Results from a wind tunnel experiment will be used to confirm that Tangential Leading Edge Blowing is capable of controlling the vortical flow over a delta wing to very high angles of attack. The production of significant rolling moments and the ability to unburst a vortex has been demonstrated to 55 angle of attack. Strain gauge balance measurements and upper surface pressure distributions will be presented which illustrate the various modes of operation and which, in particular, identify the uncoupled/coupled nature of the vortex control at pre- and post-stall angles of attack. At angles of attack beyond 40°, rolling moments are produced that exceed those produced by 20 of aileron deflection at 0 angle of attack.