Abstract
In this work, the effects of corona discharges on a wing and flap system are studied through numerical simulation. The mathematical model, which is used, reproduces the overall phenomenon of boundary layer acceleration and does not intend to model the plasma itself. The model integrates an electro hydrodynamic force, which is a function of the electric charge density of the plasma to the Navier-Stocks equations. The CFD code FLUENT associated with a UDF module is used to solve the equations associated with the mathematical model and perform the simulations. Computations are validated through the turbulent air flow over a flat plate system. Numerical results of the high lift system show a significant increase of the lift coefficients between the angles of attack of 1.8 degree and 6 degree and a delay of the boundary layer separation.