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 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 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. <EOS>