Aerodynamic And Aeroacoustic Study Of Using Multiple-Element-Wing Leading-Edge Slat On Plain And Slotted Flap Wing Airfoil NACA 43018

Aerodynamic performance and noise are important things to consider when using highlift devices on aircraft wings. The use of high-lift devices that aim to improve aerodynamics has the side effect of noise in its use. Aerodynamic performance and noise can be estimated by numerical simulation which in this study uses NACA 43018. The numerical simulation in this study uses Ansys 19.1 with the k − ε Realizable turbulent model. The research model uses several angles of attack α including 0^◦, 2^◦, 4^◦, 6^◦, 8^◦, 10^◦, 12^◦, 15^◦, 16^◦, 17^◦, 19^◦, and 20^◦. The models are plain wing, leading edge-slat combined with plain flap, and leading edge-slat with slotted flap. The use of leading-edge slats and flaps improved the aerodynamic performance at all observed angles of attack for both plain flaps and slotted flaps. The use of a leading-edge slat enhances the flow transition process from laminar to turbulent in addition to increasing the flow momentum so that the separation point is pushed towards the trailing edge. Velocity fluctuations show an increase in noise value in the use of leading-edge slats and flaps with a significant value, especially in the wingtip area. The velocity fluctuations also show the potential for vorticity, especially at high-velocity fluctuations. In addition, an increase in wake topology in the area behind the trailing edge.