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 ; 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 a compressor airfoil arranged in the low pressure compressor , the compressor airfoil comprising pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, the 0% span position corresponding to a radially innermost span position, wherein the high pressure compressor is arranged immediately upstream of the combustor section , the low pressure compressor having blades which are counter-rotating relative to the fan blades , and the low pressure compressor is immediately downstream from the fan section ; characterized in that the airfoil has a relationship between leading edge sweep angle (σ LE ) and span position defined by a curve (110; 112; 114; 116) in which the leading edge sweep angle (σ LE ) is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span, wherein a negative sweep angle is in the forward direction with respect to the orientation established by the velocity vector (VrLE), and a positive sweep angle is in the rearward direction with respect to the orientation established by the velocity vector (VrLE), and wherein: the airfoil has a relationship between trailing edge sweep angle (σTE) and span position defined by a curve (118; 120) in which the trailing edge sweep angle (σTE) is negative at 0% span and changes less than 10° from 0% span to 90% span; or the airfoil has a relationship between trailing edge sweep angle (σ TE ) and span position defined by a curve (122; 124) in which the trailing edge sweep angle (σ TE ) is positive at 0% span and has a decrease in trailing edge sweep angle (σ TE ) of greater than 10° from 0% span to 40% span. 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 ; 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 a compressor airfoil arranged in the low pressure compressor , the compressor airfoil comprising pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, the 0% span position corresponding to a radially innermost span position, wherein the high pressure compressor is arranged immediately upstream of the combustor section , the low pressure compressor having blades which are counter-rotating relative to the fan blades , and the low pressure compressor is immediately downstream from the fan section ; the airfoil has a relationship between trailing edge sweep angle (σTE) and span position defined by a curve (118; 120) in which the trailing edge sweep angle (σTE) is negative at 0% span and changes less than 10° from 0% span to 90% span; or the airfoil has a relationship between trailing edge sweep angle (σ TE ) and span position defined by a curve (122; 124) in which the trailing edge sweep angle (σ TE ) is positive at 0% span and has a decrease in trailing edge sweep angle (σ TE ) of greater than 10° from 0% span to 40% span. <EOS>