About the Problem of Two-Element Airfoil Optimization

A numerical solution is presented for the problem of finding an optimal two-element wing airfoil shape with maximum lift coefficient flowed by a subsonic viscous non-separation stream. The solution method is based on the theory of inverse boundary-value problem of aerohydrodynamics for analytical functions. The effects of viscosity and compressibility within the framework of boundary layer theory and the Chaplygin's gas model are taken into account.