The current paper represents experimental and computational investigation for the aerodynamic characteristics of a linear compressor cascade. The experimental part has been realized by installing a cascade of axial blades in an open loop wind tunnel and acquiring the corresponding flow conditions having Reynolds number of 2.87× 105. The measurements include the static pressure distribution on the end-wall by employing static pressure tabs connected to digital micro-manometer. The 3-D flow velocity as well as both the static and the total pressure through the flow passage between the blades have been measured using a calibrated five-hole pressure probe connected with a data acquisition system. Moreover, the total pressure loss coefficient through the cascade is calculated from the measurements of the total pressure through the flow field between the two successive experimental blades. At this flow conditions, regions of corner separation are appeared. Throughout these regions, the velocity has been reduced and the total pressure as well as the flow are reversed; these features of the flow can lead to flow blockage. In the second part of this work, the linear compressor cascade flow features have been investigated using computational fluid dynamics calculations. A computational domain has been solved against the flow governing equations (continuity and momentum) with the help of an appropriate turbulence models. Separation lines and flow vortices were predicted and measured through this study which enhanced understanding the loss mechanism in compressor cascades. The results obtained here demonstrated a good agreement between the experimental and computational results.