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This paper examines the effects of trailing-edge jet entrainment on the streamwise vortices over a delta wing. Although studies have examined the effects of leading-edge suction and blowing on the burst location of delta wing vortices, very little research has focused on the effects of trailing-edge jet exhaust on the burst location. Using a 60-deg delta wing model in a water tunnel with dye to mark the vortex core, it was possible to visualize how the location of the vortex breakdown changes with trailing-edge jet velocity. This research has determined that at moderate angles of attack it is possible to delay the burst location up to 18% of the chord by increasing the flow velocity from the exhaust ports. In addition, at higher angles of attack, the trailing-edge jets stabilized the asymmetric separated vortices by reattaching the flow and moving the burst location aft on the wing.

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