Abstract: A nozzle system for providing improved thrust augmentation for an aircraft lift and/or propulsion system is provided. The unique nozzle structure is designed such that counter-rotating vortices emanate from the nozzle tips. When this unique nozzle configuration is combined with simple slot nozzles in a specific manner a vortex rich flow will result. When a diffuser is placed around this unique combination such that jet pumping is obtained, significant improvement in thrust augmentation is realized from the vortex rich flow mixing with the coflowing secondary air stream.