This paper details the identification of the dynamics of a flexible delta wing model. The wing model was tested in the low speed dynamic wind tunnel of NAL at three dynamic pressure conditions. The model was aerodynamically excited by driving its trailing edge control surface with sinesweep signals. Time domain time series identification technique was used to identify the flexible wing dynamics from its responses. Lower order models were deduced from the identified higher order models using balanced reduction technique. The identified dynamics showed that the frequency and damping of the dominant mode varied appreciably for the tested dynamic pressure range
