一种刚柔混合弦向变弯度机翼后缘设计

In order to realize the continuously chord-wise camber change of a wing under driving control, with material deformation ability considered,, an airfoil with hybrid (rigid-flexible) variable trailing edge is proposed. Through the geometric analysis of the mean camber line of the trailing edge, the parametric model of variable camber configuration is established. Taking lift-drag ratio as the optimization objective, the optimal bending angle of the rigid section and the optimal curve of the flexible section are calculated. The lift coefficient, lift-drag ratio and other aerodynamic characteristics of the rigid-flexible airfoil and traditional rigid airfoil are compared at different angles of attack by CFD calculation. When the lift required by the unit span during cruise is taken as the optimization objective, the bending angles and deformation modes of two different trailing edge airfoils are solved respectively in low-speed cruise condition and landing condition. The pressure distribution, velocity distribution and separation position of the two bending forms are compared. A wing model with rigid-flexible variable trailing edge based on the optimized configuration is fabricated and the deformation capability testing is conducted. The results show that: the rigid-flexible trailing edge airfoil has higher lift coefficient, lift-drag ratio and better aerodynamic characteristics in same deflection angle; in the same flight condition, the rigid-flexible trailing edge airfoil has a smaller deflection angle and a more backward separation point, so it has a higher aerodynamic efficiency. The rationality of the flexible wing rib structure and skin design has been verified through deformation capability testing.