Abstract
The use of active flow control to affect the aerodynamic loads on a half model of a generic tailless chined forebody delta wing was examined experimentally on a modular half model equipped with pairs of surface-normal or angled synthetic jets (SJs). Tuft visualizations were performed to qualitatively validate the model. Then, aerodynamic load measurements and time and phase-averaged �������� with and without flow control were performed. When the SJs were pulse-modulated to the main helical mode frequency of the vortical system, Surface-normal SJs increased ���� & ���� while angled SJs decreased ���� & ���� . Additionally, the effect of pitch break was found to be reduced with either jet configuration. �������� results showed this effect on the surface-normal SJs to be from moving the time-averaged position of the forebody vortex closer to the surface. Phase-locked data showed this was caused by the jet blowing between the primary and secondary forebody vortices and temporarily detaching the forebody vortex from the separated shear layer during the on portion of the actuation duty cycle.
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