ANALISIS KARAKTERISTIK AERODINAMIKA PADA AIRFOIL NACA 4415 DENGAN VARIASI SUDUT SERANG
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Sahlan Mataiya, Rahul
Subject
T Technology (General)
Datestamp
2024-02-27 03:12:31
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.
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.
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