Aeroelastic Model Development for the Integrated Adaptive Wing Technology Maturation Project Wind-Tunnel Test

摘要

In this paper, several aeroelastic models were developed in support of an upcoming wind-tunnel test by coupling a linear structural dynamics model with aerodynamic models of varying fidelities. These aeroelastic models were then used to predict the flutter boundary associated with the wind-tunnel test across several Mach numbers. Additional comparisons were made showing differences in the aeroelastic models at Mach 0.8. While none of the codes were expected to match completely because of fundamental differences in aerodynamic modeling, all gave similar predictions for flutter speed and frequency. The results presented in this paper will be used in support of the upcoming IAWTM (Integrated Adaptive Wing Technology Maturation) wind-tunnel test at the Transonic Dynamics Tunnel at the NASA Langley Research Center.