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Universitas Muhammadiyah Sidoarjo
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Engineering
DOI: 10.21070/acopen.10.2025.10782
Published: 2025-03-25

Simulation Analysis of Airfoil for Solar-Powered UAV Applications


Analisis Simulasi Profil Sayap untuk Aplikasi UAV Bertenaga Surya

Tashkent State Transport University
Uzbekistan

(*) Corresponding Author

Solar-Powered UAV Airfoil Aerodynamic Analysis UAV performance Energy Efficiency Lift to Drag Ratio Reynolds Number Solar Energy Systems

Abstract

General Background: Solar-powered unmanned aerial vehicles (UAVs) are increasingly utilized for long-duration missions due to their ability to harness renewable energy, reducing operational costs and environmental impact. Specific Background: The aerodynamic performance of airfoils is crucial in optimizing flight efficiency and endurance for solar-powered UAVs, as it directly affects lift, drag, and overall energy consumption. Knowledge Gap: Despite the importance of airfoil selection, there is limited research on the aerodynamic characteristics of the NACA 2412 airfoil for solar-powered UAV applications under varying flight conditions. Aims: This study aims to analyze the aerodynamic performance of the NACA 2412 airfoil using XFLR5 software, focusing on the variation of lift, drag, and the coefficient of lift (Cl) across different angles of attack and Reynolds numbers to evaluate its suitability for solar UAVs. Results: The findings reveal that the NACA 2412 airfoil offers a well-balanced aerodynamic performance with favorable lift-to-drag characteristics. It demonstrates efficient lift generation while maintaining low drag at moderate angles of attack, making it a viable candidate for solar UAV applications. Novelty: This study provides a comprehensive simulation-based evaluation of the NACA 2412 airfoil, offering new insights into its performance under specific flight conditions for solar-powered UAVs. Implications: The results contribute to the informed selection of airfoils for solar UAV design, supporting the development of more efficient and enduring solar-powered aerial systems.

Highlights:

  1. Evaluating NACA 2412 airfoil for solar-powered UAV efficiency.
  2. XFLR5 simulation analyzing lift, drag, and aerodynamic performance.
  3. NACA 2412 offers balanced lift-to-drag, supporting solar UAV applications.

Keywords: Solar-Powered UAV, Airfoil, Aerodynamic Analysis, UAV performance, Energy Efficiency, Lift to Drag Ratio, Reynolds Number, Solar Energy Systems.

Introduction

Unmanned aerial vehicles (UAVs) are increasingly used in a variety of applications, ranging from surveillance to environmental monitoring. Solar-powered UAVs, in particular, offer the advantage of extended flight times by utilizing solar energy, thereby reducing dependency on traditional fuel sources [1, 2]. One of the key factors influencing the performance of solar-powered UAVs is the selection of an appropriate airfoil [3, 4, 5]. Airfoil design directly impacts the lift-to-drag ratio, stability, and overall efficiency of the aircraft [6, 7, 8].

In this study, we focus on the aerodynamic analysis of the NACA 2412 airfoil (figure 1), which is widely used in UAV applications due to its balance of stability and efficiency. The objective of this research is to simulate and analyze the aerodynamic performance of the NACA 2412 airfoil using XFLR5 software, a tool widely used for the analysis of airfoils in subsonic flight conditions. By investigating key parameters such as lift, drag, and the coefficient of lift across different angles of attack and Reynolds numbers, this study aims to provide insights into the suitability of the NACA 2412 for solar-powered UAVs.

Figure 1.Airfoil Geometry of the NACA 2412

Methods

The simulation analysis of the NACA 2412 airfoil was conducted using XFLR5 software, which is a widely used tool for analyzing the aerodynamic properties of airfoils and wings at low to moderate Reynolds numbers. XFLR5 is based on the Lifting Line Theory and provides a detailed analysis of aerodynamic parameters such as lift, drag, and the coefficient of lift (Cl) for a given airfoil shape. The following steps outline the methodology [9, 10, 11, 12]:

1.Airfoil Selection: The NACA 2412 airfoil was selected for this study due to its well-established use in UAV applications. Its moderate camber and thickness offer a good balance between lift and drag, making it a promising candidate for solar-powered UAV designs [13, 14, 15].

2. Simulation Setup:

· Angle of Attack. A range of angles of attack from -5° to 15° were simulated to assess the airfoil’s performance at different flight conditions.

· Reynolds Numbers. The simulations were performed at various Reynolds numbers, which reflect the scale and flight conditions typical of small UAVs, ranging from 50,000 to 500,000.

· Flow Conditions. The airfoil was assumed to operate under steady-state, incompressible flow conditions, with a Mach number less than 0.3, appropriate for subsonic flight regimes.

3. Analysis Parameters:

· Lift Coefficient (Cl). The coefficient of lift was evaluated across different angles of attack to determine the airfoil’s lift characteristics.

· Drag Coefficient (Cd). The drag coefficient was calculated to assess the resistance encountered by the airfoil during flight.

