Airfoil for a compressor of a turbomachine

1. An airfoil for a compressor of a turbomachine, which extends starting from a blade root between a leading edge and a trailing edge to a blade tip,

wherein the leading edge has a leading-edge thickness and the airfoil has a maximum profile thickness, the ratio of the leading-edge thickness to the maximum profile thickness represents a relative leading-edge thickness, and the airfoil has a leading-edge wedge angle,

wherein a product of the relative leading-edge thickness and a leading-edge wedge angle value, in at least one cross-section of the airfoil, forms a leading-edge ratio parameter, the value of which is between 5.5 and 10.0.

2. The airfoil according to claim 1 , wherein the at least one cross-section of the airfoil lies in a region in which the relative airfoil height is at least 20% of the total airfoil height.

3. The airfoil according to claim 1 , wherein the value of the leading-edge ratio parameter, in at least one cross-section of the airfoil, is greater than 7.

4. The airfoil according to claim 1 , wherein the at least one cross-section of the leading edge lies in a region in which the relative airfoil height is at least 40% of the total airfoil height.

5. The airfoil according to claim 1 , wherein the leading-edge thickness has a value of 0.2 mm to 5 mm.

6. The airfoil according to claim 1 , wherein the leading-edge wedge angle value has a value of 2° to 45°.

7. A compressor for a turbomachine, comprising at least one airfoil according to claim 1 .

8. A turbomachine with a compressor, wherein the compressor is configured and arranged with at least one airfoil according to claim 1 .