Gas turbine engine airfoil

A gas turbine engine comprising:

• a combustor section arranged between a compressor section and a turbine section;
• a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a low fan pressure ratio of less than 1.55;
• a geared architecture coupling the fan section to the turbine section or the compressor section;
• and
• wherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve, wherein the airfoil extends from a root, and a zero axial reference point corresponds to axial center of the root, XLE corresponds to an axial distance from a leading edge to the reference point at a given span position, XTE corresponds to an axial distance from a trailing edge to the reference point at a given span position, Xd corresponds to an axial stacking offset at a given span position, wherein (XLE−Xd)/(Xd−XTE) at 100% span position is 1+/−0.10 and (XLE Xd)/(Xd−XTE) at 90% span position is 1+/−0.10.