Approximate method to estimate non-linear aerodynamical parameters of the wing itself and with regard for frame influence

The method enabling to determine approximately the wing aerodynamic parameters on subsonic flight velocities, is considered. The method is based on using the experimental data for airfoil characteristics with their further recalculation on a finite wing. Such approach actuality is explained by saving means and time when solving applied problems connected with enhancing the efficiency of the carrying and control surfaces.