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基于雷诺平均N-S方程和多块结构网格技术计算大展弦比机翼的气动力.机翼采用梁模型结构,利用有限元方法计算结构变形.建立基于多点约束(MPC,Multi-Point Constrain)的气动、结构数据的双向传递方法.采用MPC数据插值方法快捷地实现自主研发的计算流体力学(CFD,Computational Fluid Dynamics)程序和NASTRAN计算结构力学(CSD,Computational Structural Dynamics)软件的耦合计算,发展出可以考虑结构非线性的静气动弹性CFD/CSD耦合计算方法,该方法比只考虑单方向变形的柔度法更精确.开展了某大展弦比机翼的静气动弹性数值计算分析,结果显示只考虑机翼纵向变形而忽略展向变形对计算结果会有一定影响,而该算例几何非线性影响较小.
Based on the Reynolds-averaged Navier-Stokes equations and the multi-block grid technique, the aerodynamic forces of a large aspect ratio airfoil were calculated.The beam model structure was used to calculate the structural deformation using finite element method.Multi-point Constraint (MPC) ) Method, the MPC data interpolation method is used to quickly and easily realize the coupling calculation of Computational Fluid Dynamics (CFD) program and NASTRAN Computational Structural Dynamics software, Developed the static-dynamic elastic CFD / CSD coupling calculation method which can consider the structural nonlinearity, which is more accurate than the flexibility method that only considers unidirectional deformation.A numerical simulation analysis of the static aerodynamic elasticity of a large aspect ratio airfoil is carried out, The results show that considering the longitudinal deformation of the wing and disregarding the span deformation will have some influence on the calculation results, and the geometrical nonlinearity of this example has less influence.