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Continuous trailing-edge flap has many advantages over conventional discrete flap in helicopter rotor vibration reduction applications, such as light weight, compact structure and stable airflow. Macro fiber composite is chosen as the actuating material. A blade section with a continuous trailing-edge flap is designed based on NACA23012 airfoil, and its materials are selected and analyzed. The influence of continuous trailing-edge flap on airfoil aerodynamic characteristics is analyzed by fluid-solid coupling method. Results show that continuous trailing-edge flap can output sufficient deflection under the working conditions of helicopter blade, including angle of attack as well as Mach number, and improve aerodynamic lift and moment of the blade profile significantly, which demonstrates the potential value of continuous trailing-edge flap in rotor vibration reduction applications.