Analisa Aerodinamika Flap Pada Airfoil NACA 0012 Terhadap Nilai Cl Dan Nilai Cd Dengan Menggunakan Metode CFD

Analysis of the aerodynamic performance of an airfoil is necessary to determine the value of the lift coefficient and drag coefficient value that happens to an airfoil. The design that was used in this study is NACA 0012 series airfoil simulated with CFD method using Ansys Workbench 2021R1 student version software. Flap variation was added to the airfoil so the drag coefficient (Cd) and lift coefficient (Cl) value in airfoil NACA 0012 can be compared between with and without flap. The simulation using Reynold number 6,000,000. Airfoil NACA 0012 model taken from airfoil tools cites then exported to Autodesk Fusion 360 student version software then adding the flap in it. The gap variation is 1% chord, flap 30% chord, and 5°, 10°, 15° flap deflection. Simulation using Ansys Workbench 2021R1 student version with various setting airfoil boundary conditions. The resulting parameters include Cl value, Cd value, as well as pressure and velocity distribution contours. Research from simulations on airfoil variations obtained the results that the highest Cl and Cd values were obtained by airfoils with the largest flap variation of 15° with values of 0.554 for Cl and 0.031 for Cd.