Plasma-Based Dynamic Stall Control and Modeling on an Aspect-Ratio-One Wing

Quasi-static and dynamic stall control experiments, using dielectric barrier discharge plasma actuators, were performed on a square-tipped aspect-ratio-one wing, with NACA 0015 profile, under harmonic pitching, at Reynolds number of . Relatively low relatively high pulse-modulated reduced excitation frequencies introduced the leading edge; former produced largest poststall lift improvements, whereas latter highest maximum lift. A frequency, based laminar separation bubble shedding, was enlisted to explain differences between two results. Under conditions evidence vortex absent, due its interaction strong tip vortices, consistent prior experimental numerical investigations. As general rule, performance benefits by quasi-static reproduced pitching. Low-order models, modified version Goman–Khrabrov delta-wing concept, evaluated. Model constants obtained from data sets, single baseline case employed determine time constants. The model excellent results for both controlled cases, which attributed similar mechanisms exhibited delta rectangular low-aspect-ratio planforms.