Lifting body with reduced-strength trailing vortices

Claim 2

In a predetermined lifting body for moving relative to a fluid medium, the relative motion being in an x-direction defined as the direction of a velocity vector of the fluid medium relative to said lifting body upstream thereof, wherein said lifting body has a predetermined planform with a chord length in the x-direction, said chord length being defined as a predetermined function c(y) that provides a predetermined lift distribution in a y-direction normal to the x-direction to create in the fluid medium a vortex field having a predetermined total vorticity at any given location downstream of said lifting body, wherein such total vorticity is represented by an equivalent vortex with a center at a centroid of the vortex field and a radius in a plane normal to the x-direction, the equivalent vortex having the same total vorticity as the vortex field at the same given location and the radius having a rate of growth in the x-direction depending on a fluid velocity component of the equivalent vortex directed outwardly from the centroid of the vortex field, the improvement comprising: a perturbation in said lifting body that changes the periphery of said predetermined planform to vary c(y) only in a region of said lifting body and thereby alter said predetermined lift distribution to enhance the fluid velocity component of the equivalent vortex directed outwardly from the centroid of the vortex field and increase the rate of growth of the radius of the equivalent vortex in the x-direction.

Claim 3

A lifting body according to claim 1, wherein said lifting body is a control surface.

Claim 4

A lifting body according to claim 2, wherein said control surface is a submarine control surface.

Claim 5

A lifting body according to claim 2, wherein said control surface is an aircraft control surface.

Claim 6

A lifting body according to claim 1, wherein said lifting body has a root end for attachment to a supporting body and a tip end for extending into the fluid medium and said perturbation is disposed at a trailing edge of said tip end of said lifting body.

Claim 7

A lifting body according to claim 5, wherein said lifting body is a airfoil and said perturbation is a damped sine wave having the formula P=a o e -d .sbsp.o z .spsp.'2 sin kz' wherein z' is a distance measured along a coordinate axis formed by the outline of said planform without said perturbation, z'=0 being defined as the start of said perturbation along said outline, P is the distance along an axis perpendicular to the z' axis, and a o , d o and k are factors chosen to provide said predetermined lift distribution.

Claim 8

A lifting body according to claim 1, wherein said lifting body selected from the group consisting of a helicopter rotor, a ship propellor blade, a fan blade, an aircraft propellor blade and a compressor blade.

Claim 9

A lifting body according to claim 1, wherein the total lift generated by said predetermined planform with said perturbation is substantially the same as the total lift generated by said predetermined planform without said perturbation.

Claim 10

A lifting body according to claim 1, wherein said perturbation is disposed at a leading edge of said lifting body.

Claim 11

A lifting body according to claim 9, wherein said lifting body has a double-delta planform with at least two delta wing portions intersecting at a leading edge of said lifting body and said perturbation is disposed at said intersection of said two delta wing portions.

Claim 12

A lifting body according to claim 1, wherein said perturbation is disposed in a tip region of said lifting body.

Claim 13

A lifting body according to claim 1, wherein said lifting body is an aircraft wing.

Claim 14

A lifting body according to claim 1, wherein said lifting body is an aircraft flap and said perturbation is provided at two tip ends of said flap.

Claim 15

A lifting body according to claim 1, wherein said lifting body is a submarine sail.

Claim 16

In a predetermined lifting body for moving relative to a fluid medium, the relative motion being in an x-direction defined as the direction of a velocity vector of the fluid medium relative to said lifting body upstream thereof, wherein said lifting body and a velocity vector of the fluid medium form a predetermined angle of attack α between a chord of said lifting body and a velocity vector of the fluid medium in the x-direction, said angle of attack being defined as a predetermined function α(y) that provides a predetermined lift distribution in a y-direction normal to the x-direction to create in the fluid medium a vortex field having a predetermined total vorticity at any given location downstream of said lifting body, wherein such total vorticity is represented by an equivalent vortex with a center at a centroid of the vortex field and a radius in a plane normal to the x-direction, the equivalent vortex having the same total vorticity as the vortex filed at the same given location and the radius having a rate of growth in the x-direction depending on a fluid velocity component of the equivalent vortex directed outwardly from the centroid of the vortex field, the improvement comprising: a twist in said lifting body that changes said predetermined angle of attack to vary α(y) only in a region of said lifting body and thereby alter said predetermined lift distribution to enhance the fluid velocity component of the equivalent vortex directed outwardly from the centroid of the vortex field and increase the rate of growth of the radius of the equivalent vortex in the x-direction.

Claim 17

In a predetermined lifting body for moving relative to a fluid medium, the relative motion being in an x-direction defined as the direction of a velocity vector of the fluid medium relative to said lifting body upstream thereof, wherein said lifting body and a velocity vector of the fluid medium form a predetermined angle of attack α between a chord of said lifting body and a velocity vector of the fluid medium in the x-direction, said angle of attack being defined as a predetermined function α(y) that provides a predetermined lift distribution in a y-direction normal to the x-direction to create in the fluid medium a vortex field having a predetermined total vorticity at any given location downstream of said lifting body, wherein such total vorticity is represented by an equivalent vortex with a center at a centroid of the vortex field and a radius in a plane normal to the x-direction, the equivalent vortex having the same total vorticity as the vortex filed at the same given location and the radius having a rate of growth in the x-direction depending on a fluid velocity component of the equivalent vortex directed outwardly from the centroid of the vortex field, the improvement comprising: a twist in said lifting body that changes said predetermined angle of attack to vary α(y) only in a region of said lifting body and thereby alter said predetermined lift distribution to enhance the fluid velocity component of the equivalent vortex directed outwardly from the centroid of the vortex field and increase the rate of growth of the radius of the equivalent vortex in the x-direction.

Claim 18

A lifting body according to claim 15, wherein said lifting body has a root end for attachment to a supporting body and a tip end for extending into the fluid medium.

Claim 19

A lifting body according to claim 15, wherein the total lift generated by said predetermined lifting body with said twist is substantially the same as the total lift generated by said predetermined lifting body without said twist.

Claim 20

A lifting body according to claim 15, wherein said lifting body is an aircraft wing.

Claim 21

A lifting body according to claim 15, wherein said lifting body is selected from the group consisting of a helicopter rotor, a ship propeller blade, a fan blade, an aircraft propeller blade and a compressor blade.