In view of the problem of the static aero elastic divergence of forward-swept wings, based on plasma flow control and fluid-solid two-way interaction technology, the three-dimensional constant compressible N-S equation and structural static balance equation are solved. Under condition of subsonic velocity, the flow field with and without plasma actuation is calculated. The forward-swept wing being NACA0015 airfoil and the plasma actuation area being a phenomenological model, both of them are applied to the leading edge of the upper surface of the wing. The results show that when the plasma actuation is applied to the upper surface of the outer leading edge of the forward-swept wing the local incoming flow in the actuation region is excited, and the work is done by the electric field force. The total energy, the kinetic energy and the pressure potential energy increase to a different degree, whose external manifestation is that the local flow velocity on the upper surface increases and the pressure increases while the lift partly decreases, and the pressure on the lower surface remains basically unchanged. A bow moment is generated near the wing tip on the outside of the leading edge of the wing, which can control the elastic deformation of the forward swept wing. This effectively suppresses the static aero elastic divergence of the forward-swept wing ,and with the increment of excitation intensity, the suppression effect gradually increases. The results give a reference to the aero elastic design of the variable forward-swept wing aircraft and the flow control of the wing.