A coupled aero-structural optimization framework for the design of a mission adaptive airfoil is presented. A two-dimensional linear finite element solver and a constant strength doublet flow solver, along with a load-transfer and mesh displacement scheme constitute the fluid-structure interaction system. The morphing airfoil configuration is synthesized by concurrent consideration of both aerodynamic and structural design objectives. A topology optimization sub-problem is solved for the conceptual design of an internal compliant mechanism that morphs the airfoil shape based on different cl requirements. A three-dimensional flow-field analysis using high-fidelity RANS-based simulations indicates that the mission adaptive airfoil configurations outperform a baseline NACA 0012 airfoil at all design points. Instantaneous flow-field characterization in the trailing edge region shows the evolution of distinct asymmetric flow features as the design cl increases.