Identification of Experimental Unsteady Aerodynamic Impulse Responses

The identification of experimental unsteady aerodynamic impulse responses using the Oscillating Turntable (OTT) at NASA Langley's Transonic Dynamics Tunnel is described. Results are presented for two configurations: a rigid semispan model and a rectangular wing with a supercritical airfoil section. Both models were used to acquire unsteady pressure data caused by pitching oscillations on the OTT. A deconvolution scheme involving a step input in pitch and the resultant step response in pressure, for several pressure transducers, is used to identify the pressure impulse responses. The identified impulse responses are then used to predict the pressure response caused by pitching oscillations at several frequencies