Fan blade or vane with improved bird impact capability

A gas turbine engine, comprising:

• an airfoil;
• and
• an adjacent airfoil, which is adjacent to the airfoil and which at least partially overlaps the airfoil in a circumferential dimension,
• wherein the airfoil comprises:
• a suction surface exhibiting droop over a first 5% of an airfoil chord, after which a suction surface metal-angle distribution decreases flatly along a flat suction surface region to where the adjacent airfoil at least partially overlaps the airfoil in the circumferential dimension,
• wherein:
• following the flat suction surface region, the suction surface metal-angle distribution exhibits a bump of an airfoil covered-passage starting position, and
• following a precompression region, the suction surface metal-angle distribution is linear along a linear section, except at front and end points of the linear section, where the linear section blends into precompression and trailing-edge locations, respectively.