficiency under the premise of ensuring the accuracy of aeroelastic calculation.