It the early 1970s Saab-Scania experimented with a wing similar to this drawing.   In this experimented a jet of air is blown toward the tip to energize the axial flow.  They found that by centering the blower nozzle in the vortex core the wing produced a C_Lmax of 4.45 at Re=150,000.   On highly swept wings the axial flow is naturally pushed along by the strong spanwise flow, but on wings with little or no sweep the spanwise flow is rather weak so new fluid being entrained into the vortex has no energy pushing it toward the tip and may stagnate in the core thus causing the inner radius to expand until the vortex bursts.  In terms of mechanical complexity and power requirement this system compares favorably with other power augmented lift systems used in short takeoff and landing (STOL) cargo planes but the need to center the nozzle in the vortex core may be a problem because as the aircraft's lift requirements change the vortex may move around a bit. There is also some question as to whether a jet will be effective over a practical span.