An airfoil for a gas turbine engine comprising: a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub, and wherein: the airfoil section includes an airfoil body extending between leading and trailing edges (LE, TE) in a chordwise direction, extending between pressure and suction sides (PS, SS) separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion; the tip portion defines a stagger angle (α) relative to the root section, and the stagger angle (α) is greater than or equal to one of 5 or 15 degrees, absolute, prior to welding the first portion to the second portion along the interface; a recessed region extends inwardly from at least one of the pressure and suction sides (PS, SS); and the airfoil body includes at least one rib bounding at least one respective pocket within a perimeter of the recessed region; a cover skin welded to the airfoil body along the at least one rib to enclose the recessed region; characterized in that the recessed region is dimensioned to extend across the interface; and the at least one rib is dimensioned to extend across the interface. a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub, and wherein: the airfoil section includes an airfoil body extending between leading and trailing edges (LE, TE) in a chordwise direction, extending between pressure and suction sides (PS, SS) separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion; the tip portion defines a stagger angle (α) relative to the root section, and the stagger angle (α) is greater than or equal to one of 5 or 15 degrees, absolute, prior to welding the first portion to the second portion along the interface; a recessed region extends inwardly from at least one of the pressure and suction sides (PS, SS); and the airfoil body includes at least one rib bounding at least one respective pocket within a perimeter of the recessed region; a cover skin welded to the airfoil body along the at least one rib to enclose the recessed region; the airfoil section includes an airfoil body extending between leading and trailing edges (LE, TE) in a chordwise direction, extending between pressure and suction sides (PS, SS) separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion; the tip portion defines a stagger angle (α) relative to the root section, and the stagger angle (α) is greater than or equal to one of 5 or 15 degrees, absolute, prior to welding the first portion to the second portion along the interface; a recessed region extends inwardly from at least one of the pressure and suction sides (PS, SS); and the airfoil body includes at least one rib bounding at least one respective pocket within a perimeter of the recessed region; a cover skin welded to the airfoil body along the at least one rib to enclose the recessed region; characterized in that the recessed region is dimensioned to extend across the interface; and the at least one rib is dimensioned to extend across the interface. the recessed region is dimensioned to extend across the interface; and the at least one rib is dimensioned to extend across the interface.