Abstract: To address the comprehensive technical requirements of high loading, low weight and low noise for aero-engine fans, and to break through the bottleneck of noise reduction and weight reduction for high-bypass-ratio fans, this paper proposes and develops an integrated design method for low noise and flutter suppression of fans. This method incorporates the two key issues of fan low noise design and flutter suppression, which are usually treated independently, into a unified design process for collaborative optimization. Based on the nonlinear harmonic method (NLH), three-dimensional unsteady flow field numerical simulation of the fan is conducted, and the wave decomposition method is applied to evaluate the tonal noise induced by shock waves. By applying key techniques such as controlling expansion wave systems on the blade surface, end-bending, and swept design to the high-bypass-ratio fan design, the pulsating pressure in the fan inlet duct is significantly reduced, and shock wave noise is effectively suppressed; at the same time, the flutter stability of the blades is significantly improved. The results demonstrate that, compared to the baseline fan blade, the rotor blade optimized with wave system control, end-bending, and swept design achieved a reduction of up to 11.0 dB in sound pressure level at the fan inlet at design speed and 5.8 dB at takeoff speed, indicating notable noise reduction effects. Additionally, blade stress was significantly reduced, stress concentration was effectively mitigated, and aerodynamic damping was substantially enhanced. The design methodology proposed in this study shows clear potential for engineering applications and provides an effective approach for high-performance design of high-bypass-ratio fans.