Gas turbine engine airfoil

摘要

A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.