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 or equal to about 1.7;
• a geared architecture coupling the fan section to the turbine section or the compressor section;
• and
• wherein the fan blades include a root, and an airfoil having pressure and suction sides extending from the root 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 has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope, the positive slope leans toward the suction side and the negative slope leans toward the pressure side, wherein a zero tangential stacking offset corresponds to tangential center of the root, and the 0% span position is offset from the zero tangential stacking offset, wherein the first critical point is less than 15% span.