Computational study for the design of a hypersonic panel flutter experiment
This work describes the use of a nonlinear computational structural model coupled with Piston Theory aerodynamics for the design of a panel flutter experiment in hypersonic flow. The goal of the experiment is to reach flutter onset within the available flow conditions of the hypersonic wind tunnel at the University of Southern Queensland. Several physical parameters that are present in the experimental configuration have a strong effect on flutter onset conditions, making flutter more or less likely. The nonlinear computational structural model includes the effects of non-ideally clamped boundary stiffness, distributed static pressure differential across the panel, and a temperature differential between the panel and its support. Comparison between solutions obtained by a linear eigenvalue method and direct time-marching solution in modal coordinates show good agreement for flutter and the onset of limit cycle oscillations (LCO), as expected. Time simulations of the nonlinear model are used to predict the root-mean-square of panel’s response after the onset of flutter. Given plate length and width that can fit within the wind tunnel’s dimensions, the panel thickness needed to produce flutter and LCO is determined. Several thicknesses are suggested for the experiment with varying likelihood for flutter and LCO. Transient simulations show that the chosen configurations reach a limit cycle within the 200ms of test duration.