· Lift-to-Drag Ratio (L/D). The efficiency of the airfoil was assessed by calculating the lift-to-drag ratio, an essential factor in solar-powered UAV performance.

4. Post-Processing: The results from the simulations were analyzed and compared to identify trends in aerodynamic performance as functions of angle of attack, Reynolds number, and flight conditions.

Result and Discussion

The simulation results reveal key insights into the aerodynamic performance of the NACA 2412 airfoil under different conditions.

1. Lift and Drag Performance

At an angle of attack of 5°, the NACA 2412 airfoil exhibited a coefficient of lift (Cl) of 0.79534 and a coefficient of drag (Cd) of 0.01178. This results in an impressive Lift-to-Drag ratio (L/D) of approximately 67.5, which highlights the airfoil's high aerodynamic efficiency at this angle of attack. The relatively low drag coefficient (Cd) suggests that the airfoil can generate significant lift while minimizing drag, which is essential for the performance of solar-powered UAVs. Figure 2 shows the variation of Cl and Cd with respect to the angle of attack. The graph clearly demonstrates how Cl increases with the angle of attack, peaking at around 5° before plateauing or decreasing due to flow separation. Similarly, Cd increases with the angle of attack but remains relatively low at moderate angles, indicating that the airfoil operates efficiently at these conditions.

Figure 2.Variation of the Coefficient of Lift (Cl) and Coefficient of Drag (Cd) with Angle of Attack for the NACA 2412 Airfoil at 5°

2. Moment Coefficient (Cm) and Aircraft Stability

The Moment Coefficient (Cm) (figure 3 (a)) at an angle of attack of 5° is -0.05210, indicating a small negative pitching moment for the NACA 2412 airfoil. This negative Cm suggests that at this angle, the airfoil generates a nose-down moment, which is typical for an airfoil that provides inherent stability. This negative pitching moment is beneficial for maintaining the stability of the UAV, as it helps counteract excessive pitching and ensures controlled flight.

Figure 3.a) Change in the Moment Coefficient (Cm) with Angle of Attack (α) for the NACA 2412 Airfoil. b) Change in the Coefficient of Lift (Cl) with the Boundary Layer Transition Point (Xtr top) for the NACA 2412 Airfoil

3. Lift Coefficient (Cl) and Boundary Layer Transition (Xtr top)

The graph in Figure 3 (b) shows the variation of the Coefficient of Lift (Cl) with respect to the location of the Xtr top, or the boundary layer transition point on the upper surface of the NACA 2412 airfoil. As the Xtr top moves toward the leading edge, the airfoil experiences more laminar flow, which generally results in lower drag but can reduce the Cl. On the other hand, as the Xtr top moves towards the trailing edge, the flow becomes more turbulent, which can increase the Cl but at the expense of higher drag. Understanding the behavior of Cl relative to the Xtr top location is essential for designing efficient airfoils. The precise control of boundary layer transition can optimize the aerodynamic performance, ensuring high lift while minimizing drag. The graph demonstrates how the Cl is influenced by the position of this transition point, highlighting the relationship between flow characteristics and lift production.

4. Hinge Force (Fy) and Angle of Attack (α)

The graph in Figure 4 shows the variation of the Hinge Force (Fy) with the Angle of Attack (α) for the NACA 2412 airfoil. As the angle of attack increases, the force on the hinge changes, reflecting the impact of aerodynamic forces on control surfaces such as ailerons or elevators. At moderate angles of attack, the Hinge Fy force is relatively small, suggesting that the airfoil is maintaining stable control characteristics. However, as the angle of attack increases, the Hinge Fy force increases, which may indicate increased aerodynamic loading on the control surfaces, potentially affecting the stability and maneuverability of the UAV. This information is crucial for understanding the aerodynamic forces acting on the UAV’s control surfaces, which can influence both stability and control effectiveness, especially at higher angles of attack.

Figure 4.Variation of Hinge Force (Fy) with Angle of Attack (α) for the NACA 2412 Airfoil

Conclusion

The results demonstrate that the NACA 2412 airfoil offers a well-balanced aerodynamic performance, showing favorable lift and drag characteristics across a range of angles of attack and Reynolds numbers. Its moderate lift-to-drag ratio makes it an ideal candidate for solar-powered UAVs, where energy efficiency plays a crucial role in enhancing flight endurance and reducing dependency on energy sources. The study highlights that at moderate angles of attack, the NACA 2412 airfoil exhibits strong lift capabilities while keeping drag relatively low, which is essential for efficient solar-powered flight. Additionally, the airfoil’s performance at various Reynolds numbers suggests its suitability for the specific flight conditions of small UAVs. These findings support the potential of the NACA 2412 for long-duration flights, a critical requirement for solar UAVs.

While the simulation results provide valuable insights, further research is needed to optimize the airfoil design for specific mission profiles and environmental conditions. Experimental validation of the results could also provide additional confidence in the model predictions. Future studies could explore how variations in airfoil shape, material properties, and flight conditions affect the overall performance, further improving solar-powered UAV efficiency.

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