In the paper, the author presents a certain approach to interpretation of surface vorticity distribution on the airfoil surface, which leads to reduction of computational cost of surface vorticity distribution method (SYM). Some examples of the calculations are shown, and the results compared with solutions based on conformal mapping method as well as with experimental data. The calculations were done employing linear vortex distributions on each panel. The Neuman boundary condition was established at the collocation points. An unloaded trailing edge Kutta-Joukowski condition was applied in the present work. The interpretation of continuous vorticity distribution at the airfoil surface made it possible to reduce the number of panels on airfoil surface, and a satisfactory accuracy was maintained. In these circumstances one can do the calculations even by means of a programmable calculator.