Abstract: The method consists of wing geometry and grid generation,transonic full potential solver and numerical optimization algorithm,etc. An especial perturbation technique of curve fitting shape function is applied for variation of the wing shape. Numerical test indicated that it only needed to perturb the ordinates of two spline support points located at the section of the middle semispan of the wing. An aerodynamically satisfactory optimization solution can be obtained,grealty saving the CPU time.