Abstract
Aerodynamic characteristics of asymmetrically wing tip damaged aircraft have been investigated experimentally, numerically and analytically. This study is aimed to simulate unexpected airframe damage during flight such as a bird strike. Wind tunnel studies were conducted at a Reynolds number of 4.83 × 105 based on a wing mean aerodynamic chord. The results indicated decreases in lift and drag, increases in pitching moment and rolling moment for the wig tip damaged configuration. Good agreement between wind tunnel experiments and numerical simulations was observed. Further studies based on a vortex lattice method and a lifting line theory were also conducted. It was confirmed that the observed rolling moment increase is caused by the lift loss of the wing tip damage. Furthermore, a distinctive feature of yawing moment decrease for the wing tip damaged configuration was observed both by the wind tunnel study and the numerical simulation. The vortex lattice method and the lifting line theory confirmed that this yawing moment decrease is caused by the movement of wing center line due to the reduced wing span length.
