Design and numerical simulation of ejector nozzles for very small turbojet engines

Abstract The examination of small turbojet engines for unmanned aviation systems is a main research activity at the Institute Aeronautical Engineering Universität der Bundeswehr München. special requirements design these propulsion include compact installation size, high reliability and low acquisition costs. But overall efficiency, exhaust gas temperature excessive noise emission limit options integration mission profiles. concept ejector nozzles offers solution further improving system following requirements. secondary mass flow delivered from nozzle can not only reduce but also enhance thrust. Ejector have been developed in combination with mixer goal increasing pumping performance thrust augmentation. Both numerical experimental investigations are conducted to study mixing ability primary nozzle, key optimising performance.