Boundary layer ingestion is a concept that can reduce the power requirement of an aircraft. The ingestion of the boundary layer creates non-uniform fan inflow conditions. This thesis work aims to research the effect of installation in a propulsive fuselage concept on fan performance. On top of this, the effect of fan installation on the propulsive fuselage concept itself is evaluated. Through experimental work, the effect of installation on the fan has been mapped. The effect of fan operation on the propulsive fuselage has been investigated through the use of RANS simulations utilising an actuator volume model. The experimental work has shown that the fan deals with a drop in flow coefficient due to installation with favourable behaviour in the hub region. Numerical data support this finding. Moreover, a momentum excess has a disproportional effect on the kinetic energy deposition rates in the jet wake.