Gas turbine engine fan blade airfoil profile

A gas turbine engine comprising:

• a compressor section;
• a combustor fluidly connected to the compressor section;
• a turbine section fluidly connected to the combustor, the turbine section comprising:
• a high pressure turbine coupled to the high pressure compressor via a shaft;
• a low pressure turbine;
• and
• a fan section operatively coupled to the turbine section, wherein the fan section includes an array of fan blades, wherein at least one fan blade includes an airfoil having leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface extending from in a radial direction to a tip;
• and
• wherein the external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates 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, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.