刚性变弯度机翼设计及低速风洞试验研究

Aircraft wing variable camber technology can adjust wing camber in real time to improve flight efficiency, and adapt to complex and changeable mission environment, it is considered as one of the future aviation technology study directions. Here, considering the current technology maturity and reliability, a rigid variable camber wing composed of four rigid wing boxes was designed. The variable camber wing could have characteristics of complex structure and difficult to accurately model. In its preliminary design stage, combining simulation calculation and wind tunnel tests was needed to perform the study. Firstly, the aerodynamic force calculation software XFOIL was used to do simulation calculation for rigid variable camber wing. Then, the wind tunnel test platform for variable camber wing was designed, and the testing acquisition system was built to conduct low-speed wind tunnel tests for rigid variable camber wing. Finally, the simulation calculation and wind tunnel tests results showed that the rigid variable camber wing proposed here as a design scheme of variable camber wing can have simple and reliable structure and remarkable deformation effect, and have advantages in increasing lift and reducing drag to ensure high lift-drag ratio and providing wing trim torque; the wind tunnel test platform designed here is reliable in structure and easy to operate, the average relative error between test value and simulated value is less than 15%, so this platform can correctly reflect effects of rotating angle variation on aerodynamic force of rigid variable camber wing, and provide a verification means for development of design method and future actual aircraft design.