Numerical method of static aeroelastic correction and jig-shape design for large airliners

• DOI: 10.1007/s11431-012-4936-0
• Publication Date: 2012-07-16T09:22:03Z
• Authors: Wei Huang; ZhiLiang Lu; TongQing Guo; Fei Xue; Miao Zhang
• Keywords: Aeroelasticity; Flexibility method; Interpolation; Aerodynamic force

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.