This paper presents a numerical investigation of a fluidic thrust vectoring nozzle based on the coflow Coanda method applied to a medium-mass unmanned airborne system on the basis of the Aero Design Works B300STG turbojet engine. The main objective is to numerically study its general steady and transient behaviour and to provide data for subsequent investigations regarding its performance in case of an implementation into a generic unmanned aerial system. The numerical studies show that two-dimensional simulation results can be transferred with minor discrepancies to a fully three-dimensional rectangular fluidic thrust vectoring nozzle. Furthermore, investigations on chosen geometric parameters, namely the Coanda Radius R and the height of the secondary channel h_s show that maximum thrust deflection angles of up to beta = 30° are achievable. Transient simulations reveal a very fast convergence of the thrust vector angle towards a steady value which positively influences its controllability. Additionally, fluidic thrust vectoring performance investigated at chosen flight points in altitudes ranging from h = 10000 ft - 30000 ft and Mach numbers from Ma = 0.3 - 0.9 shows overall good performance. In these flight cases, maximum thrust deflection angles of up to beta = 25° are achieved. However, these investigations have shown that for future fluidic thrust vectoring performance studies the nozzles tailored integration into the aircrafts nacelle is recommended to be taken into account to realise its maximum potential.    «

This paper presents a numerical investigation of a fluidic thrust vectoring nozzle based on the coflow Coanda method applied to a medium-mass unmanned airborne system on the basis of the Aero Design Works B300STG turbojet engine. The main objective is to numerically study its general steady and transient behaviour and to provide data for subsequent investigations regarding its performance in case of an implementation into a generic unmanned aerial system. The numerical studies show that two-dime...    »