Morphing aircraft equipped with inflatable wings have demonstrated exceptional reliability and unique capabilities across various applications, primarily due to their lightweight structures and ease of folding. This study aims to evaluate the aerodynamic performance of a bumpy airfoil based on the NACA 4413 airfoil, focusing on low Reynolds numbers from 105 to 2·105. Wind tunnel experiments and numerical simulations were conducted over a broad spectrum of angles of attack from −4° to 28°. The objective was to establish a comprehensive database to inform the design process of aircraft utilizing inflatable wings. The study compares experimental and numerical results by analyzing the pressure distributions along the wing surface. This comparison not only validates the numerical simulations but also offers insights into optimizing installation configurations for future wind tunnel experiments. The findings significantly enhance the design, performance assessment, and testing methodologies for inflatable-wing aircraft, supporting the development of more efficient and versatile aircraft for diverse applications.