This paper utilizes an advanced aeroelastic CFD code to analyze the aerodynamic forcing functions and resulting vibrational response of the embedded rotor in a 3-stage axial compressor operating at the 1 torsion mode crossing. A forced response analysis of a fullannulus computational model was performed to compute the vibrational response of the rotor as well as the steady and unsteady aerodynamics of the upstream and downstream vanerows. Detailed analyses investigate the computationally predicted wake shapes and subsequent frequency spectra of the propagating disturbances. Potential disturbances from the downstream stator are also characterized as a means of quantifying the strength of the aerodynamic forcing. The structure and strength of the vortical and potential disturbances dictate the modal force amplitude and resulting blade displacements of the embedded rotor blades vibrating at the 1 torsion mode. Comparisons are made to an extensive experimental dataset previously acquired on the compressor, which characterized the same forced response condition.