Flexible tailored elastic airfoil section

• US 5,181,678 A
• Filed: 02/04/1991
• Issued: 01/26/1993
• Est. Priority Date: 02/04/1991
• Status: Expired due to Fees

• Current Assignee: Flex Logix Technologies, Inc.
• Original Assignee: Flex Logix Technologies, Inc.
• Inventors: Widnall, Sheila E., Widnall, William S., Gorgen, William E., Evernham, Jeffrey T.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/650,472
• Time in Patent Office: 722 Days
• Field of Search: 244/12.5, 244/219, 244/123, 244/213-215, 244/48, 244/76 R, 416/240, 416/24, 416/138 R, 416/138 A, 416/136, 114/127, 114/135, 114/136, 114/142, 114/143, 114/162, 114/39, 114/39.2
• US Class Current: 244/219
• CPC Class Codes: B63B 2039/063 the foils comprising flexible portions
• CPC Class Codes: B64C 3/48 by relatively-movable parts of wing structures
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A flexible airfoil section for a wing or a blade comprising a streamlined shape and an elastic structure whose stiffness distribution along its chord and span is tailored to provide a desirable cambered shape with proportional increases in camber with increases in lift, mounted to a supporting structure such that the airfoil sections are free to pivot about axes near their leading and trailing edges. In operation, the foil derives much of its lift from elastic bending deformation of its flexible shape, thereby achieving a higher lift than a symmetric foil at the same angle of attack while postponing the onset of flow separation and stall and, for operation in water, of ventilation and cavitation. A wing or blade of general planform comprising flexible elastic airfoil sections which can be used to stabilize, or to control the direction of travel of, as well as provide side force for, a watercraft such as a sailboat or a sailboard, or for application to a variety of aircraft components and configurations to provide lift and side force and as well can serve as the aerodynamic surfaces of various types of fluid machinery including fans, helicopter rotors and wind turbines operating in subsonic flow.

Claims

1. A flexible elastic airfoil for generating lift as a result of cambered deflection under load in a moving fluid medium, mounted on a support structure attached to an apparatus operating in contact with a moving fluid medium, said flexible airfoil assembly comprising

a) a flexible elastic airfoil section having a leading edge, a trailing edge, a chord c and an exterior profile of a general continuous streamlined shape such that adjacent points on said exterior surface remain in contact as the airfoil deflects in camber, the airfoil being generally made of flexible materials,

b) means for pivotably mounting the airfoil near its leading edge forming a leading edge pivot axis, said leading edge pivot axis mounting means attached to the support structure, said leading edge pivot axis mounting means constructed and arranged for passive rotation about the pivot axis the leading edge pivot axis being located a distance in the chordwise direction from the leading edge of the airfoil not exceeding 0.25 of the chord c of the airfoil,

c) means for pivotably mounting the airfoil near its trailing edge forming a trailing edge pivot axis, said trailing edge pivot axis mounting means attached to the support structure, said trailing edge pivot axis mounting means constructed and arranged for passive rotation about the pivot axis the trailing edge pivot axis being located a distance in the chordwise direction from the leading edge of the airfoil of at least 0.6 of the chord c of the airfoil, with the distance between the leading edge pivot axis and the trailing edge pivot axis being at least 0.6 c,

d) means to permit the airfoil section to slide in a direction generally aligned with its undeformed centerline to permit proportional cambered deflection of the airfoil under load, the sliding means incorporated into one or both of the pivot axis mounting means.

2. The airfoil of claim 1 wherein the leading edge pivot axis mounting means comprises a leading edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure, with the flexible airfoil incorporating a cavity near its leading edge into which said axle is inserted forming a pivotable mount for the airfoil near its leading edge.

3. The airfoil of claim 2 wherein the sliding means is provided by the flexible airfoil having the cavity at its leading edge into which the leading edge mounting axle is inserted being elongated in a direction generally aligned with the undeformed airfoil centerline such that the airfoil may slide relative to the leading edge mounting axle as it deforms under load.

4. The airfoil of claim 1 wherein the trailing edge pivot axis mounting means comprises a trailing edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure, with the flexible airfoil incorporating a cavity near its trailing edge into which said axle is inserted forming a pivotable mount for the airfoil near its trailing edge.

