Gas turbine engine airfoil

1. A gas turbine engine comprising:

a combustor section arranged between a compressor section and a turbine section, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged upstream of the combustor section;

a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a fan pressure ratio of less than 1.55, wherein the low pressure compressor is downstream from the fan section, the low pressure compressor is counter-rotating relative to the fan blades;

a geared architecture coupling the fan section to the turbine section or the compressor section; and

an airfoil arranged in the low pressure compressor and including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear, wherein the curve transitions from the positive slope to the negative slope in a range of 60% span to 75% span.

2. The gas turbine engine according to claim 1 , wherein the gas turbine engine is a two-spool configuration.

3. The gas turbine engine according to claim 1 , wherein the airfoil is rotatable relative to an engine static structure.

4. The gas turbine engine according to claim 1 , wherein the curve has a negative slope from 90% span to 100% span.

5. The gas turbine engine according to claim 4 , wherein the curve has a negative slope from 80% span to 100% span.

6. The gas turbine engine according to claim 1 , wherein the curve has a positive slope beginning at 0% span, where the positive slope leans toward the suction side.

7. The gas turbine engine according to claim 6 , wherein the positive slope extends from 0% span to 40% span.