The low-speed aerodynamic characteristics of a flat-plate delta wing with deflected wing tips rotated about the chord line are the focus of this study. The flat-plate delta wing used in this study has a leading-edge sweep of 60 deg, a rounded leading edge, and interchangeable wing-tip inserts mounted at two-thirds half-span that vary in deflection angles from Formula: see text. Wind-tunnel tests of the model were performed in the Eiffel-type subsonic wind tunnel at The Ohio State University’s Aerospace Research Center. The tests included measurements of aerodynamic forces and wing surface pressure, oil flow visualization, and global velocity measurement with particle image velocimetry. All tests were carried out at a Reynolds number of Formula: see text with respect to the mean aerodynamic chord. The results have shown that the deflected wing tips change the static longitudinal stability characteristics of the model from statically stable to statically unstable. The deflected wing tips were determined to be an effective way to change the longitudinal stability characteristics of the aircraft and increase its potential maneuverability, without negatively impacting the aircraft’s coefficient of lift and drag characteristics.
Trussa et al. (Sun,) studied this question.