An efficient framework for multi-disciplinary design and optimization of transport aircraft was elaborated and developed. Semi-empirical methods were employed for wing weight estimation; a multi-block full-potential code was used for drag calculation and maximum-lift coefficient estimation; a calibrated single-point Breguet simplified equation was considered for aircraft performance calculation. The optimization design variables are related to the wing planform geometry and cruise speed. The design constraints were the fuel tank capacity, flight quality of the aircraft, and takeoff field length. A simple stability augmentation control system was implemented in order to compute its effects on the optimal configurations. Multi-objective wing optimization cases were performed accomplishing minimization of the block time and block fuel for a given mission.