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This paper presents an experimental and computational study of a novel passive version of the air jet vortex generator flow control system for the delay or suppression of trailing edge boundary layer separation and subsequent stall. The results show that a passive vortex generating jet flow control system can effectively delaying trailing edge separation and subsequent stall to higher angles of attack, without the need for any active energy input and without significant drag penalty. Nomenclature α Angle of attack (deg) c Chord length (m) C A Axial force coefficient C D Drag force coefficient C L Lift force coefficient C M 1 / 4 chord pitching moment coefficient C µ Blowing momentum coefficient Cp Pressure coefficient m & Mass flow rate through AJVG duct (kg/s) p Static Pressure (N/m 2 ) p 0 Total Pressure (N/m 2 ) ρ Density (kg/m 3 ) U Velocity (m/s) S Reference (model planform) area (m 2 ) x Chordwise distance from leading-edge (m) y Spanwise distance from model centre (m) z Distance normal to the chordline (m) Subscripts: 1 Local conditions ∞ Freestream conditions j

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