The paper investigates the Lift-to-drag Coefficient ratio (CL/CD) efficiency of three airfoils, namely E387, RG15, and SD6060. The objective is to optimize the airfoils for maximum CL/CD efficiency and evaluate them using XFOIL software. The study focuses on these airfoils' performance at different Reynolds numbers (Re) from 500,000 to 1,000,000, with varying thickness-to-camber ratio percentages (t/c%). The results indicate that the E387-Opt airfoil improved the maximum CL/CD by 18.92% at Re 500,000, 23.77% at Re 600,000, 27.14% at Re 700,000, 32.44% at Re 800,000, 32.93% at Re 900,000, and 38.46% at Re 1,000,000. The RG15-Opt airfoil also demonstrated impressive performance, with a maximum CL/CD increase of 34.38% at Re 500,000, 36.75% at Re 600,000, 38.54% at Re 700,000, 41.58% at Re 800,000, 45.57% at Re 900,000, and 51.30% at Re 1,000,000. Finally, the SD6060-Opt airfoil showed even better results, with a maximum CL/CD increase of 37.07% at Re 500,000, 38.16% at Re 600,000, 42.44% at Re 700,000, 48.99% at Re 800,000, 53.10% at Re 900,000, and 56.91% at Re 1,000,000.