A compressor aerofoil for a turbine engine, having a suction surface wall and a pressure surface wall meeting at a leading edge and trailing edge, a tip plate extends between the walls and has a first and a second tip rib extending therefrom. At least one of the first and second tip rib has a height extending from the tip plate. A camber line is defined as passing through the leading and trailing edge and the camber line length is from the leading to trailing edge along the tip plate. The first and second tip rib define a slot along the camber line of the aerofoil. The first tip rib is located a distance L1 from the leading towards the trailing edge and the second tip rib is located a distance L2 from the leading edge, the distances L1 and L2 greater than 1% of the camber line length.