Next generation tactical missiles will include flight profiles from subsonic to hypersonic speeds and very high Angle-of-Attack (AOA) conditions at subsonic-transonic speeds. These conditions result in two critical design requirements for the control fins: (a) increased control authority at high AOA and superior maneuverability to successfully engage the target; and (b) minimum hinge moments over the complete mission profile to improve efficiency, performance and range by reducing actuator size/power and missile weight. However, the increased fin normal force requirement (a) may result in excessive hinge moments defying requirement (b). Thus, a design compromise must be sought which best satisfies both requirements. A two-step sequential optimized fin design procedure is proposed. Step one will utilize the NEAR OPTMIS missile shape optimization software and CFD to design a rigid fin planform with enhanced control authority which maximizes normal force and maintains positive aerodynamic force slope for the control fin at high AOA and deflection angle. Step two will employ the integrated ASTROS*/CFD aeroelastic tailoring methodology to minimize fin hinge moments while maintaining the improved controllability. Composite fins will be designed, fabricated and wind-tunnel tested covering all critical flight conditions. Design solutions will be validated with the test data.