A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.