AERODYNAMIC CHARACTERISTICS OF FLUID FLOW ON MULTIPLE-ELEMENT WING AIRFOIL NACA 43018 WITH LEADING-EDGE SLAT AND PLAIN FLAP

At this time, commercial aircraft always use high lift devices. The equipment can be in the form of flaps, leading-edge slats (slat slots), vortex generators, fences, and others. One type of aircraft can use one or more of this equipment so that the resulting lift coefficient can be optimal. The variation of the flap and leading-edge slat is one of the interesting things to observe in terms of phenomena around the wing and the area behind the trailing edge. The addition of flaps and leading-edge slats will certainly change the aerodynamic performance of the wings compared to plain wings so that the most optimum variation can be determined. Numerical simulation of the wing with the NACA 43018 airfoil in this research using Ansys 19.1. with the turbulent model k-epsilon Realizable. The free stream flow rate used is 120 m/s with over a wide range of angles of attack. The variations used are plain wing, flap deflection 0 degrees, 15 degrees, and 30 degrees with a leading-edge slats gap size of 5% to the chord line. Lift coefficient, drag coefficient, and lift-to-drag ratio produced with the addition of flaps and leading-edge slats showed significant differences compared to the plain wing. These variations can be used for certain conditions such as take-off, cruising, and landing. The vorticity magnitude and vortex produced by the addition of flaps and leading-edge slats showed a significant increase compared to plain wings. This shows that the drag and induced drag resulting from the addition of flaps and leading-edge slats also increase.