The aerodynamic performance of high-lift blades was experimentally investigated at different Reynolds numbers ranging from 0.8×10 5 to 1.8×10 5 . Upstream wakes, inherent in real aero-engines, were generated by moving bars operating at reduced frequencies (Fr) of 0.3 and 0.6. Measurements were carried out by pneumatic probes and static pressure taps on the blade surfaces. The results show that high-lift blades experience a significant rise in profile loss under steady conditions, which is mitigated by upstream wakes due to the suppressed separation bubble. The loading distributions relate the non-dimensional flow deceleration rate (DR) to the profile loss. It is found that the variation pattern depends on the flow state, which is classified into parabolic increase, linear increase, and concave parabolic variation. A single hot-wire probe was employed to measure the boundary layer at the trailing edge. The results are used to examine the modified loss model based on Denton’s method.