Abstract: Flutter of a three-dimensional fixed-wing due to external stores was studied. Modeling of the structure was accomplished using equivalent plate solution (ELAPS) where the geometries of the wing were expressed as polynomials. The Ritz method approximates the displacement fields by polynomials whose unknown coefficients were determined by solving Lagrange's equation of motion. Mass and stiffness matrices as well as natural modes and frequencies were obtained from the solution of the equations of motion. Aerodynamic modeling was achieved using three-dimensional doublet-lattice method (DLM). DLM calculates the lifting pressure distribution on oscillating surfaces in compressible subsonic flow. Aerodynamic forces obtained from DLM were transformed from the frequency-domain into time-domain using a rational function approximation called Roger's Approximation. Finally, flutter analysis was conducted using normal mode method where the motion of the structure was assumed to consist of a superposition of a finite number of normalized mode shapes. The equations of motion lead to an ordinary differential equation where the stability of the system is determined by the complex eigenvalues of the determinant. Flutter suppression was implemented using the unique stiffness and damping properties of shape memory alloys. Shape memory alloys exhibit pseudo-elastic behavior through a rearrangement of the atomic lattice to accommodate the applied stress. This reversible mechanism of 'twin boundary motion' recovers 100% strains via a hysteresis loop. The area enclosed by the hysteresis loop represents the energy absorbed by the material; that is, its damping capacity. The hysteretic loss coefficient of the material is directly related to the equivalent modal damping coefficient, ζ and can be included in the equations of motion as structural damping. An example of a cantilevered wing was presented. The flutter boundary of the bare wing was compared to experimental results and was in excellent agreement, validating the analytical methods used in this research. External stores were then added to the wing, resulting in a reduced flutter velocity. A layer of the shape memory alloy Ni-Ti (nickel-titanium) was then laminated to the top and bottom surfaces of the wing and the flutter velocity was determined. The results of this research indicate that applying Ni-Ti material on a fixed-wing carrying external stores can increase the flutter velocity of the wing to the bare wing flutter velocity, alleviating the effects of the addition of the external stores.