5. The airfoil of claim 4 wherein the sliding means is provided by the flexible airfoil having the cavity at its trailing edge into which the trailing edge mounting axle is inserted being elongated in a direction generally aligned with the undeformed airfoil centerline such that the airfoil may slide relative to the trailing edge mounting axle as it deforms under load.

6. The airfoil of claim 1, pivotably mounted on the pivot axes mounting means incorporating the sliding means having a deflection response w to a load p per unit span concentrated at a point Q on the surface of the airfoil section midway between the leading and trailing edge pivot axis, said deflection w at the point Q being generally proportional to p for w between zero and the value such that the point Q passes through the undeflected centerline of the airfoil section, the ratio p/w being the section stiffness S_B constructed and arranged to operate in a substantially incompressible fluid of dynamic pressure q, such that 1<

A S_S with 0.09<

A<

0.12.

7. The airfoil of claim 1, pivotably mounted on the pivot axes mounting means incorporating the sliding means having a deflection response w to a load p per unit span concentrated at a point Q on the surface of the airfoil section midway between the leading and trailing edge pivot axis, said deflection w at the point Q being generally proportional to p for w between zero and the value such that the point Q passes through the undeflected centerline of the airfoil section, the ratio p/w being the section stiffness S_s constructed and arranged to operate in a gas at a dynamic pressure q and a Mach number M, such that 9<

A S_s Sqrt (1-M²) with 0.09<

A<

0.12.

8. A flexible elastic wing assembly for generating lift as a result of cambered deflection under load in a moving fluid medium, mounted on a support structure attached to an apparatus operating in contact with a moving fluid medium, said flexible wing assembly comprising

a) a wing of general planform, having a root section, a tip, a span s, an average chord c_ave, and an aspect ratio AR, said wing having flexible, elastic airfoil sections having an exterior profile of a general, continuous streamlined shape such that adjacent points on said exterior surface remain in contact as the wing deflects in camber, the wing being generally made of flexible materials,

b) means for pivotably mounting the wing near its leading edge forming a leading edge pivot axis, said pivot axis aligned generally in the spanwise direction, said leading edge pivot axis mounting means attached to the support structure, said leading edge pivot axis mounting means constructed and arranged for passive rotation about the pivot axis said leading edge pivot axis passing generally through the airfoil sections at points near the leading edge, the portion of the leading edge pivot axis between the root and tip of the wing being located an average distance in the chordwise direction from the leading edge of the wing not exceeding 0.25 of the average chord c_ave of the wing,

c) means for pivotably mounting the wing near its trailing edge forming a trailing edge pivot axis, said pivot axis aligned generally in the spanwise direction, said trailing edge pivot axis mounting means attached to the support structure, said trailing edge pivot axis mounting means constructed and arranged for passive rotation about the pivot axis said trailing edge pivot axis passing generally through the airfoil sections at points near the trailing edge, the portion of the trailing edge pivot axis between the root and tip of the wing being located an average distance in the chordwise direction from the leading edge of the wing of at least 0.6 of the average chord c_ave of the wing, with the average distance between the portion of the leading edge pivot axis between the root and tip of the wing and the portion of the trailing edge pivot axis between the root and tip of the wing having an average distance in the chordwise direction of at least 0.6 c_ave,

d) means to permit the airfoil sections to slide in a direction generally aligned with their undeformed centerlines to permit proportional cambered deflection of the airfoil under load, the sliding means incorporated into one or both of the pivot axis mounting means.

9. The wing of claim 8 wherein the leading edge pivot axis mounting means comprises a leading edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure,

with the flexible wing incorporating a cavity near its leading edge into which said axle is inserted forming a pivotable mount for the wing near its leading edge.

10. The wing of claim 9 wherein the sliding means is provided by the flexible wing having the cavity at its leading edge into which the leading edge mounting axle is inserted being elongated in a direction generally aligned with the undeformed airfoil centerline such that the wing may slide relative to the leading edge mounting axle as it deforms under load.

11. The wing of claim 8 wherein the trailing edge pivot axis mounting means comprises a trailing edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure,

with the flexible wing incorporating a cavity near its trailing edge into which said axle is inserted forming a pivotable mount for the wing near its trailing edge.

12. The wing of claim 11 wherein the sliding means is provided by the flexible wing having the cavity at its trailing edge into which the trailing edge mounting axle is inserted being elongated in a direction generally aligned with the undeformed airfoil centerline such that the wing may slide relative to the trailing edge mounting axle as it deforms under load.

