This study presents an application of a three-dimensional approach for detailed analysis of an articulated rotor blade undergoing large displacement and elastic deformations. The articulated blade has the geometry, structural and mass properties similar to the UH60 blade. In analyzing an articulated blade, each member of the cross-section is modeled individually. The titanium box-beam and the Graphite-Epoxy skin are modeled using plate elements, the homogeneous core is modeled using solid elements. Lumped mass is used to represent the balance weight. One dimensional spring and damper are also utilized to model the pitch link and the lead-lag damper. A quasi-steady aerodynamic model based on the lifting line theory has been utilized to compute the aerodynamic load. A wind tunnel trim analysis has been utilized to compute the control setting that are required to produce a specific thrust and eliminate the 1/rev flapping motion.