The propeller requires precise design tailored to various flight conditions. In this study, the aerodynamic relations governing propeller performance were examined, focusing on the analysis of lift and drag forces acting on the blades. To achieve an optimized design, several propeller configurations were investigated, and the effects of parameters such as angle of attack, thrust distribution, and velocity profiles on propeller efficiency were analyzed. Subsequently, based on the Blade Element Momentum Theory (BEMT), a propeller suitable for an electrically powered aircraft capable of operating at speeds above 60 m/s was designed. The initial design and simulation were performed using JavaProp software, and the obtained results were validated through comparison with reference data. The results demonstrated that the presented design enhances aerodynamic behavior at high speeds and can serve as an efficient option for electric propulsion systems. For the flow analysis around the propeller, a CFD approach based on the Reynolds‑Averaged Navier–Stokes (RANS) equations and the k–ω turbulence model was utilized. As the engine rotational speed increased from 2500 to 5000 rpm, the thrust rose from approximately 4,500 N to 12,500 N, and the uniform velocity field indicated stable and coherent flow structures around the blades. Furthermore, the gradual increase in thrust with rotational speed confirms the proper adaptation of attack angles and geometric twist to real‑flow conditions. Overall, the designed propeller demonstrated a 35 % increase in efficiency making it a reliable and effective choice for electric propulsion systems in light and aerobatic aircraft applications.