13. The wing of claim 8 wherein the leading edge pivot axis mounting means comprises a rigid axle integral with the wing structure and pivotably mounted to the support structure, said structure incorporating a cavity for containing the axle, said axle inserted into the cavity, the rotation of said axle in the cavity forming the pivot axis,

with the wing being rigid in bending along the leading edge pivot axis in a direction perpendicular to the undeformed airfoil centerline.

14. The wing of claim 13 wherein the sliding means is provided by the support structure having a cavity elongated in a direction generally aligned with the undeformed centerline of the airfoil, into which the leading edge pivot axle is inserted, such that the axle will slide in cavity as the wing deforms.

15. The wing of claim 8 wherein the trailing edge pivot axis mounting means comprises a rigid axle integral with the wing structure and pivotably mounted to the support structure, said structure incorporating a cavity for containing the axle, said axle inserted into the cavity, the rotation of said axle in the caviy forming the pivot axis,

with the wing being rigid in bending along the trailing edge pivot axis in a direction perpendicular to the undeformed airfoil centerline.

16. The wing of claim 15 wherein the sliding means is provided by the support structure having a cavity elongated in a direction generally aligned with the undeformed centerline of the airfoil, into which the trailing edge pivot axle is inserted, such that the axle will slide in cavity as the wing deforms.

17. The wing of claim 8, pivotably mounted on pivot axis mounting means incorporating sliding means having a deflection response w to a load P concentrated in the chordwise direction, and uniformly distributed along the spanwise direction along a line on the wing surface located midway between the leading and trailing edge pivot axis and located between the root and tip of the wing, said deflection w taken at a point Q on the surface of the airfoil section midway between the root and tip of the wing, point Q located on the loaded line on the wing surface, the deflection w being generally proportional to P for w between zero and the value such that the point Q passes through the undeflected centerline of the airfoil section located midway between root and tip, the ratio P/(s w) being the wing stiffness S_w, constructed and arranged to operate in a substantially incompressible fluid of dynamic pressure q, such that q<

A S_w 1/(1-2/AR) with 0.09<

A<

0.12.

18. The wing of claim 8, pivotably mounted on pivot axis mounting means incorporating sliding means having a deflection response w to a load P concentrated in the chordwise direction, and uniformly distributed along the spanwise direction along a line on the wing surface located midway between the leading and trailing edge pivot axis and located between the root and tip of the wing, said deflection w taken at a point Q on the surface of the airfoil section midway between the root and tip of the wing, point Q located on the loaded line on the wing surface, the deflection w being generally proportional to P for w between zero and the value such that the point Q passes through the undeflected centerline of the airfoil section located midway between root and tip, the ratio P/(s w) being the wing stiffness S_w constructed and arranged to operate in a gas at a dynamic pressure q and a Mach number M, such that

19. The wing of claim 8 constructed and arranged to serve as the fin for a sailboard to provide side force, said fin having an aspect ratio greater than 0.65 and being generally made of materials having elastic moduli in the range 100 to 12000 psi.

20. In combination, a sailboard and the wing of claim 8 adapted for use as a fin for said sailboard, the sailboard adapted to incorporate the pivotable means of the wing of claim 8, said sailboard containing at least one cavity for mounting said fin to the sailboard.

21. The wing of claim 8 constructed and arranged to serve as an aerodynamic surface for generating lift.

22. The aerodynamic surface of claim 21 incorporating a control suface for increased control effectiveness,

a means for actuating the control surface.

23. An aircraft adapted to incorporate the wing of claim 8 as an aerodynamic surface,

said aircraft incorporating the attachments for the pivotable mounting means.

24. The wing of claim 8 constructed and arranged for use as an appendage for watercraft to provide sideforce,

said wing being made of generally flexible materials having elastic moduli in the range 100 to 12000 psi.

25. a watercraft incorporating the wing of claim 8, adapted to provide side force,

said wing being made of generally flexible material having elastic moduli in the range 100 to 12000 psi.,

the watercraft adapted for incorporating the wing.

