The effect of sweep angle and taper ratio on the formation of separated flows over finite wings with 𝑠𝐴𝑅 = 2 at 𝑅𝑒𝑐 = 247,500 is demonstrated. Using these flow physics insights, the optimal spanwise location for steady blowing to reduce the reversed flow region over a tapered planform is presented. The 𝜆 = 0.269 tapered wing has a 30◦ forward swept trailing edge and an unswept leading edge, which is shown to form the inverted ram’s horn post-stall. The inverted ram’s horn vortex forms near the wing tip and grows in diameter towards the wing root. When active flow control, via steady blowing, is applied slightly inboard of the midspan, it creates a virtual fence where the inverted ram’s horn is diverted and the flow is reattached inboard of the jet. With full-span steady blowing, the flow is completely reattached at 𝛼 = 18◦.