This paper presents a numerical investigation on aerodynamic control of integrally-actuated membrane wings made of dielectric elastomers. They combine the advantages of membrane shape adaptability with the benefits of the simple, lightweight but high-authority control mechanism offered by integral actuation. For that purpose, high-fidelity numerical models have been developed to predict their performance. They include a fluid solver based on the direct numerical integration of the unsteady Navier-Stokes equations, an electromechanical constitutive material model and a non-linear three-dimensional membrane structural model. In addition, using the Eigensystem Realization Algorithm, it is obtained a very low order model description of the fully coupled aero-electromechanical system to aid the design of a simple PID control scheme for the feedback control of the wing. The resulting regulator is then implemented in the high-fidelity model and used for the mitigation of flow disturbances.