ANALISIS PENGARUH GROUND EFFECT
TERHADAP KARAKTERISTIK AERODINAMIKA
PADA AIRFOIL NACA 4415
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Saskia Rianasari Hayuningtyas, RR
Subject
T Technology (General)
Datestamp
2024-04-05 03:27:43
Abstract :
The ground effect is a phenomenon in which a lift-producing device, such as a wing, moves very close to the ground. The closer to the ground, the more wingtip vortices formed, but the magnitude of the induced drag will decrease. In this study, a simulation was conducted to determine the effect of the ground effect on the NACA 4415 airfoil by varying the angle of attack (AoA) and height to the ground. This research uses a simulation method based on Computational Fluid Dynamic 2D using Ansys Fluent software and is also supported by AutoCAD 2016 software. The results obtained from this simulation are lift coefficient (CL), drag coefficient (CD), pressure contour, velocity contour, and streamline. Based on the results of the study, it shows that the NACA 4415 airfoil has a maximum angle of attack of 15o at a height of 0.05c where the angle of attack has the highest lift coefficient (CL) value. While the value of the highest drag coefficient (CD) is generated by an angle of attack of 18o at a height of 0.8c, which is at this angle of attack the stall phenomenon occurs, so the closer the airfoil to the ground, the higher the lift coefficient value (CL) and the lower the drag coefficient value (CD), and vice versa. This research is expected to be useful for consideration in the design of Wing In Ground Effect (WIG) aircraft, so that the flying performance of an aircraft can be maximized.
The ground effect is a phenomenon in which a lift-producing device, such as a wing, moves very close to the ground. The closer to the ground, the more wingtip vortices formed, but the magnitude of the induced drag will decrease. In this study, a simulation was conducted to determine the effect of the ground effect on the NACA 4415 airfoil by varying the angle of attack (AoA) and height to the ground. This research uses a simulation method based on Computational Fluid Dynamic 2D using Ansys Fluent software and is also supported by AutoCAD 2016 software. The results obtained from this simulation are lift coefficient (CL), drag coefficient (CD), pressure contour, velocity contour, and streamline. Based on the results of the study, it shows that the NACA 4415 airfoil has a maximum angle of attack of 15o at a height of 0.05c where the angle of attack has the highest lift coefficient (CL) value. While the value of the highest drag coefficient (CD) is generated by an angle of attack of 18o at a height of 0.8c, which is at this angle of attack the stall phenomenon occurs, so the closer the airfoil to the ground, the higher the lift coefficient value (CL) and the lower the drag coefficient value (CD), and vice versa. This research is expected to be useful for consideration in the design of Wing In Ground Effect (WIG) aircraft, so that the flying performance of an aircraft can be maximized.
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