Abstract
This paper examines the feature of the two-degrees-of-freedom, finite dimensional, nonlinear mathematical model for the transonic flutter of a high aspect ratio wing. The model has been developed by the authors and can explain qualitatively every feature of the wind tunnel test data accumulated at National Aerospace Laboratory in Japan such as the subcritical Hopf bifurcation, saddle node bifurcation, and an unstable limit cycle. By making use of the continuation method for analyzing the bifurcation nature of the model, quantitative matching is expected for the LCO amplitude between the math model and the test results
