Modern helicopters employ swept, dihedral blade-tip and nonlinear twist to enhance its aerodynamic performance, which also increase manufacturing complexity and induce significant vibratory loads, and thus vibration reduction of NTBT (New Type Blade-Tip) rotors has become a key research focus. Due to the excellent compatibility and quick response, the TEF (Trailing Edge Flap) technology is promising for rotor vibration reduction. Nevertheless, most aeroelastic researches have been focused on TEF technology or NTBT rotor, respectively, the combinations of TEF/NTBT rotor system remain hardly explored. The CFD/CSD (Computational Fluid Dynamics/Computational Structural Dynamics) method is competent to meet this challenge, which can effectively consider the unconventional blade platforms, unsteady flowfields, and structural dynamics. Therefore, the present aeroelastic study on TEF/NTBT rotor based on CFD/CSD method holds significant theoretical value and engineering importance.