A turbine blade for a gas turbine engine, the turbine blade comprising: a platform having a radially inner side and a radially outer side; a root portion extending from the radially inner side of the platform; and an airfoil extending from the radially outer side of the platform, the airfoil including: a pressure side extending between a leading edge and a trailing edge; a suction side extending between the leading edge and the trailing edge, and a bowed tip portion extending perpendicular to a mid-camber line of the airfoil, such that the bowed tip portion is bowed to extend towards the suction side in a circumferential direction and towards the trailing edge in an axial downstream direction, characterised in that: the bowed tip portion begins at between 75% and 85% of a span of the airfoil; said bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion between 2 degrees at a radially innermost part of the bowed tip portion and 15 degrees at a tip of the airfoil relative to a radial direction perpendicular to the mid-camber line in the circumferential direction; the bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion at an angle (β) between 3 degrees at a radially innermost part of the bowed tip portion and 19.6 degrees at a tip of the airfoil relative to the radial direction perpendicular to the mid-camber line in the axial direction; the bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion by the same degree relative to the radial direction in both the circumferential direction and the axial direction; and the bowed tip portion follows a curvilinear profile at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion beginning at 3 degrees and increasing to 19.6 degrees relative to a radial direction at a tip of the airfoil in the axial direction. a platform having a radially inner side and a radially outer side; a root portion extending from the radially inner side of the platform; and an airfoil extending from the radially outer side of the platform, the airfoil including: a pressure side extending between a leading edge and a trailing edge; a suction side extending between the leading edge and the trailing edge, a pressure side extending between a leading edge and a trailing edge; a suction side extending between the leading edge and the trailing edge, and a bowed tip portion extending perpendicular to a mid-camber line of the airfoil, such that the bowed tip portion is bowed to extend towards the suction side in a circumferential direction and towards the trailing edge in an axial downstream direction, characterised in that: the bowed tip portion begins at between 75% and 85% of a span of the airfoil; said bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion between 2 degrees at a radially innermost part of the bowed tip portion and 15 degrees at a tip of the airfoil relative to a radial direction perpendicular to the mid-camber line in the circumferential direction; the bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion at an angle (β) between 3 degrees at a radially innermost part of the bowed tip portion and 19.6 degrees at a tip of the airfoil relative to the radial direction perpendicular to the mid-camber line in the axial direction; the bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion by the same degree relative to the radial direction in both the circumferential direction and the axial direction; and the bowed tip portion follows a curvilinear profile at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion beginning at 3 degrees and increasing to 19.6 degrees relative to a radial direction at a tip of the airfoil in the axial direction. the bowed tip portion begins at between 75% and 85% of a span of the airfoil; said bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion between 2 degrees at a radially innermost part of the bowed tip portion and 15 degrees at a tip of the airfoil relative to a radial direction perpendicular to the mid-camber line in the circumferential direction; the bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion at an angle (β) between 3 degrees at a radially innermost part of the bowed tip portion and 19.6 degrees at a tip of the airfoil relative to the radial direction perpendicular to the mid-camber line in the axial direction; the bowed tip portion is bowed at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion by the same degree relative to the radial direction in both the circumferential direction and the axial direction; and the bowed tip portion follows a curvilinear profile at a leading edge of the bowed tip portion or a trailing edge of the bowed tip portion beginning at 3 degrees and increasing to 19.6 degrees relative to a radial direction at a tip of the airfoil in the axial direction.