Turbine engine airfoil

A stator vane structure for a turbine engine, comprising:

• a first platform;
• a second platform;
• and
• a plurality of stator vanes arranged circumferentially about an axis in an array, each of the plurality of stator vanes comprising an airfoil;
• the airfoil including a leading edge, a trailing edge, a pressure side and a suction side;
• the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first platform to the second platform;
• the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil defined by a set of Cartesian coordinates which includes each Cartesian coordinate set forth in Table 1, wherein the set of Cartesian coordinates have a tolerance of +/−0.050 inches;
• the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location;
• and
• the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.

A turbine engine, comprising:

• a flowpath, a compressor section, a combustor section and a turbine section;
• the flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
• the turbine section including a plurality of turbine vanes arranged circumferentially about an axis in an array, each of the plurality of turbine vanes comprising an airfoil located in the flowpath;
• the airfoil including a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side;
• the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil;
• the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil defined by a set of Cartesian coordinates which includes each Cartesian coordinate set forth in Table 1;
• the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location;
• and
• the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.