A nonlinear, aeroelaslic analysis of a low-aspect, rectangular wing modeled as a plate of constant thickness demonstrates that limit cycle oscillations of the order of the plate thickness are possible. The structural nonlinearity arises from double bending in both the chordwise and spanwise directions. The present results using a vortex lattice aerodynamic model for low-Mach-number flows complement earlier studies for high supersonic speed that showed similar qualitative results. Also, the theoretical results are consistent with experimental data reported by other investigators for low-aspect-ratio delta wings.