Investigating the Effect of Moving Surface on NACA 0012 Airfoil in High Speed Ratio

The design and development of high-performance airfoils is essential for the development of the aviation industry. At larger angles of attack, higher lift and shorter flight bands are achieved. But at high angle of attack, the phenomenon of flow separation occurs so that after the stall angle, the flow is completely separated from the upper surface of the wing, resulting in a sharp drop in lift and drag increase. In this study, an attempt has been made to prevent the separation of flow by using the moving surface in the ratio of high velocities on NACA 0012 airfoil and to improve the aerodynamic performance of NACA 0012 airfoil by increasing the lift force and reducing the drag force. The velocity ratio means the ratio of the moving surface velocity to the free flow velocity. This research was performed by numerically in two dimensions using Ansys Fluent and k-ω-SST turbulence model with SIMPLE algorithm. The use of a moving surface in the form of a rotating cylinder at the leading edge of the NACA 0012 airfoil at a high speed ratio, in addition to preventing current separation and increasing the lift, has negatively affected the drag, which indicates its propulsive force contribution. Of all the simulated states, the velocity ratio of 20 at attack angle of 24 with a lift coefficient of 3.564 and a drag coefficient of -0.185 had the most favorable aerodynamic performance.