Various configurations of a cropped delta wing featuring a NACA 0012 wing-section were evaluated experimentally at a Reynolds number of 5.0 x 105 in the Air Force Institute of Technology Low-Speed Wind Tunnel facility. The effects of active flow control (AFC) and passive boundary-layer fences (BLF) were shown to improve high angle of attack delta wing performance. The AFC BLFs were shown to replicate the performance enhancements found in passive BLFs without incurring a drag penalty. An experimental characterization of the wake region is presented to compare the wake roll-up and leading edge vortices for these baseline, passive BLF, and AFC BLF delta wing configurations. Using a tuft mesh and a constant temperature anemometry triple wire probe, the wake was characterized at several discrete planes of interest aft of the trailing edge. This wake data was used to elucidate causes for AFC BLF configuration increasing the maximum lift coefficient by 60.3%. The present study shows this aerodynamic improvement is largely attributed to: 1) strengthening the leading edge vortex (LEV), which delays vortex breakdown, and 2) truncating spanwise flow
