Comparison of engine models of UHBPR turbofan at high incidence

owered-on flight is typically simulated via 1D boundary conditions (BC) at the engine entry and exit planes of the computational domain. In this paper, we apply this standard approach and two flow-coupled blade models based on an actuator disk (AD) and a body force (BFM) model to an ultra-high bypass ratio turbofan at take-off condition. The results obtained with the BC are compared to the two rotating engine representations at increasing angle of attack. The AD calibrated from 3D CFD solutions exhibits a deficit of mass flow and fan stage total pressure ratio impacting the prediction. In the investigated regime, the flow field obtained is generally homogeneous between BC and BFM, since no inlet stall has developed. The exhaust flow shows the largest differences, due to the non-uniform work input and mass flux generated by the coupled blade models, mainly due to the pylon backpressure. Engine characteristics are qualitatively captured in the AD, although influenced by the integral metrics deviation. Code-to-code comparison between Ansys Fluent and DLR TAU solver with the BC model indicates close agreement