Abstract: The dual throat nozzle (DTN) technique is capable to achieve higher thrustvectoring efficiencies than other fluidic techniques, without compromising thrust efficiency significantly during vectoring operation. The excellent ...

Abstract: The bypass dual throat nozzle (BDTN) does not consume any secondary injection from the other part of the engine, while it can produce steady and efficient vectoring deflection similar to the conventional dual throat nozzle ...

Abstract: The bypass dual throat nozzle (BDTN) is a new kind of fluidic vectoring nozzle. A bypass is set between the upstream convergent section and upstream minimum area based on the conventional dual throat nozzle (DTN). The BDTN ...

Abstract: Turbinebased combinedcycle (TBCC) propulsion systems have been a topic of research as a means for more efficient flight at supersonic and hypersonic speeds. The present study focuses on the fundamental physics of the complex ...

Abstract: Compared to the conventional axisymmetric dual throat nozzle, the axisymmetric divergent dual throat nozzle (ADDTN) can offer larger thrust vector angles. However, the starting problem maybe exists in the ADDTN and results ...

Abstract: Compared to other engines, turbine-based combined cycle (TBCC) engine is one of the most suitable propulsion systems for hypersonic vehicle. Because of its fine reusability, wide flight envelope, and safety margins, TBCC ...

Abstract: Turbofan engines with afterburners usually have variable nozzle throat area, and the nozzle throat area may increase by 50–100% during afterburning. An axisymmetric divergent bypass dual throat nozzle (ADBDTN) can offer ...