| dc.description.abstract | In the past, for making and investigating performance of airfoil should be conducted by
trial and error, and often many materials castaway. Since every time, if we would like to change
of the model, we should produce first for doing next investigation. Beside that, for testing the
airfoil should be done in the wind tunnel, it is difficult to get information of pressure and velocity
distribution accurately. Now adays, it can be done computationally, faster and cheaper by using
softwares.
The aim of this research are to investigate the characteristics of airfoil performance. It
cover the pressure distribution, velocity around the airfoil, and visualization of trajectories.
Specifically, it will compare performance of symetric airfoil NACA-0012 and asymmetric airfoil
NACA-2410, especially relationship between Cl, Cd versus ά computationally. Method of
research is proceded by making of symatric airfoil meodil as well as asymmetric airfoil medel by
using design foil software, and then for adjusting angle of attach be assisted by the AutoCad
software, and solving process to be done by the SolidWork CosmosFlow software 2007,
Analisys covers distribution of pressure, velocity and trajectories simulation.
The result of the research shows, that increasing angle of attach will be followed by
increasing of lift coefficient polynomially, it also the drug coefficient has exponentionally
relationship with angle of attach. However, it can be seen that NACA-0012 has the higher
coefficient of lift and coefficient of drug than NACA-2410. This patterns then be compared to
Trend of US Departement of Transportation Federal Aviation document, Apparently there has
similar trend each other. | en_US |
