For a realistic and practical aerodynamic optimization the most appropriate combination of the three sets of tools taking part in the process should be carefully studied. That is, the optimization should allow an easy implementation of constraints, and should be multipoint without the need to prescribe pressure distributions in the objective function; the design space should be broad enough; and the analysis tool should be fast and robust. Taking into account these criteria, a code for multipoint design and optimization of wings in subsonic and transonic regime has been developed and will be described in this paper. The objective can be any combination of the global aerodynamic coefficients, and geometrical and physical constraints can be applied. Results for subsonic and transonic cases will be presented. Flexibility in the use of the design variables allows many different tests to be performed before the best solution is achieved. Lastly, the computational cost is reduced by the use of a low level code for computing the aerodynamic coefficients.