Using the simple typical section model for aeroelastic analysis, we examine the vibration properties of a two-dimensional wing model for various morphing shapes. The morphing condition discussed is wing sweep for small uninhabited air vehicles (UAVs). Asymmetric wing sweep can be used to effect advantageous roll maneuvers for highly agile flight. Essentially, with one wing swept, the mass moment of inertia decreases, causing a large roll velocity, which is desirable to initiate a fast turn. The issue addressed here is how does such a drastic change affect wing vibration, and does it cause flutter or divergent instability? Using the typical section model and expanding it slightly by modeling the torsional spring effect as that due to a beam model of the wing in torsion, the characteristic equation describing the wing vibration is studied. The model then allows the eigenvalue solution corresponding to the first modes of vibration to be computed. This is done for each wing shape in order to determine and characterize the effect of wing morphing on the wing’s vibration. In particular, the shapes at which the wing will experience instability due to flutter or divergence are examined.