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 1.55; a geared architecture coupling the fan section to the turbine section or the compressor section ; and a compressor airfoil arranged in the compressor section , the compressor airfoil comprising pressure and suction sides and extending in a radial direction (R) from a 0% span position at a radially inner position to a 100% span position at a radially outer position; wherein the compressor section includes at least a low pressure compressor and a high pressure compressor , and the high pressure compressor is arranged immediately upstream of the combustor section and the airfoil is provided in the low pressure compressor ; wherein the low pressure compressor comprises low pressure compressor blades that are counter-rotating relative to the fan blades; and wherein the low pressure compressor is immediately downstream from the fan section ; wherein the trailing edge angle (β 2 ∗ ) of the compressor airfoil is the angle between a tangential plane (PR) normal to the engine axis (X) and a line tangent to a camber mean line (ML) at a trailing edge of the airfoil and is measured from the line towards the suction side of the airfoil ; characterized in that the airfoil has a relationship between a trailing edge angle (β 2 ∗ ) and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle (β 2 ∗ ). 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 1.55; a geared architecture coupling the fan section to the turbine section or the compressor section ; and a compressor airfoil arranged in the compressor section , the compressor airfoil comprising pressure and suction sides and extending in a radial direction (R) from a 0% span position at a radially inner position to a 100% span position at a radially outer position; wherein the compressor section includes at least a low pressure compressor and a high pressure compressor , and the high pressure compressor is arranged immediately upstream of the combustor section and the airfoil is provided in the low pressure compressor ; wherein the low pressure compressor comprises low pressure compressor blades that are counter-rotating relative to the fan blades; and wherein the low pressure compressor is immediately downstream from the fan section ; wherein the trailing edge angle (β 2 ∗ ) of the compressor airfoil is the angle between a tangential plane (PR) normal to the engine axis (X) and a line tangent to a camber mean line (ML) at a trailing edge of the airfoil and is measured from the line towards the suction side of the airfoil ; characterized in that the airfoil has a relationship between a trailing edge angle (β 2 ∗ ) and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle (β 2 ∗ ). <EOS>