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. MFC is used as the driving material, the blade section with continuous deformation trailing edge flap is designed based on the NACA23012 airfoil, and the material selection design of the profile structure is analyzed. The aerodynamic characteristics of the Continuous Trailing-Edge Flap is analyzed by Fluid-Structure Interaction method. The results show that the Continuous Trailing-Edge Flap can realize effective deflection in range of the helicopter blade working angle of attack, Mach number, and generate significant additional lift and torque increment. That demonstrates the potential value of Continuous Trailing-Edge Flap in rotor vibration damping application.