STUDI KOMPARASI PERFORMA AERODINAMIKA
TERHADAP PENAMBAHAN STRUKTUR WINGLET
PADA SAYAP PUNA KARGO
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
BACHTIAR, OSCAR
Subject
T Technology (General)
Datestamp
2024-04-05 03:27:02
Abstract :
The initial design of the UAV cargo wing was made without being equipped with a winglet structure. The specifications and flight capabilities of UAV cargo allow for induced drag generated by the vortex on the wing during operation. One of the efforts to overcome this vortex is to add winglet structures. In the first development of the UAV cargo wing, the addition of a whit comb winglet structure was carried out which generated in less optimal results. In the second development, this research was carried out by comparing aerodynamic performance on variations of the UAV cargo wing model without winglets, with the addition of whit comb winglets and blended winglets. This research was conducted using the Computational Fluid Dynamic 3D simulation method through the fluent Ansys software and also supported by Solidworks 2018. The simulation was carried out on the UAV cargo wing which has the basic shape of the NACA 23018 airfoil. The simulation parameter settings were carried out close to the original conditions at an altitude of 20,000 feet. The output of this simulation was the value of the lift coefficient, drag coefficient, streamlined contour and vortex region. The results of the UAV cargo wing research showed that the addition of the blended winglet increased the wing's aerodynamic performance by 7.40%, while the addition of the whit comb winglet decreased the wing's performance by -18.18%.
The initial design of the UAV cargo wing was made without being equipped with a winglet structure. The specifications and flight capabilities of UAV cargo allow for induced drag generated by the vortex on the wing during operation. One of the efforts to overcome this vortex is to add winglet structures. In the first development of the UAV cargo wing, the addition of a whit comb winglet structure was carried out which generated in less optimal results. In the second development, this research was carried out by comparing aerodynamic performance on variations of the UAV cargo wing model without winglets, with the addition of whit comb winglets and blended winglets. This research was conducted using the Computational Fluid Dynamic 3D simulation method through the fluent Ansys software and also supported by Solidworks 2018. The simulation was carried out on the UAV cargo wing which has the basic shape of the NACA 23018 airfoil. The simulation parameter settings were carried out close to the original conditions at an altitude of 20,000 feet. The output of this simulation was the value of the lift coefficient, drag coefficient, streamlined contour and vortex region. The results of the UAV cargo wing research showed that the addition of the blended winglet increased the wing's aerodynamic performance by 7.40%, while the addition of the whit comb winglet decreased the wing's performance by -18.18%.
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