@thesis{thesis,
		author={Sahlan Mataiya  Rahul},
		title ={ANALISIS KARAKTERISTIK AERODINAMIKA PADA AIRFOIL NACA 4415 DENGAN VARIASI SUDUT SERANG},
		year={2023},
		url={http://eprints.stta.ac.id/1240/},
		abstract={Air transportation is now experiencing rapid development. This can be seen 
from the number of airlines that serve flight services to various routes both domestic 
and international. An airfoil is a geometric shape that when placed in a fluid flow 
will produce a lift force (lift) greater than the drag force (drag). The testing in this 
study was carried out computationally based on Computational Fluid Dynamics 
using ANSYS fluent software.
The simulation results were carried out on NACA 4415 airfoils with the 
attack angle parameters of 0°, 2°, 4°, 6°, 8°, 10°, 12°, 14°, 16°, and 18° with an 
unbound height. In this study, the highest lift coefficient value was generated by the 
14° angle of attack with a CL value of 1,7404 at the angle of attack which depicted 
the maximum angle of attack for the airfoil. So, at the angle of attack of 18 ° with a 
CD value of 0,22508 generated the highest drag coefficient (CD) value. The 
maximum CL/CD value on NACA 4415 was found at the angle of attack (AoA) of 6
° at the unbound height with a CL/CD value of 64.56114122. In conclusion, the 
greater the distance between the airfoil and the ground, the smaller the CL/CD 
value generated.}
		}