A computational investigation of limit cycle oscillation behavior of the F-16 fighter configuration using a nonlinear frequency-domain harmonic-balance approach is presented. The research discussed in this latest paper is a follow-on to our work presented at the 2004 SDM conference. Our latest efforts have been directed toward assessing the effects of mean angle-of-attack, wingtip geometry, wing twist, and static aeroelastic deformation on flutter onset and LCO response.