AEROELASTICITY OF AN AIRFOIL TEST RIG

This paper describes an aeroelastic model for an airfoil test rig whic h is based on the mode superposition method for structural systems and linear airfoil theory for describing the unsteady airfoil loading. Th e model is applied to the case of an airfoil undergoing rapid, small a mplitude step-like maneuvers. The motivation for these tests was an in terest in measuring airfoil indicial responses, which are defined as t he loading response to a step input in angle of attack. Due to the rap id starting and stopping of the airfoil rig, the structure may experie nce significant aeroelastic deformations. These may arise from inertia l as well as aerodynamic effects. The present model may be of general interest as a means for quantifying and correcting aeroelastic effects In tow tank and wind tunnel test facilities. (C) 1997 Academic Press Limited.