A series of three convergent round-to-rectangular high-aspect ratio nozzles were designed for acoustics measurements. The nozzles have exit area aspect ratios of 8:1, 12:1, and 16:1. With septa inserts, these nozzles will mimic an array of distributed propulsion system nozzles, as found on hybrid wing-body aircraft concepts. Analyses were performed for the three nozzle designs and showed that the flow through the nozzles was free of separated flow and shocks. The exit flow was mostly uniform with the exception of a pair of vortices at each span-wise end of the nozzle.
Design and Analyses of High Aspect Ratio Nozzles for Distributed Propulsion Acoustic Measurements
2016
27 pages
Report
No indication
English
Aircraft , Test Facilities & Equipment , Acoustic measurement , Computational fluid dynamics , Separated flow , Turbulence models , Design analysis , Free flow , High aspect ratio , Navier-stokes equation , Nozzle design , Partitions (structures) , Propulsion , Reynolds averaging , Boundary layers , Computerized simulation , Control surfaces , Shock waves , Structured grids (mathematics) , Vanes , Vortices
British Library Conference Proceedings | 2016
|