The “wall stall” in compressor cascades has been observed by many research workers. There is a region of high loss in the corner bounded by the end wall and the suction surface of a blade. It is the separation of the flow in this region which is largely responsible for the increase in the axial velocity across the midspan section of the blades when there is no end-wall suction. It is important to differentiate between this wall stall and the two-dimensional stall of the blading. The work on wall stall described in the paper was carried out at the University of Cambridge and the University of Liverpool in the period 1955-1962.

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