A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section, wherein the compressor section includes a low pressure compressor and a high pressure compressor, and the high pressure compressor is arranged immediately upstream of the combustor section; a fan section having an array of twenty-six or fewer fan blades, and a fan pressure ratio of less than 1.55; a geared architecture coupling the fan section to the turbine section; and a compressor airfoil arranged in the low pressure compressor of the compressor section, the compressor airfoil comprising pressure and suction sides (72, 74) extending in a radial direction from a 0% span position to a 100% span position, wherein the low pressure compressor comprises a plurality of the compressor airfoils, and the compressor airfoils counter-rotate relative to the fan blades, characterized in that the airfoil has a relationship between an axial leading edge position and span position that defines a curve with a negative slope from 80% span to 100% span, the negative slope corresponding to a forward leaning leading edge, the forward direction defined in relation to the front of the gas turbine engine, the curve having a positive slope preceding the negative slope, the positive slope corresponding to an aft leaning leading edge, a transition between the positive and negative slope being in a range of 50% span to 75% span, the positive slope beginning at 0% span and continuing to the transition, and the airfoil has a relationship between an axial trailing edge position and span position that includes another curve with a non-linear slope from 50% span to 100% span. a combustor section arranged between a compressor section and a turbine section, wherein the compressor section includes a low pressure compressor and a high pressure compressor, and the high pressure compressor is arranged immediately upstream of the combustor section; a fan section having an array of twenty-six or fewer fan blades, and a fan pressure ratio of less than 1.55; a geared architecture coupling the fan section to the turbine section; and a compressor airfoil arranged in the low pressure compressor of the compressor section, the compressor airfoil comprising pressure and suction sides (72, 74) extending in a radial direction from a 0% span position to a 100% span position, wherein the low pressure compressor comprises a plurality of the compressor airfoils, and the compressor airfoils counter-rotate relative to the fan blades, characterized in that the airfoil has a relationship between an axial leading edge position and span position that defines a curve with a negative slope from 80% span to 100% span, the negative slope corresponding to a forward leaning leading edge, the forward direction defined in relation to the front of the gas turbine engine, the curve having a positive slope preceding the negative slope, the positive slope corresponding to an aft leaning leading edge, a transition between the positive and negative slope being in a range of 50% span to 75% span, the positive slope beginning at 0% span and continuing to the transition, and the airfoil has a relationship between an axial trailing edge position and span position that includes another curve with a non-linear slope from 50% span to 100% span.