Dynamic wind tunnel testing of a flexible wing model 13; 13;

The current state-of-art in the design of modern combat aircraft is to use CCV concepts to obtain high performance at lower weight. This demands an unstable aerodynamic configuration with the stability provided artificially by the control system. This needs longitudinal servo-actuators of high bandwidth. With lower structural frequencies there is scope for interaction and aeroservoelastic problems could occur. This document details a simple experimental study13; of servoelastically exciting a wing to yield transfer function data. The aim of these experiments is to provide a vehicle for generating experimental data for validating aeroservoelastic codes and to obtain insight of flutter I aeroservoelastic phenomena through scaled models.13