A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0° view. The various views include the 0° view which projects into an axial plane in the axial direction. A 90° view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0° and 90° views. The airfoil has a maximum leading edge projection in a 20° to 40° view. The radial direction is normal to the axial and tangential directions.