Presented are flutter-onset trends of the F-16 fighter computed using a harmonic balance version of the NASA OVERFLOW 2 flow solver code. The harmonic technique enables one to model unsteady aerodynamics and aeroelastic response in the frequency domain with reduced computational cost compared to time marching solutions. Computed results compare well to flutter results computed using a separate harmonic balance computational flow solver code developed at Duke University. Select aeroelastic limit cycle oscillation results are also presented. © 2010 by Jeffrey P. Thomas, Chad H. Custer, Earl H. Dowell, and Kenneth C. Hall.