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 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 blade comprising an airfoil and a root arranged in the compressor section, the compressor airfoil comprising pressure and suction sides extending in a radial direction (R) relative to an engine axis (X-X) from a 0% span position at the radially innermost location of the airfoil to a 100% span position at the radially outermost location of the airfoil , 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 , the blade is provided in the low pressure compressor ; the low pressure compressor blade is counter-rotating relative to the fan blades; the low pressure compressor is immediately downstream from the fan section ; and characterized in that the airfoil has a relationship between an axial stacking offset (X d ) and span position that includes a curve with a negative slope from 90% span to 100% span, wherein the axial stacking offset (Xd) corresponds to the axial distance from an axial centre of the root of the blade to the centre of gravity (X CG ) at a given span location of the airfoil relative to the engine axis (X-X), and the negative slope means that that span section of the airfoil leans forward relative to the engine axis (X-X). 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 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 blade comprising an airfoil and a root arranged in the compressor section, the compressor airfoil comprising pressure and suction sides extending in a radial direction (R) relative to an engine axis (X-X) from a 0% span position at the radially innermost location of the airfoil to a 100% span position at the radially outermost location of the airfoil , 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 , the blade is provided in the low pressure compressor ; the low pressure compressor blade is counter-rotating relative to the fan blades; the low pressure compressor is immediately downstream from the fan section ; and characterized in that the airfoil has a relationship between an axial stacking offset (X d ) and span position that includes a curve with a negative slope from 90% span to 100% span, wherein the axial stacking offset (Xd) corresponds to the axial distance from an axial centre of the root of the blade to the centre of gravity (X CG ) at a given span location of the airfoil relative to the engine axis (X-X), and the negative slope means that that span section of the airfoil leans forward relative to the engine axis (X-X). <EOS>