A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section; a fan section; and a geared architecture coupling the fan section to the turbine section or the compressor section, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged immediately upstream of the combustor section, and the low pressure compressor comprises an airfoil comprising: pressure and suction sides (72, 74) and extending in a radial direction from a 0% span position to a 100% span position; a camber mean line that lies equidistant between the exterior surface of the pressure and suction sides (72, 74); a first line tangent to the camber mean line at a leading edge of the airfoil; a second line tangent to the camber mean line at a trailing edge of the airfoil; a leading edge angle (β1*) defined between a first tangential plane normal to an engine axis and the first line; a trailing edge angle (β2*) defined between a second tangential plane normal to the engine axis and the second line; and a camber angle (θ) defined as the difference between the trailing edge angle (β2*) and the leading edge angle (β1*); and characterised in that the airfoil has a relationship between the camber angle (θ) and span position with the camber angle (θ) continually increasing to define a curve (88, 90, 92) having a positive slope from 0% span to 100% span; and in that the camber angle (θ) is less than 20° at 0% span. a combustor section arranged between a compressor section and a turbine section; a fan section; and a geared architecture coupling the fan section to the turbine section or the compressor section, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged immediately upstream of the combustor section, and the low pressure compressor comprises an airfoil comprising: pressure and suction sides (72, 74) and extending in a radial direction from a 0% span position to a 100% span position; a camber mean line that lies equidistant between the exterior surface of the pressure and suction sides (72, 74); a first line tangent to the camber mean line at a leading edge of the airfoil; a second line tangent to the camber mean line at a trailing edge of the airfoil; a leading edge angle (β1*) defined between a first tangential plane normal to an engine axis and the first line; a trailing edge angle (β2*) defined between a second tangential plane normal to the engine axis and the second line; and a camber angle (θ) defined as the difference between the trailing edge angle (β2*) and the leading edge angle (β1*); and pressure and suction sides (72, 74) and extending in a radial direction from a 0% span position to a 100% span position; a camber mean line that lies equidistant between the exterior surface of the pressure and suction sides (72, 74); a first line tangent to the camber mean line at a leading edge of the airfoil; a second line tangent to the camber mean line at a trailing edge of the airfoil; a leading edge angle (β1*) defined between a first tangential plane normal to an engine axis and the first line; a trailing edge angle (β2*) defined between a second tangential plane normal to the engine axis and the second line; and a camber angle (θ) defined as the difference between the trailing edge angle (β2*) and the leading edge angle (β1*); and characterised in that the airfoil has a relationship between the camber angle (θ) and span position with the camber angle (θ) continually increasing to define a curve (88, 90, 92) having a positive slope from 0% span to 100% span; and in that the camber angle (θ) is less than 20° at 0% span. the airfoil has a relationship between the camber angle (θ) and span position with the camber angle (θ) continually increasing to define a curve (88, 90, 92) having a positive slope from 0% span to 100% span; and in that the camber angle (θ) is less than 20° at 0% span.