This document summarizes the optimal wing design of a NACA 2412 series wing. A team of 4 students studied the NACA 2412 geometry, designed the wing in SolidWorks using NASA equations, and conducted static, dynamic and flow simulations. Material selection focused on aluminum alloy 7079 for its strength, lightweight properties and cost effectiveness. Static stress simulations showed stress exceeded limits at the tail, but this area is reinforced by the main body. Thermal simulations from 300-500K indicated stress levels below failure thresholds. The design process and simulations met the objectives of optimizing the NACA 2412 wing design.