An efficient methodology for multi-disciplinary design and optimization of transport was elaborated and developed. The methodology was implemented in a commercial known optimization framework. Semi-empirical methods were employed for wing weight estimation; a multi-block full-potential code was used for drag calculation; Vortex Lattice method was implemented for spanwise lift distribution in order to compute de aircraft maximum-lift coefficient via critical section method; a calibrated single-point Breguet simplified equation was considered for aircraft performance calculation. The optimization design variables are related to the wing planform and airfoil 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 optimal configurations. Multi-objective optimization tasks were performed accomplishing minimization of the block time and block fuel for a specified mission.