Gas turbine engine airfoil profile

A gas turbine engine comprising:

• a compressor section;
• a combustor section fluidly connected to said compressor section;
• a turbine section fluidly connected to said combustor section, said turbine section including a mid-turbine frame;
• wherein said mid-turbine frame includes at least one airfoil, wherein said at least one airfoil includes an airfoil body having a leading edge and a trailing edge joined by a pressure side and a suction side that is spaced from said pressure side to provide an external airfoil surface extending in a radial direction from at least one platform;
• and
• wherein said external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of said at least one airfoil described by a set of Cartesian coordinates set forth in Table 1, said Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein said local axial chord corresponds to a width of the airfoil between said leading edge and said trailing edge at said span location and said Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to ±0.050 inches (±1.27 mm).