A static nozzle section including a plurality of stationary nozzles adapted for placement within a flowpath of a turbomachine, each of the stationary nozzles representing a static blade and comprising: an airfoil including: a suction side; a pressure side opposing the suction side; a leading edge between the pressure side and the suction side; a trailing edge opposing the leading edge and between the pressure side and the suction side; a root region at a first radial end; a tip region at a second radial end opposite the first radial end; and a midspan region between the root region and the tip region; and at least one endwall connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein the midspan region includes a reduced axial width relative to an axial width of the root region and an axial width of the tip region, wherein the axial width is the distance along an axis substantially parallel to an axis of rotation of the turbomachine from the leading edge to a point tangentially aligned with the trailing edge of the airfoil, and a blade opening-to-pitch ratio between the airfoil and a neighbouring airfoil of a neighbouring stationary nozzle at the midspan region is greater than the blade opening-to-pitch ratio between the airfoil and neighbouring airfoil at the root region and the tip region to concentrate a fluid flow within the flowpath toward the midspan region of the airfoil compared to the root region and the tip region, the blade opening representing the distance between the airfoil and the neighbouring airfoil at a throat section, and corresponding to the smallest passage distance between the trailing edge of the airfoil and a suction side surface of the neighbouring airfoil, and wherein the midspan region creates an axial width differential between the root region and the tip region that reduces fluid flow profile loss across the midspan region relative to the root region and the tip region, characterized in that a back surface deflection of the suction side surface between the blade opening of the airfoil with the neighbouring airfoil and the trailing edge of the airfoil is significantly less at the midspan region than at the root region or the tip region, wherein the back surface deflection is the angular displacement between a tangential orientation of the suction side surface at the throat section and approximately at the location of the trailing edge. an airfoil including: a suction side; a pressure side opposing the suction side; a leading edge between the pressure side and the suction side; a trailing edge opposing the leading edge and between the pressure side and the suction side; a root region at a first radial end; a tip region at a second radial end opposite the first radial end; and a midspan region between the root region and the tip region; and at least one endwall connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein the midspan region includes a reduced axial width relative to an axial width of the root region and an axial width of the tip region, wherein the axial width is the distance along an axis substantially parallel to an axis of rotation of the turbomachine from the leading edge to a point tangentially aligned with the trailing edge of the airfoil, and a blade opening-to-pitch ratio between the airfoil and a neighbouring airfoil of a neighbouring stationary nozzle at the midspan region is greater than the blade opening-to-pitch ratio between the airfoil and neighbouring airfoil at the root region and the tip region to concentrate a fluid flow within the flowpath toward the midspan region of the airfoil compared to the root region and the tip region, the blade opening representing the distance between the airfoil and the neighbouring airfoil at a throat section, and corresponding to the smallest passage distance between the trailing edge of the airfoil and a suction side surface of the neighbouring airfoil, and wherein the midspan region creates an axial width differential between the root region and the tip region that reduces fluid flow profile loss across the midspan region relative to the root region and the tip region, characterized in that a back surface deflection of the suction side surface between the blade opening of the airfoil with the neighbouring airfoil and the trailing edge of the airfoil is significantly less at the midspan region than at the root region or the tip region, wherein the back surface deflection is the angular displacement between a tangential orientation of the suction side surface at the throat section and approximately at the location of the trailing edge.