In summary, the invention relates to a compressor stator vane (14) for axial compressors (10), comprising a cantilevered airfoil (22) attached to a compressor casing (18) via a blade root, the airfoil (22) comprising an airfoil tip (28) extending from a leading edge (34) to a trailing edge (35). To improve aerodynamic efficiency, a corrugated airfoil tip (28) is suggested, exposing a wave-like shape having at least one wave crest (38). To further reduce parasitic secondary leakage flows, the airfoil tip (28) comprises a first trough (42) and a second wave crest (40). The amplitude of the first crest (38) is larger than the amplitude of the second crest (40). Furthermore, the facing rotor hub endwall (30) may be formed correspondingly. Thus, tip leakage swirl length and position is shifted upstream substantially thereby reducing overall tip losses and minimising blockage of the flow passage which both improves compressor efficiency.