To investigate the aerodynamic characteristics and optimization design of variable camber supercritical airfoils, numerical simulation methods were employed to analyze the effects of leading and trailing edge deflection angles on aerodynamic performance under different angles of attack and Mach numbers. By comparing the Isight traditional single objective optimization process with the Kriging surrogate model-based single objective optimization process, the advantages of the surrogate model-based method were verified. A multi-objective optimization approach for variable camber airfoil based on Kriging surrogate model and NSGA-II (non-dominated sorting genetic algorithm II) was proposed. The deflection angles of the leading and trailing edges were taken as input variables, while the maximum lift coefficient and maximum lift-to-drag ratio were set as optimization objectives. Optimal airfoil design parameters were obtained at Mach numbers 0.74 and 0.75. The results indicate that upward deflection of the leading edge can enhance the lift coefficient to some extent, while downward deflection increases the critical angle of attack. The trailing edge deflection has a limited effect on the critical angle of attack, but downward deflection improves the lift coefficient. Moderate upward deflections of both the leading edge and trailing edge delay the critical Mach number, whereas downward deflections advance it. Traditional optimization methods are sensitive to the settings of algorithm parameters, whereas the Kriging-based method can quickly trace the optimal solution, with all predicted errors of the Kriging model being less than 2%. Compared with the baseline airfoil, the optimized airfoils exhibited increases in lift coefficient by 7.55% and 6.79%, and improvements in lift-to-drag ratio by 6.97% and 9.81%, respectively, significantly enhancing the aerodynamic performance.