The paper describes the application of Bspline parameterization method on the supercritical airfoil and wing design. Wing section curves and span wise guide lines are generated by Bspline curve fitting and interpolation. Two lofting surfaces and a pointsinterpolation surface were overlaid by CoonsGordon method, and bidirectional curve network on wing surface is interpolated.The aerodynamic characteristics of different loft surfaces were compared with CFD analysis. The research results show Bspline control points are passed to aerodynamic optimization process as design variables, and the Bspline expression can be treated as a linear combination of the design variables, which provides an easy access to the geometry gradient information.