Research covers propulsion installation characteristics for novel air-vehicle configurations in the class of small
missile/UAVs. A modular experimental model has been developed featuring a fully integrated tail mounted inline
boundary layer ingesting (BLI) Electric Ducted Fan (EDF) propulsion system. The research aims to
investigate the aerodynamic characteristics and gain understanding of the optimisation of a fully integrated
propulsion system. A combination of experimental and validated CFD methods will be used to develop suitable
performance metrics and optimisation approaches for in-line BLI EDFs, thus enabling the generation of a toolset
to be applied in the future design and implementation of this class of propulsion system. Progress in both
experimental design and computational analysis will be presented, including initial analysis of the overall flow
physics, focussing on the upstream and downstream effect of the body boundary layer, the condition of the flow
ingested into the fan and an assessment of the performance of the overall integrated EDF.
The aerodynamic characteristics of an aft-body, in-line mounted, boundary layer ingesting, electric ducted fan, propulsion installation system has been investigated through experimental and computational analysis. A modular wind-tunnel model allows variation in the geometry of the propulsion installation system to be assessed, in combination with fan speed. Various experimental measurement techniques, including LDA, seven-hole-probe and surface pressures are employed. The propulsion installation system has also been investigated using RANS CFD and comparison with experimental data is presented. An investigation of the boundary conditions for efficiently representing the fan in CFD is described. Initial results show reasonably good agreement between CFD and experiment, in terms of velocity profiles and surface pressures, but highlight remaining differences for cases exhibiting flow separation.