Flow separation over blade surfaces is an important parameter and its reduction or elimination can improve
better aerodynamic performance, efficiency and stall margin. In this work, numerical investigation has
been carried out to study the flow separation and performance analysis of a transonic axial compressor
rotor blade at off-design operating conditions. The off-design cases studied comprised of compressor
operation at 80%, 90%, 100% and 105% on the on-design rotational speed. The results are validated with
experimental work from literature. Additionally, 3D flow visualisations and performance parameters were
examined in detail to understand the blade to blade relative mach number distributions and shock front
created by the model. Finally, the benefits of unsteady simulation on axial compressor blade performance
predictions were examined.