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The goal of this research is the control of leading-edge vortex breakdown location utilizing along-the-core blowing near the apex on the leeward surface of sharp-edged, slender, delta wings at high angles of attack. In the S2Ch subsonic wind tunnel at ONERA Chalais-Meudon, two delta wing models with 70-deg sweep angles and root chords of 950 mm have been con gured to collect qualitative and quantitative surface and ow eld data. First, an examination of the streamwise, time-dependent oscillationdoi:10.2514/2.1059 fatcat:bfw6svk72rb3vfys4xgi4kz2ya