Numerical study of leading edge separated flow over wing-canard configuration, with emphasis on aerodynamic coefficients estimation

摘要

A numerical investigation for wing-canard configuration, based on potential flow, and non-linear panel methods, is performed. Flow emanating from leading edges is allowed to separate, with every vortex line represented by a number of segments with the last segment extending to infinity. Effect of canard vertical position, and deflection on the wing loading are investigated. Tapered swept wing with rectangular canard and cropped delta wing with swept canard are considered. the model assumes a simplified geometry with no thickness or camber. Results indicate considerable influence onto the main lifting surface in the presence of the canard.