| Autor: |
Anuar, Kaspul, Fatra, Warman, Asral, Asral, Nazaruddin, Nazaruddin, Taslim, Muhammad |
| Předmět: |
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| Zdroj: |
AIP Conference Proceedings; 2024, Vol. 2891 Issue 1, p1-11, 11p |
| Abstrakt: |
This study aims to produce a design of tail-sitter UAVs. The research process is begun by determining the design requirement objective and calculating the required wing dimensions. Three candidates of wing airfoil were analyzed for their aerodynamic characteristics using XFLR 5 software. The results were selected using a decision matrix. The three candidates of fuselage design were proposed and also were analyzed for their aerodynamic characteristics using Ansys CFD software. The three fuselage candidates were selected using a decision matrix. The result of the selected wing and fuselage are then assembled and the aerodynamic characteristics are calculated. Based on the calculations, the Clark-Y was selected as the wing airfoil with a lift coefficient and lift-to-drag ratio of 0.83185 and 84.16466, respectively. The second fuselage candidate was chosen as the fuselage design with a drag coefficient value of 0.10077. Finally, at the takeoff phase, the tailsitter UAV design is able to produce lift coefficients and drag coefficients of 0.90017 and 0.11958, respectively. While at the cruise phase, the UAV tail-sitter design is able to produce lift and drag coefficients of 0.99239 and 0.09571, respectively. [ABSTRACT FROM AUTHOR] |
| Databáze: |
Complementary Index |
| Externí odkaz: |
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