THE EFFECTS OF CYLINDER AT THE LEADING EDGE OF AIRFOIL NACA 0012 ON THE BOUNDARY LAYER SEPARATION

The study of boundary layer separation control using cylinder based at the leading edge of airfoil NACA 0012 was carried out in this research. The experimental work have been done using wind tunnel with air flow velocity 24 m/s, and with airfoil NACA 0012 at angles of attack (0°, 5°, 10°, 14° and 20°) respectively. The pressure distribution around airfoil NACA 0012 was measured at each above angles of attack to calculate lift and drag coefficients with and without circular cylinder at the leading edge of this airfoil. The visualization of flow around and behind the airfoil NACA 0012 was experimentally produced using smoke wind tunnel at angles of attack(0°, 5°, 10°,14° and 20°) respectively, and repeat the works with circular cylinder at the leading edge of this airfoil at the same angles. The results compared with computational results of other theoretical results researchers, and there is a good approximate between most of results. The angle of separation of the boundary layer of airfoil is 14°, but the angle will be change to 20° when the cylinder be at the leading edge of the airfoil.