Abstract: A method to calculate nonlinear compressibility effects of airfoils in subsonic flow based on the method of finite elementary solution （MFES） is presented. Using the progressive iterative, the method allows direct extension of MFES to nonlinear inviscid compressible flow. Thus it provides a new approach to the solution of the nonlinear equations.A computer program was completed in FORTRAN IV. The comparison of the results obtained with those of exact and other theoretical solutions shows superiority of this method to the ordinary method of finite difference, especially in the airfoil nose region.