A finite-difference relaxation method is used for numerical solution of consevative type 3-Dsteady full potential equation. Computations give the results for wing performance included surface pressure distribution, force and moment coefficients. In the computation, Joukowsky tranform,successive line over-relaxation (SLOR) scheme of Jameson and multigrid technique are used. Test runs for ONERA M6 wing coinside with satisfaction to other computational results and experimental data.