26. A flexible, elastic blade assembly for a rotating device operating in a flow mounted on a rotating hub support structure, said flexible blade assembly comprising

a) a blade of general planform, having a root section, a tip, a span s, an average chord c_ave, and an aspect ratio AR, said blade having flexible, elastic airfoil sections having an exterior profile of a general, continuous streamlined shape such that adjacent points on said exterior surface remain in contact as the blade defects in camber, the blade being generally made of flexible materials,

b) means for pivotably mounting the blade near its leading edge forming a leading edge pivot axis, said pivot axis aligned generally in the spanwise direction, said leading edge pivot axis mounting means attached to the support structure, said leading edge pivot axis mounting means constructed and arranged for passive rotation about the pivot axis said leading edge pivot axis passing generally through the airfoil sections at points near the leading edge, the portion of the leading edge pivot axis between the root and tip of the blade being located an average distance in the chordwise direction from the leading edge of the blade not exceeding 0.25 of the average chord c_ave of the blade

c) means for pivotably mounting the blade near its trailing edge forming a trailing edge pivot axis, said pivot axis aligned generally in the spanwise direction, said trailing edge pivot axis mounting means attached to the support structure, said trailing edge pivot axis mounting means constructed and arranged for passive rotation about the pivot axis said trailing edge pivot axis passing generally through the airfoil sections at points near the trailing edge, the portion of the trailing edge pivot axis between the root and tip of the blade being located an average distance in the chordwise direction from the leading edge of the blade of at least 0.6 of the average chord c_ave of the blade, with the average distance between the portion of the leading edge pivot axis between the root and tip of the blade and the portion of the trailing edge pivot axis between the root and tip of the blade having an average distance in the chordwise direction of at least 0.6 c_ave,

d) means to permit the airfoil sections to slide in a direction generally aligned with their undeformed centerlines to permit proportional cambered deflection of the airfoil under load, the sliding means incorporated into one or both of the pivot axis mounting means.

27. The blade ov claim 26 wherein the blade is flexible over a portion of its span and relatively stiff over the remainder.

28. The blade of claim 26 wherein the leading edge pivot axis mounting means comprises a leading edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure,

with the flexible blade incorporating a cavity near its leading edge into which said axle is inserted forming a pivotable mount for the blade near its leading edge.

29. The blade of claim 28 wherein the sliding means is provided by the flexible blade having the cavity at its leading edge into which the leading edge mounting axle is inserted being elongated in a direction generally aligned with the undeformed airfoil centerline such that the blade may slide relative to the leading edge mounting axle as it deforms under load.

30. The blade of claim 26 wherein the trailing edge pivot axis mounting means comprises a trailing edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure,

with the flexible blade incorporating a cavity near its trailing edge into which said axle is inserted forming a pivotable mount for the blade near its trailing edge.

31. The blade of claim 30 wherein the sliding means is provided by the flexible blade having the cavity at its trailing edge into which the trailing edge mounting axle is inserted being elongated in a direction generally aligned with the undeformed airfoil centerline such that the blade may slide relative to the trailing edge mounting axle as it deforms under load.

32. The blade of claim 28 wherein the leading edge pivot axis mounting means comprises a rigid axle integral with the blade structure and pivotably mounted to the support structure, said structure incorporating a cavity for containing the axle, said axle inserted into the cavity, the rotation of said axle in the cavity forming the pivot axis,

with the blade being rigid in bending along the leading edge pivot axis in a direction perpendicular to the undeformed airfoil centerline.

33. The blade of claim 32 wherein the sliding means is provided by the support structure having a cavity elongated in a direction generally aligned with the undeformed centerline of the airfoil into which the leading edge pivot axle is inserted such that the axle will slide in cavity as the blade deforms.

34. The blade of claim 26 wherein the trailing edge pivot axis mounting means comprises a rigid axle integral with the blade structure and pivotably mounted to the support structure, said structure incorporating a cavity for containing the axle, said axle inserted into the cavity, the rotation of said axle in the cavity forming the pivot axis,

with the blade being rigid in bending along the trailing edge pivot axis in a direction perpendicular to the undeformed airfoil centerline.

35. The blade of claim 34 wherein the sliding means is provided by the support structure having a cavity elongated in a direction generally aligned with the undeformed centerline of the airfoil into which the trailing edge pivot axle is inserted such that the axle will slide in cavity as the blade deforms.

36. The blade of claim 26 wherein the leading edge pivot axis mounting means, the trailing edge pivot axis mounting means and the sliding means are provided by mounting the blade to the support structure, said structure containing a cavity into which the wing is inserted, said blade in its undeflected position bearing against the walls of the cavity at its leading and trailing edge and bearing against the side of the cavity in its fully deflected position, with the leading and trailing edges of the wing being made of relatively stiff material.

