One of the important issues in the assessment of the Net/engine compatibility in turbofan engines is to predict the coupling effects between the non-uniform inlet and engine. The computational method using an actuator-disk model has been applied to the calculations of the flow through a civil high-bypass-ratio turbofan engine with drooped intake and the flow through a multistage turbofan engine subjected to non-uniform total pressure inlet flow. The results of a series of calculations are presented and the nature of the interactions between the flow through a fan and non-uniform inlet flow is addressed.