Winglet for a wind turbine rotor blade

1. A winglet for a rotor blade, comprising:

a winglet body extending at least partially between a winglet origin and a blade tip and including a plurality of radial locations between the winglet origin and the blade tip, the winglet body defining a sweep at each of the plurality of radial locations generally in accordance with the values for sweep shown in TABLE 1,

wherein the winglet body further defines a cant angle, the cant angle at the blade tip ranging from 60 degrees to 130 degrees, and

wherein each of the values for sweep shown in TABLE 1 is variable within a tolerance range of +/−10%.

2. The winglet of claim 1 , wherein the cant angle at a given radial location along the winglet body is defined as an angle measured in a local Y-Z plane of the winglet body between a reference line extending parallel to a local Z-axis for the winglet body and a reference line extending tangent to a blade reference line for the rotor blade at the given radial location.

3. The winglet of claim 1 , wherein the cant angle at the blade tip ranges from 70 degrees to 100 degrees.

4. The winglet of claim 1 , wherein the winglet body further defines a chord, the chord at the winglet origin ranging from 1.2% to 2.6% of the span of the rotor blade.

5. The winglet of claim 1 , wherein the winglet body further defines a chord, the chord at the blade tip ranging from 0.0% to 0.5% of the span of the rotor blade.

6. The winglet of claim 1 , wherein the winglet body further defines a spanwise radius, the spanwise radius defined between the winglet origin and the blade tip ranging from 2.4% to 4% of the span of the rotor blade.

7. The winglet of claim 1 , wherein the winglet body further defines a twist angle, the twist angle at the winglet origin ranging from −4.6 degrees to 1.4 degrees.

8. The winglet of claim 1 , wherein the winglet body further defines a twist angle, the twist angle at the blade tip ranging from −4.0 degrees to 2.0 degrees.

9. The winglet of claim 1 , wherein the winglet body further defines a pre-bend between the winglet origin and the blade tip that ranges from 1.5% to 4.5% of the span of the rotor blade.

10. A winglet for a rotor blade, comprising:

a winglet body extending at least partially between a winglet origin and a blade tip and including a plurality of radial locations between the winglet origin and the blade tip, the winglet body defining a sweep and a cant angle, the cant angle at a given radial location along the winglet body being defined as an angle measured in a local Y-Z plane of the winglet body between a reference line extending parallel to a local Z-axis for the winglet body and a reference line extending tangent to a blade reference line for the rotor blade at the given radial location, the cant angle being defined at each of the plurality of radial locations generally in accordance with the values for cant angle shown in TABLE 1,

wherein the sweep defined between the winglet origin and the blade tip ranges from 1.7% to 2.8% of a span of the rotor blade, and

wherein each of the values for cant angle shown in TABLE 1 is variable within a tolerance range of +/−20 degrees.

11. The winglet of claim 10 , wherein the winglet body further defines a chord at the blade tip ranging from 0.0% to 0.5% of a span of the rotor blade and a chord at the winglet origin ranging from 1.2% to 2.6% of a span of the rotor blade.

12. A rotor blade for a wind turbine, the rotor blade comprising:

a blade body extending from a blade root towards a blade tip; and

a winglet body extending between a winglet origin defined at an interface between the blade body and the winglet body and a tip end defined at the blade tip, the winglet body including a plurality of radial locations between the winglet origin and the blade tip, the winglet body defining a sweep and a pre-bend, the pre-bend being defined at each of the plurality of radial locations generally in accordance with the values for pre-bend shown in TABLE 1,

wherein the sweep defined between the winglet origin and the blade tip ranges from 1.7% to 2.8% of a span of the rotor blade, and

wherein each of the values for pre-bend shown in TABLE 1 is variable within a tolerance range of +/−10%.

13. The rotor blade of claim 12 , wherein the winglet body further defines a cant angle, the cant angle at the blade tip ranging from 60 degrees to 130 degrees, the cant angle at a given radial location along the winglet body is defined as an angle measured in a local Y-Z plane of the winglet body between a reference line extending parallel to a local Z-axis for the winglet body and a reference line extending tangent to a blade reference line for the rotor blade at the given radial location.

14. The rotor blade of claim 13 , wherein the cant angle at the blade tip ranges from 70 degrees to 100 degrees.

15. The rotor blade of claim 12 , wherein the winglet body further defines a chord, the chord at the winglet origin ranging from 1.2% to 2.6% of the span of the rotor blade.

16. The rotor blade of claim 12 , wherein the winglet body further defines a chord, the chord at the blade tip ranging from 0.0% to 0.5% of the span of the rotor blade.

17. The rotor blade of claim 12 , wherein the winglet body further defines a spanwise radius, the spanwise radius defined between the winglet origin and the blade tip ranging from 2.4% to 4% of the span of the rotor blade.

18. The rotor blade of claim 12 , wherein the winglet body further defines a twist angle, the twist angle at the winglet origin ranging from −4.6 degrees to 1.4 degrees.

19. The rotor blade of claim 12 , wherein the winglet body further defines a twist angle, the twist angle at the blade tip ranging from −4.0 degrees to 2.0 degrees.