37. The blade of claim 26 for a fan, axial wind turbine or a propeller, operating in a gas of density p, axial speed V, rotation speed Ω

and speed of sound a with the airfoil section at the radius r pivotably mounted on pivot axis mounting means incorporating sliding means having flexible airfoil sections, each section having a deflection response W to a load p per unit span concentrated in the chordwise direction midway between the leading and trailing edge pivot axis, said deflection w taken at a point Q on the surface of the airfoil section, at the point of load application on the blade surface, the deflection w being generally proportional to p for w between zero and a value such that the point Q passes through the undeflected centerline of the airfoil section located midway between root and tip, the ratio p/w being the local section stiffness S_s (r), r being the radial coordinate of the section, such that

space="preserve" listing-type="equation">1/2ρ

(V.sup.2 +Ω

.sup.2 r.sup.2)<

A S.sub.s (r) Sqrt(1-(V.sup.2 +Ω

.sup.2 r.sup.2)/a.sup.2)/(1-2/AR)

with 0.09<

A<

0.12.

38. The blade of claim 26 for a fan, or a propeller, operating in a fluid of density ρ

, axial speed V, and rotation speed Ω

with the airfoil section at the radius R pivotably mounted on pivot axis mounting means incorporating sliding means having flexible airfoil sections, each section having a deflection response W to a load p per unit span concentrated in the chordwise direction midway between the leading and trailing edge pivot axis, said deflection w taken at a point Q on the surface of the airfoil section, at the point of load application on the blade surface, the deflection w being generally proportional to p for w between zero and a value such that the point Q passes through the undeflected centerline of the airfoil section located midway between root and tip, the ratio p/w being the local section stiffness (S_s (r), r being the radial coordinate of the section, such that 1/2ρ

(V² +Ω

² r²)<

A S_sl (r) 1/(1-2/AR)

with 0.09<

A<

0.12.

39. The blade of claim 26 for a helicopter rotor operating in air of density ρ

, forward wpeed V, rotation speed Ω and

speed of sound a with the airfoil section at the radius r having a section stiffness S_s)r) such that

space="preserve" listing-type="equation">1/2ρ

(V+Ω

r).sup.2 <

A S.sub.s (r) Sqrt(1-((V+Ω

r)/a).sup.2)/(1-2/AR)

with 0.09<

A<

0.12.

40. An elastic articulated airfoil for generating lift as a result of deflection under load in a moving fluid medium, mounted on a support structure attached to an apparatus operating in contact with a moving fluid medium, said airfoil assembly comprising

a) a plurality of sections joined together to form an articulate airfoil section of a general streamlined shape,

b) an axis disposed between eac neighboring pair of sections as a means of attaching them together and permitting rotation about said axis,

c) means for pivotably mounting the airfoil at an axis near its leading edge forming a leading edge pivot axis, said leading edge pivot axis mounting means attached to the support structure, said trailing edge pivot axis mounting means constructed and arranged for passive rotation about the pivot axis the leading edge pivot axis being locatd a distance in the chordwise direction from the leading edge of the airfoil not exceeding 0.25 of the chord c of the airfoil,

d) means for pivotably mounting the airfoil at an axis near its trailing edge forming a trailing edge pivot axis, said trailing edge pivot axis mounting means attached to the support structure, pivotably mounted on the pivot axes mounting means incorporating the sliding means having a deflection response w to a load p per unit span concentrated at a point Q on the surface of the airfoil section midway between the leading and trailing edge pivot axis, said deflection w at the point Q being generally proportional to p for w between zero and a value such that the point Q passes through the undeflected centerline of the airfoil section, the ratio p/w being the section stiffness S_s the trailing edge pivot axis being located a distance in the chordwise direction from the leading edge of the airfoil of at least 0.6 of the chord c of the airfoil, with the distance between the leading edge pivot axis and the trailing edge pivot axis being at least 0.6 c,

e) the axes constituting rotation points for the airfoil sections in relation to one another and to the pivot axes mounting means,

f) means to permit the airfoil section to slide in a direction generally aligned with its undeformed centerline to permit proportional cambered deflection of the airfoil under load, the sliding means incorporated into at least one of the axes,

g) at least one torsion spring located at said axes disposed between the two relatively rotating elements.

