This study presents a comprehensive modal analysis of NACA 4412 airfoil-based air-wings constructed from various composite materials, aiming to evaluate their dynamic performance characteristics. The NACA 4412 airfoil is widely recognized for its aerodynamic efficiency, making it a popular choice in aerospace applications. The modal analysis focuses on identifying natural frequencies, mode shapes, and damping ratios of the air-wings, which are critical parameters for assessing structural integrity and performance during flight operations. Different composite materials, including carbon fiber, glass fiber, and aramid fiber, are employed to investigate their effects on the vibrational behavior of the air-wings. Utilizing advanced finite element analysis (FEA) techniques, this research reveals significant variations in modal properties based on material selection, highlighting the influence of stiffness, mass distribution, and damping characteristics on the overall dynamic response. The findings underscore the importance of optimizing material choices to enhance the performance and reliability of air-wing designs in aerospace engineering. Furthermore, the insights gained from this study can inform future developments in lightweight and high-performance airfoil structures, contributing to advancements in aircraft efficiency and safety.