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In this paper,a coupled CFD-CSD method based on N-S equations is described for static aeroelastic correction and jig-shape design of large airliners.The wing structural flexibility matrix is analyzed by a finite element method with a double-beam model.The viscous multi-block structured grid is used in aerodynamic calculations.Flexibility matrix interpolation is fulfilled by use of a surface spline method.The load distributions on wing surface are evaluated by solving N-S equations with a parallel algorithm.A flexibility approach is employed to calculate the structural deformations.By successive iterations between steady aerodynamic forces and structural deformations,a coupled CFD-CSD method is achieved for the static aeroelastic correction and jig-shape design of a large airliner.The present method is applied to the static aeroelastic analysis and jig-shape design for a typical large airliner with engine nacelle and winglet.The numerical results indicate that calculations of static aeroelastic correction should employ tightly coupled CFD-CSD iterations,and that on a given cruise shape only one round of iterative design is needed to obtain the jig-shape meeting design requirements.
In this paper, a coupled CFD-CSD method based on NS equations is described for static aeroelastic correction and jig-shape design of large airliners. The wing structural flexibility matrix is analyzed by a finite element method with a double-beam model. The viscous multi-block structured grid is used in aerodynamic calculations. Flexibility matrix interpolation is fulfilled by use of a surface spline method. The load distributions on wing surface are evaluated by solving NS equations with a parallel algorithm. deformations.By successive iterations between steady aerodynamic forces and structural deformations, a coupled CFD-CSD method is achieved for the static aeroelastic correction and jig-shape design of a large airliner. The present method is applied to the static aeroelastic analysis and jig-shape design for a typical large airliner with engine nacelle and winglet. numerical results indicating that calculations of static aer oelastic correction should employ tightly coupled CFD-CSD iterations, and that on a given cruise shape only one round of iterative design is needed to obtain the jig-shape meeting design requirements.