The German Aerospace Center (DLR) has designed and tested a 1:3 scaled model S-shaped
fan rotor as an example for a medium pressure ratio propulsor with potential application to
future UHBR aero engines. In the present study, the attention will focus on the tip region
in which the flow field is subject to complex flow phenomena and to the impact of the Sshape
feature on the radial shock structure. Steady numerical simulations with DLR in-house
solver TRACE as well as measurements were carried out. The casing is instrumented with ten
piezoelectric static pressure transducers over the rotor pitch. Particle Image Velocimetry (PIV)
is used to catch the flow velocities at three radial blade positions. All experimental data require
a phase-locked ensemble averaging procedure. The results include the global performance of
the compressor and detailed comparisons between simulations and measurements to validate
the shock structures as well as the highly three dimensional-design S-shape fan
