Effect of Steady Spanwise Blowing on the Aerodynamic Coefficients of a Maneuverable Aircraft Wing Model

In this study, the effect of steady spanwise blowing on the Aerodynamic Coefficients of a Maneuverable Aircraft Wing Model have been simulated in three dimensions and investigated applying the fluent software. The simulations have been performed at the Mach number of 0.4 and different angles of attack, using unstructured grid and the k-w sst turbulent model. Numerical simulation results showed that the spanwise blowing along the wing leading edge caused a flow along the axis of leading edge vortex and delayed the vortex breakdown until the high angles of attack. As a result, the lift coefficient increases at higher angles of attack, which is directly related to the jet momentum coefficient. By applying blowing, due to the vortex breakdown on the wing surface, drag coefficient is greater than no blowing condition until angle of attack 24 degree and after this angle, the drag coefficient decreases. Therefore, drag coefficient decrease lower at greater jet momentum coefficients. By injecting the flow on the wing, the vortex increases in the different longitudinal sections and causes a greater pressure drop on the upper surface of the wing. Also, the greatest amount of pressure in the inner span of the wing and near the edge of the wing attack is observed.