Modeling the thin flapping wing with leading edge separation

A vortex model of a flapping aerofoil with LE detached vortex sheet is presented. A system of equations, one integral that imposes the boundary condition and other describing the motion of the wakes and vorticity conservation are written. To these one must add the Kutta-like condition and the initial conditions for the wakes. A numerical solution was given that consists of a modified Glauert method in connection with vortex range wake models with finite cores. Mathcad worksheets were written to obtain numerical values and diagrams.