This paper is a continuation of the previous study [1] and focuses on the de¬sign optimization of the low Reynolds number airfoils for the Unmanned Aerial Vehicle (UAV) applications. The study uses the two-software integra¬tion methodology proposed in [1] i.e. XFOIL and modeFRONTIER. To further verify this approach, a different airfoil S1223 is used for design optimization. The proposed method showed high efficiency and up to a 10% improvement in the optimization parameter. In addition, the optimization time and steps were also reduced without conventional user intervention. The optimiza¬tion and CFD analysis demonstrated improved aerodynamic characteristics compared to the original airfoil. The optimized airfoil is especially useful in the UAV applications, which require long-endurance, high lift, and preferably lower weights. Wind tunnel testing of the design is planned in the future.