The numerical method for solving Euler equations has been developed in order to determine the steady flow field around individual airfoils plus components. This method uses nonstructured grids made up of triangular elements. Euler's equations in integral form are solved using the finite volume method with unknowns at the centers of gravity of the elements. The integration by time until the stationary state is done with Runge-Kutta of explicit scheme. To speed up the convergence, we used the standard local time-stepping methods, entalphic damping and implicit average of residuals. The attestation of the method made for the test in the subsonic and tran-sonic case.