The main focus of this research is the generation of a computational aeroelastic model for a macrofiber composite actuated micro air vehicle. Two M8528-P1 actuators were used to deform the surface of a forward-swept thin, compliant composite wing. The general approach, which included MATLAB, ABAQUS, and Athena Vortex Lattice, is described. The planform design and initial flight testing are discussed. The computational model was validated first with static tests, and then quasi-static wind-tunnel tests were used to validate the aeroelastic model. Digital image correlation was used to compare the expected and measured displacements of the wing. Flight loads were also compared for various angles of attack. The results indicated good agreement for angles of attack well within the standard flight envelope, despite small discrepancies in geometry.