Wing optimization for static aeroelastic effect

Abstract An aeroelastic analysis module based on the VLM model and FE model with non-linear static analysis was developed to calculate the lift and deformation of a wing in a cruise case. The traditional static aeroelastic analysis method focuses on compensation of loss of lift by adjusting wing root AoA (angle of attack). To improve the aeroelastic property, integrated static aeroelastic optimization was developed, which compensates for the loss lift by adjusting a series of sectional AoA instead of only wing root AoA. Compared with traditional static aeroelastic analysis, the manufacture wing optimized by integrated static aeroelastic optimization is closer to the initial design wing.