An airfoil (600; 700) for a gas turbine engine, the airfoil comprising: an airfoil body having a leading edge (606; 706) and a trailing edge (608; 708), a root region (610; 710) and a tip region (612; 712), wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from the root region to the tip region; a forward-flowing serpentine flow path (602; 702) formed within the airfoil body, the forward-flowing serpentine flow path defined by a first serpentine cavity (618; 732), a second serpentine cavity (620; 720), and a third serpentine cavity (622; 722), wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity; a flag tip cavity (604; 704) extending aftward from proximate the leading edge to the trailing edge along the tip region of the airfoil body; and a hybrid trailing edge cavity, wherein the first serpentine cavity is part of the hybrid trailing edge cavity, wherein the forward-flowing serpentine flow path (602; 702), the flag tip cavity (604; 704), and the hybrid trailing edge cavity are arranged to supply a cooling air flow into the forward-flowing serpentine flow path from a hybrid trailing edge feed cavity inlet at the hybrid trailing edge cavity, the cooling air flow passing through the first serpentine cavity, the second serpentine cavity, the third serpentine cavity, into and through the flag tip cavity, and exiting through the trailing edge of the airfoil body, wherein the hybrid trailing edge cavity and the airfoil body are arranged such that a portion of the cooling air flow exits the hybrid trailing edge cavity at the trailing edge of the airfoil body, and characterized in that: a first shielding cavity (614; 714) and a second shielding cavity (616; 716) are located on a pressure side of the airfoil body between a portion of the forward-flowing serpentine flow path and an external pressure side of the airfoil body, wherein the first shielding cavity (614; 714) and the second shielding cavity (616; 716) extend radially through the airfoil body from the root region to the tip region. an airfoil body having a leading edge (606; 706) and a trailing edge (608; 708), a root region (610; 710) and a tip region (612; 712), wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from the root region to the tip region; a forward-flowing serpentine flow path (602; 702) formed within the airfoil body, the forward-flowing serpentine flow path defined by a first serpentine cavity (618; 732), a second serpentine cavity (620; 720), and a third serpentine cavity (622; 722), wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity; a flag tip cavity (604; 704) extending aftward from proximate the leading edge to the trailing edge along the tip region of the airfoil body; and a hybrid trailing edge cavity, wherein the first serpentine cavity is part of the hybrid trailing edge cavity, wherein the forward-flowing serpentine flow path (602; 702), the flag tip cavity (604; 704), and the hybrid trailing edge cavity are arranged to supply a cooling air flow into the forward-flowing serpentine flow path from a hybrid trailing edge feed cavity inlet at the hybrid trailing edge cavity, the cooling air flow passing through the first serpentine cavity, the second serpentine cavity, the third serpentine cavity, into and through the flag tip cavity, and exiting through the trailing edge of the airfoil body, wherein the hybrid trailing edge cavity and the airfoil body are arranged such that a portion of the cooling air flow exits the hybrid trailing edge cavity at the trailing edge of the airfoil body, and characterized in that: a first shielding cavity (614; 714) and a second shielding cavity (616; 716) are located on a pressure side of the airfoil body between a portion of the forward-flowing serpentine flow path and an external pressure side of the airfoil body, wherein the first shielding cavity (614; 714) and the second shielding cavity (616; 716) extend radially through the airfoil body from the root region to the tip region. a first shielding cavity (614; 714) and a second shielding cavity (616; 716) are located on a pressure side of the airfoil body between a portion of the forward-flowing serpentine flow path and an external pressure side of the airfoil body, wherein the first shielding cavity (614; 714) and the second shielding cavity (616; 716) extend radially through the airfoil body from the root region to the tip region.