ANALISA AERODINAMIKA AIRFOIL NACA 0012 DENGAN ANSYS FLUENT

Abstract

Performance analysis in airfoil is very important to get maximum lift. In this riset an airfoil design NACA 0012 a simetric airfoil test with ANSYS Fluent software with input velocity, viscositas and densitas of fluids so we can get velocity distribution and pressure distribution in span of airfoil. To get the maximum airfoil lift, gift angle of attack variation so can get maximum angle of attack to get maximum of lift. From velocity contour and pressure contour in ANSYS Fluent in Bottom and Up of airfoil span can get mean of velocity and pressure so can get lift coefficient and drag coefficient. This riset can get advantage in aerodynamics modelling in wing section and can get maximum performance in lift of plane and can develop creativity design of airfoil in NACA Standard.