ANALISIS AERODINAMIKA PENGGUNAAN PLAIN FLAP PADA AIRFOIL NACA 2412

Abstract

Research on airfoils is a technological improvement in the field of aerodynamics. The results of many tests have been widely applied to design airfoils with various wing shapes according to their function. In the past, working and analysing the capacity of an airfoil required a wind tunnel and took a lot of time and money for the experimental process. The experimental method used is a simulation analysis procedure on NACA 2412 airfoil test specimens that are given additional plain flaps with variations at various angles of attack. The variations used are angle of attack 0^o, 2^o, 4^o, 6^o, 8^o, 10^o, 12^o, 15^o, 16^o, 17^o, 19^o,  and 20^o with wind speed of 20 m/s. To create airfoils, meshing, and calculation processes are carried out using software. From the simulation results on the NACA 2412 airfoil without plain flaps and those that have been added plain flaps, it shows that the airfoil that has been added plain flaps at an angle of attack of 6o can increase the value of the lift force by 1.543038 and has a drag force value of 0.076344, compared to the airfoil without plain flaps with an angle of attack of 12o which has a lift force value of 1.175629 and a drag force value of 0.077251.