A computational work to determine the post-critical flutter behavior of orthotropic
and isotropic panels, according to the Von Karman’s large deflection plate theory and
quasisteady linearized aerodynamic theory, has been performed. Three different
numerical schemes, based on Galerkin, Ritz and finite element method, have been
employed for the integration over the panel surface, to reduce the mathematical
problem to a system of differential equations in time. These can be integrated by
appropriate algorithms to derive the vibrating plate behavior over time.
Thus, it has been possible to determine a permanent solution in post-critical
conditions. The paper focuses on the influence of the elastic parameters
on the limit cycle solution of the vibrating plate under a high supersonic
flow. Comparisons between the results obtained by panels with different
elastic properties have been mandatory to characterize their effects on the
post-critical flutter stationary solution. Particular attention has been given to the
limit cycle amplitude, which is a fundamental parameter indicative of the
fluttering panel resistance to a high supersonic airflow. Thus it has been
possible to state an evaluation criterion of the hierarchic importance of the
plate elastic parameters, based on their influence on the panel resistance to
the post-critical flutter phenomenon. The reliability of our analysis can be
guaranteed through the good agreement between the results of the three
methods.
