The aerodynamic design of supercritical wings is one of the core technologies in the design of modern large civil aircraft. The airfoil serves as the foundation for the supercritical wing to achieve favorable aerodynamic characteristics. This paper focuses on the optimization design requirements of airfoils with multiple states, objectives, and constraints. It analyzes the relationship between separation regions and both low-speed stall characteristics as well as transonic buffet characteristics. This analysis significantly reduces the number of computational states required for aerodynamic optimization. Based on the genetic optimization algorithm, an aerodynamic optimization method for supercritical airfoils considering separation constraints is established. Finally, using the RAE2822 airfoil as the baseline, aerodynamic optimization is conducted. The resulting supercritical airfoil design meets engineering constraints such as thickness limitations, low-speed separation characteristics, and drag divergence characteristics, and it demonstrates high engineering application value.