A compressor airfoil of a gas turbine engine, the compressor airfoil defining a span-wise axis and comprising: a pressure side and a suction side extending downstream from a stagnation point, the suction side being generally convex in shape; the suction side including a suction side surface portion within a leading edge region, and a main suction side airfoil surface downstream from the suction side surface portion and extending contiguously therewith; the suction side surface portion has a compound curvature profile, the compound curvature profile comprising at least a leading edge having a first curvature profile and a chamfered surface having a second curvature profile different from the first curvature profile, the chamfered surface being contiguous with and extending immediately downstream from the leading edge, the first curvature profile being curved, the second curvature profile of the chamfered surface being substantially flat and defining a substantially straight-line profile in a cross-section transverse to the span-wise axis of the airfoil, wherein the suction side surface portion further comprises a third curvature profile different from both the second curvature profile of the chamfered surface and the first curvature profile of the leading edge, the third curvature profile defining a curve surface contiguous with and extending downstream from the chamfered surface, the curve surface also being contiguous with and upstream from the main suction side airfoil surface, characterised in that the first curvature profile of the leading edge defines a continuously increasing radius of curvature, and the curve surface is a blended curve surface. a pressure side and a suction side extending downstream from a stagnation point, the suction side being generally convex in shape; the suction side including a suction side surface portion within a leading edge region, and a main suction side airfoil surface downstream from the suction side surface portion and extending contiguously therewith; the suction side surface portion has a compound curvature profile, the compound curvature profile comprising at least a leading edge having a first curvature profile and a chamfered surface having a second curvature profile different from the first curvature profile, the chamfered surface being contiguous with and extending immediately downstream from the leading edge, the first curvature profile being curved, the second curvature profile of the chamfered surface being substantially flat and defining a substantially straight-line profile in a cross-section transverse to the span-wise axis of the airfoil, wherein the suction side surface portion further comprises a third curvature profile different from both the second curvature profile of the chamfered surface and the first curvature profile of the leading edge, the third curvature profile defining a curve surface contiguous with and extending downstream from the chamfered surface, the curve surface also being contiguous with and upstream from the main suction side airfoil surface, characterised in that the first curvature profile of the leading edge defines a continuously increasing radius of curvature, and the curve surface is a blended curve surface.