Abstract: To precisely quantify the aeroelastic coupling effects in transonic blades and reveal their flow mechanisms, this study employs the self-developed fluid-structure interaction (FSI) simulation software AENS to analyze the FSI characteristics of the NASA Rotor 67 transonic fan blade. By analyzing the static aerodynamic elastic deformation of transonic rotor blades, key deformation parameters of the blades were resolved to further investigate the influence of blade deformation on static aerodynamic performance. Results indicate that blade deformation under combined centrifugal and aerodynamic loads manifests primarily as ‌bending-sweep deformation‌, ‌accompanied by changes in the installation angle and radial deformation‌. The bending-sweep deformation ‌increases‌ the radial component of the aerodynamic load, ‌causing‌ the separation zone to ‌expand from the leading edge to the trailing edge near the blade tip‌. ‌The change in incidence angle‌ shifts the channel shock upstream at high spanwise locations. ‌Radial deformation alters the tip clearance, increasing the tip leakage vortex angle and exacerbating losses induced by primary and secondary leakage flows.‌ Collectively, these effects reduce the total pressure ratio and adiabatic efficiency by 1.18% and 1.78% respectively at near-stall conditions compared to the rigid blade. Validation confirms that AENS demonstrates ‌good predictive capability in compressor FSI analyses, ‌highlighting its significant engineering value‌.