A compressor aerofoil for a turbine engine, the compressor aerofoil comprising: a tip portion which extends from a main body portion; the main body portion defined by: a suction surface wall having a suction surface, a pressure surface wall having a pressure surface, whereby the suction surface wall and the pressure surface wall meet at a leading edge and a trailing edge, the tip portion comprising: a tip wall which extends from the aerofoil leading edge to the aerofoil trailing edge; the tip wall defining a squealer and having a tip surface; and one of the suction surface wall or pressure surface wall extends towards the tip wall such that the respective suction surface or pressure surface extends to the tip wall; a shoulder (104, 105) is provided on the other of the suction surface wall or pressure surface wall; wherein the squealer is narrower than the overall width of the main body and extends from the leading edge towards the trailing edge, wherein the shoulder (104, 105) extends between the leading edge and the trailing edge; and a transition region (108, 109) tapers from the shoulder (104, 105) in a direction to the tip wall, wherein, in cross-section, there is a smooth blend formed by the shoulder (104, 105) and the other of the suction surface wall or pressure surface wall and the transition region (108, 109) forms a sharp edge with the tip surface, the sharp edge extends along the aerofoil's length between the aerofoil's leading edge and the aerofoil's trailing edge, wherein the smooth blend comprises an intersection having an angle φ defined between a tangent of the shoulder and a tangent of the other of the suction surface wall or pressure surface wall, wherein the angle φ is preferably 0° and may be less than or equal to 5°, wherein the tip surface extends from the aerofoil leading edge to the aerofoil trailing edge; and wherein the transition region of the suction surface wall extendes from the shoulder in a direction towards the pressure surface, and at a suction surface inflexion point the transition region curves to extend in a direction away from the pressure surface toward the tip surface, or wherein the transition region of the pressure surface wall extends from the shoulder in a direction towards the suction surface, and at a pressure surface inflexion point the transition region curves to extend in a direction away from the suction surface toward the tip surface. a suction surface wall having a suction surface, a pressure surface wall having a pressure surface, whereby the suction surface wall and the pressure surface wall meet at a leading edge and a trailing edge, the tip portion comprising: a tip wall which extends from the aerofoil leading edge to the aerofoil trailing edge; the tip wall defining a squealer and having a tip surface; and a tip wall which extends from the aerofoil leading edge to the aerofoil trailing edge; the tip wall defining a squealer and having a tip surface; and one of the suction surface wall or pressure surface wall extends towards the tip wall such that the respective suction surface or pressure surface extends to the tip wall; a shoulder (104, 105) is provided on the other of the suction surface wall or pressure surface wall; wherein the squealer is narrower than the overall width of the main body and extends from the leading edge towards the trailing edge, wherein the shoulder (104, 105) extends between the leading edge and the trailing edge; and a transition region (108, 109) tapers from the shoulder (104, 105) in a direction to the tip wall, wherein, in cross-section, there is a smooth blend formed by the shoulder (104, 105) and the other of the suction surface wall or pressure surface wall and the transition region (108, 109) forms a sharp edge with the tip surface, the sharp edge extends along the aerofoil's length between the aerofoil's leading edge and the aerofoil's trailing edge, wherein the smooth blend comprises an intersection having an angle φ defined between a tangent of the shoulder and a tangent of the other of the suction surface wall or pressure surface wall, wherein the angle φ is preferably 0° and may be less than or equal to 5°, wherein the tip surface extends from the aerofoil leading edge to the aerofoil trailing edge; and wherein the transition region of the suction surface wall extendes from the shoulder in a direction towards the pressure surface, and at a suction surface inflexion point the transition region curves to extend in a direction away from the pressure surface toward the tip surface, or wherein the transition region of the pressure surface wall extends from the shoulder in a direction towards the suction surface, and at a pressure surface inflexion point the transition region curves to extend in a direction away from the suction surface toward the tip surface.