Application of aerodynamic flow control to the vertical tail of an aircraft could enable significant decrease in its size, with corresponding reductions in drag, weight, and fuel costs. Wind-tunnel experiments at a Reynolds number of 350,000 were conducted on a sweptback tapered vertical tail capable of sideslip rotation. The model used in the present work was approximately th scale with a NACA 0012 airfoil section. It was instrumented with an array of finite-span synthetic jet actuators distributed along the span, just upstream of the rudder hingeline. When the synthetic jets were activated, the side force coefficient was increased by a maximum of 0.17 (34%) over the baseline vertical tail. A primary objective of this work was to explore the effect of the orientation, location, and geometry of the synthetic jet orifices on control effectiveness. The parameters under investigation were orifice aspect ratio, spacing between adjacent orifice edges, the chordwise jet location, spanwise location, skew angle, and spanwise actuator density. This set of experiments suggested that the actuators’ spanwise spacing can be too dense (that is, maintaining constant individual jet strength and reducing the spanwise density of active actuators such that the total area-based momentum decreased, did not have a detrimental effect on side force enhancement for some conditions). The relative importance of other parameters that are typically used to quantify synthetic jet strength was also analyzed; the area-based momentum coefficient was determined to be a much more dominant factor than the blowing ratio and chord-based momentum coefficient.