The blade pitch angle is a critical geometric parameter that significantly affects the aerodynamic performance of coaxial contra-rotating propellers. In this study, numerical simulations were conducted to systematically investigate the effects of varying the blade pitch angles of the front and rear rotors on the aerodynamic performance of a variable-pitch contra-rotating propeller system. The results demonstrate that as the blade pitch angle increases, both the thrust coefficient and power coefficient of the front and rear rotors exhibit a significant upward trend, while the propulsive efficiency decreases. An increase in the rear rotor’s blade pitch angle slightly reduces the thrust coefficient of the front rotor, whereas an increase in the front rotor’s blade pitch angle significantly enhances the thrust coefficient of the rear rotor. When configuring the blade pitch angles of the front and rear rotors, a larger front blade pitch angle is shown to achieve superior aerodynamic performance.