ANALISA KARAKTERISTIK AIRFOIL NACA 4412 DENGAN METODE WIND TUNNEL

The aerodynamics characteristics of a body are the most important in the subject of aerodynamics application in which is intended to get the aerodynamically body profile. This research was performed on both a symmetrical model of NACA Airfoil and Joukowski Airfoil. In this research, the analysis of aerodynamics characteristics had been performed by using Smith-Hess’ panel method that distributes both the source flow and the vortex flow along the surface of airfoil to get the velocity distribution, in which is used to get the pressure distribution on the surface of airfoil. The parameters used as the aerodynamics characteristics are the coefficient of pressure distribution (Cp) and the coefficient of lift (Cl). The research results show that the accuracy level of panel method in analyzing the aerodynamics characteristics is high quite. It could be proved by the graphical visualization of software simulation. This visualization met the trend line of the available charts, hence, the greater of pressure difference between upper and lower surface of airfoil, the bigger of lift. Furthermore, the chart of lift coefficient (Cl) to the angle of attack is linear. The pressure difference was trigged by some factors including the variance of attack angle and the maximum thickness of airfoil. Furthermore, in the geometric of airfoil profile, the difference between the NACA Airfoil and the Joukowski Airfoil is on their sharper trailing edge. Keywords: aerodynamics characteristics, NACA Airfoil. coefficient of lift`