This chapter examines flutter prediction and its mechanism on a finite wing. The approach used considers aeroelastic analysis in the time domain. The dynamic-structural and aerodynamic models are coupled for simultaneous solutions of the aeroelastic equations of motion represented by structural modal coordinates. By inspecting the modal responses in time, together with their power spectra, it is possible to observe the physical mechanism that develops with airspeed until instability. The Least-Squares Complex Frequency (LSCF) method is also presented to obtain V-g–f plots through system identification. Finally, a numerical example based on the results of the literature is provided.