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INITIALLY symmetric separation vortices over slender wings and bodies become asymmetric as the angle of attack is increased beyond a certain value, causing large lateral aerodynamic loads. In addition, conventional aerodynamic control surfaces become ineffective in such situations because of vortex wakes generated by the forebody. Much theoretical, computational, and experimental work has been spent on the understanding, prediction, and control of the onset of vortex asymmetry [1–9]. It has been found both computationally and experimentally that the vortices are very sensitive to small perturbations near the apex of a forebody [3, 5, 9]. Although methods have been developed to delay the onset of asymmetric vortex shedding, the fact that the separation vortices generate large airloads and are very sensitive to small perturbations offers an exceptional opportunity for manipulating them with little energy input …