STUDI NUMERIK PENGARUH GROUND EFFECT TERHADAP KARAKTERISTIK AERODINAMIKA WING NACA 6412
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Nopri, Sabaril
Subject
T Technology (General)
Datestamp
2024-02-15 08:21:54
Abstract :
Wing in ground effect is a type of winged ship in which the wings are given to the right and left side of the hull to be able to move away from the surface of the water then fly and land properly again in the water. The wing structure experiences loading, either the dynamic loads or the static loads. This study designed and simulated the NACA 6412 airfoil wing which was affected by the height and angle of attack using ANSYS 16.5 software to identify the values of the force and drag coefficients and supported by Solidwork 2018 software. The simulation process was carried out with variations in height and variations in angles of attack. Modeling was carried out in Solidwork 2018 software then the design was simulated in ANSYS software with predetermined settings and parameters. The results showed that the NACA 6412 wing airfoil with a height of 0.1c at an angle of attack of 12° had the highest lift coefficient and a height of 1c at an angle of attack of 12° had the highest drag coefficient. The highest lift/drag coefficient value occurred at a height of 0.1c at an angle of attack of 4°.
Wing in ground effect is a type of winged ship in which the wings are given to the right and left side of the hull to be able to move away from the surface of the water then fly and land properly again in the water. The wing structure experiences loading, either the dynamic loads or the static loads. This study designed and simulated the NACA 6412 airfoil wing which was affected by the height and angle of attack using ANSYS 16.5 software to identify the values of the force and drag coefficients and supported by Solidwork 2018 software. The simulation process was carried out with variations in height and variations in angles of attack. Modeling was carried out in Solidwork 2018 software then the design was simulated in ANSYS software with predetermined settings and parameters. The results showed that the NACA 6412 wing airfoil with a height of 0.1c at an angle of attack of 12° had the highest lift coefficient and a height of 1c at an angle of attack of 12° had the highest drag coefficient. The highest lift/drag coefficient value occurred at a height of 0.1c at an angle of attack of 4°.
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