Unducted airfoil assembly
An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.
1. An unducted airfoil assembly, comprising:
an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges, and wherein the airfoil comprises a forward-most axial point located between the root and the tip, and wherein the airfoil defines a tip portion extending radially from the forward-most axial point to the tip; and
wherein a thickness of the airfoil is defined as a distance measured between the pressure side and the suction side, and wherein a maximum thickness for at least 50% of a radial extent of the tip portion for a chord extending from the leading edge to the trailing edge is located forward of 0.40 chord fraction.
2. The unducted airfoil assembly of claim 1 , wherein the airfoil is arranged about a longitudinal axis and rotates about the longitudinal axis in a rotational direction, and wherein the leading edge in the tip portion leans in a direction opposite the rotational direction.
3. The unducted airfoil assembly of claim 1 , wherein a thickness ratio of an airfoil section is defined as the thickness of the airfoil section divided by a maximum thickness of the airfoil section, and wherein the thickness ratio of any airfoil section in the tip portion is 0.8 or greater at 0.05 chord fraction.
4. The unducted airfoil assembly of claim 1 , wherein circumferential coordinates of the leading edge monotonically increase, in a radial direction, relative to a circumferential coordinate of the forward-most axial point of the leading edge in a direction away from a rotational direction of the airfoil for at least a sub-portion of the tip portion beyond a tip radius value of the forward-most axial point.
5. The unducted airfoil assembly of claim 1 , wherein the trailing edge comprises a sculpted trailing edge feature.
6. The unducted airfoil assembly of claim 1 , wherein the maximum thickness for at least a portion of the airfoil in the tip portion is located forward of a 0.25 chord fraction as measured from the leading edge.
7. The unducted airfoil assembly of claim 1 , wherein the airfoil comprises a guide vane.