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 . <EOS>