Studying of flaps and slats effects on improving the aerodynamic forces of the wings

Abstract EN

A numerical method was used for calculation the pressure distribution and then finding aerodynamic forces to give an estimation for the high- lift systems effect on two-dimensional airfoil for an inviscid incompressible flow (panel method), the computational method investigated experimentally.

The study focused on flap and slat effects on the aerodynamic forces at the wings as two of the important items of the high lift systems. Experimental study was made with suction type low-speed wind tunnel for an airfoil of (NACA 0015) supported with leading edge slat and trailing edge flap.

The effective forces of lift and drag were measured by two components balance.

Different angles of attack (-4, 0, 4, 8 and 12)o and different flap angles (0, 10, 20 and 30)o were chosen with and without slat, variable air velocities (8, 12, 16 and 20) m / s were applied.

The computational results compared with experimentally measured data.