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Unmanned Aerial Vehicle structural design: Bachelor Thesis

By: Material type: TextTextUB., Nalaikh GMIT 2023Description: 61 pageISBN:
  • 15614548153614
DDC classification:
  • 629.1 E-54
Online resources:
Contents:
This study focuses on the design, analysis, and selection of an airfoil for a heavy-lifting unmanned aerial vehicle (UAV) with the aim of achieving optimal aerodynamic performance. The UAV is intended for civilian and reconnaissance applications and must be capable of carrying a maximum take-off weight of 450 kg while operating at an altitude of 4000 meters. As such, the airfoil design must provide high lift-to-drag ratios and fulfill specific performance criteria to ensure efficient and reliable operation under the designated conditions. Through rigorous computational fluid dynamics (CFD) simulations and a comprehensive assessment of various airfoil candidates, the NACA 634421 airfoil was identified as the most suitable choice for this application. At a 10-degree angle of attack, this airfoil exhibits favorable aerodynamic characteristics, meeting the required lift coefficient and demonstrating a satisfactory lift-to-drag ratio. The study delves into the effects of airfoil geometry, camber, and flow separation on lift generation and drag reduction, emphasizing the critical role of airfoil selection in the overall performance and efficiency of the UAV. Additionally, this research explores the relationship between pressure and velocity contours and their impact on the airfoil's aerodynamic properties. The analysis highlights the importance of understanding flow separation and its consequences on lift and drag, providing valuable insights for future airfoil optimization. The results and recommendations presented in this study offer a solid foundation for the development of heavy-lifting UAVs and contribute to the growing body of knowledge in the field of airfoil design. Furthermore, the study identifies areas for future research, including experimental validation through wind tunnel testing and the use of more sophisticated simulation tools to overcome the limitations of the current computational approach, such as the low y-plus value encountered in the CFD simulations. In conclusion, this research demonstrates the significance of selecting an appropriate airfoil design for heavy-lifting UAVs, contributing to the advancement of UAV technology and its potential applications in civilian and reconnaissance operations

This study focuses on the design, analysis, and selection of an airfoil for a heavy-lifting unmanned aerial vehicle (UAV) with the aim of achieving optimal aerodynamic performance. The UAV is intended for civilian and reconnaissance applications and must be capable of carrying a maximum take-off weight of 450 kg while operating at an altitude of 4000 meters. As such, the airfoil design must provide high lift-to-drag ratios and fulfill specific performance criteria to ensure efficient and reliable operation under the designated conditions.
Through rigorous computational fluid dynamics (CFD) simulations and a comprehensive assessment of various airfoil candidates, the NACA 634421 airfoil was identified as the most suitable choice for this application. At a 10-degree angle of attack, this airfoil exhibits favorable aerodynamic characteristics, meeting the required lift coefficient and demonstrating a satisfactory lift-to-drag ratio. The study delves into the effects of airfoil geometry, camber, and flow separation on lift generation and drag reduction, emphasizing the critical role of airfoil selection in the overall performance and efficiency of the UAV.
Additionally, this research explores the relationship between pressure and velocity contours and their impact on the airfoil's aerodynamic properties. The analysis highlights the importance of understanding flow separation and its consequences on lift and drag, providing valuable insights for future airfoil optimization.
The results and recommendations presented in this study offer a solid foundation for the development of heavy-lifting UAVs and contribute to the growing body of knowledge in the field of airfoil design. Furthermore, the study identifies areas for future research, including experimental validation through wind tunnel testing and the use of more sophisticated simulation tools to overcome the limitations of the current computational approach, such as the low y-plus value encountered in the CFD simulations.
In conclusion, this research demonstrates the significance of selecting an appropriate airfoil design for heavy-lifting UAVs, contributing to the advancement of UAV technology and its potential applications in civilian and reconnaissance operations

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