The numerical investigation has been performed to explore the feasi-bility of vortex control by leading edge sucking excitation on a delta wing. The resultsreveal that the flow on the upper surface of the delta wing changes significantly in awide range of the angle of attack. For the vortical flow at moderate angle of attack,the secondary and tertiary vortices are weakened or suppressed, and the total liftis almost unchanged. For the stalled flow at high angle of attack, the leading edgeconcentrated vortex is recovered, and the lift is enhanced with increasing suction rate.For the bluff-body flow at even high angles of attack, the lift can still be improved.The concentrated vortex disappears on the upper surface, and the load increment isnearly unchanged along the chordwise direction.
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