The experimental investigation of a transonic and a supersonic aspirated compressor cascades was conducted in this paper. The aspirated compressor cascades were designed to improve the blade performance by sucking air on a slot. Various operating states were achieved by changing the slot location

the sucking air mass-flow

the sock location and the shock intensity. Generally

sucking air after the shock and before the separation had some beneficial effects in controlling the boundary separation and decreasing the loss. Then

the loading of blades was improved. The effects were especially prominent when there were strong shocks and strong boundary separations as a result of interaction between shock and boundary. There is a threshold of bleed air output for the transonic cascade

and also a threshold of sucking air mass-flow. Beyond it

suction can reduce the separation

weaken the loss and improve the performance.