This paper describes stereo photogrammetry measurements of the deformation of simple, flat-plate, clipped delta-wings that were undergoing aeroelastic oscillations in transonic flow. The measurements were made in High Reynolds Number Channel 2 (HRC-2) at Ames Research Center. Two types of aeroelastic responses were measured: (1) highly damped responses where the tip of the model was deflected and then released at subcritical dynamic pressures; and (2) responses excited by perturbations in the flow as the dynamic pressure was slowly increased until the model became unstable. The model was imaged by three synchronized black and white video cameras, and the data was recorded on videotape. Correlated images from two of these cameras were used to estimate the space coordinates of reference marks on the model at each instant, and the motion of each mark was estimated by fitting the deflection data with a damped sinusoid. The resulting estimates of the frequency and damping of the first bending mode oscillations compared favorably with strain-gauge measurements. A large increase in the phase difference between motions of the leading and trailing edges was observed just before the models became unstable.