This paper presents a wing aerostructural optimization framework based on the Indi- vidual Discipline Feasible (IDF) architecture. Using the IDF architecture the aerodynamic and the structure disciplines are decoupled in the analysis level and the optimizer is re- sponsible for the consistency of the design. The SU2 CFD code is used for the aerodynamic analysis and the FEMWET software is used for the structural analysis. The SU2 code is modi_ed in a way to receive the structural deformation as inputs and compute the sensi- tivity of the outputs, e.g. drag, with respect to the deformation. An Airbus A320 type aircraft is used as a test case for the optimization. A reduction of the aircraft fuel weight of 11% is achieved. This reduction was attained by increasing the wing span, reducing the wing sweep, improving the lift distribution and improving airfoil shapes.