41. The airfoil of claim 40 wherein the leading edge pivot axis mounting means comprises a leading edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure,

with the airfoil incorporating a cavity near its leading edge into which said axle is inserted forming a pivotable mount for the airfoil near its leading edge.

42. The airfoil of claim 41 wherein the sliding means is provided by the airfoil having the cavity at its leading edge into which the leading edge mounting axle is inserted being elongated in a direction generally aligned with the undeflected airfoil centerline such that the airfoil may slide relative to the leading edge mounting axle as it deflects under load.

43. The airfoil of claim 40 wherein the trailing edge pivot axis mounting means comprises a trailing edge mounting axle, rigid in bending in the direction perpendicular to the undeflected airfoil centerline, mounted to the support structure,

with the airfoil incorporating a cavity near its trailing edge into which said axle is inserted forming a pivotable mount for the airfoil near its trailing edge.

44. The airfoil of claim 43 wherein the sliding means is provided by the airfoil having the cavity at its trailing edge into which the trailing edge mounting axle is inserted being elongate in a direction generally aligned with the undeflected airfoil centerline such that the airfoil may slide relative to the trailing edge mounting axle as it deforms under load.

45. The airfoil of claim 40 where at least one of the airfoil sections is rigid.

46. The airfoil of claim 40 where at least one of the airfoil sections is flexible.

47. The airfoil of claim 40, pivotably mounted on the pivot axes mounting means incorporating the sliding means having a deflection response w to a load p per unit span concentrated at a point Q on the surface of the airfoil section midway between the leading and trailing edge pivot axis, said deflection w at the point Q being generally proportional to p for w between zero and a value such that the point Q passes through the undeflected centerline of the airfoil section, the ratio p/w being the section stiffness S_s operating in a fluid of dynamic pressure q such that q<

A S_s with 0.09<

A<

0.12.

48. The airfoil of claim 40, pivotably mounted on the pivot axes mounting means incorporating the sliding means having a deflection response w to a load p per unit span concentrated at a point Q on the surface of the airfoil section midway between the leading and trailing edge pivot axis, said deflection w at the point Q being generally proportional to p for w between zero and a value such that the point Q passes through the undeflected centerline of the airfoil section, the ratio p/w being the section stiffness S_s operating in a gas at a dynamic pressure q and a Mach number M such that q<

A S_s Sqrt (1-M²) with 0.09<

A<

0.12.

49. A flexible elastic wing assembly for generating lift as a result of cambered deflection under load in a moving fluid medium, mounted on a support structure attached to an apparatus operating in contact with a moving fluid medium, said flexible wing assembly comprising:

a) a wing of general planform, having a root section, a tip, a span s, an average chord c_ave, and an aspect ratio AR, said wing having flexible, elastic airfoil sections having an exterior profile of a general, continuous streamlined shape such that adjacent points on said exterior surface remain in contact as the wing deflects in camber, the wing being generally made of flexible materials,

b) means for pivotably mounting the wing near its leading edge forming a leading edge pivot axis, said pivot axis aligned generally in the spanwise direction, said leading edge pivot axis mounting means attached to the support structure, said leading edge pivot axis passing generally through the airfoil sections at points near the leading edge, the portion of the leading edge pivot axis between the root and tip of the wing being located an average distance is the chordwise direction from the leading edge of the wing not exceeding 0.25 of the average chord c_ave of the wing,

c) means for pivotably mounting the wing near its trailing edge forming a trailing edge pivot axis, said pivot axis aligned generally in the spanwise direction, said trailing edge pivot axis mounting means attached to the support structure, said trailing edge pivot axis passing generally through the airfoil sections at points near the trailing edge, the portion of the trailing edge pivot axis between the root and tip of the wing being located an average distance in the chordwise direction from the leading edge of the wing of at least 0.6 of the average chord c_ave of the wing, with the average distance between the portion of the leading edge pivot axis between the root and tip of the wing and the portion of the trailing edge pivot axis between the root and tip of the wing having an average distance in the chordwise direction of at least 0.6 c_ave,

d) means to permit the airfoil sections to slide in a direction generally aligned with their undeformed centerlines to permit proportional cambered deflection of the airfoil under load, the sliding means incorporated into one or both of the pivot axis mounting means,

e) said leading edge pivot axis mounting means, the trailing edge pivot axis mounting means and the sliding means provided by mounting the wing to the support structure, said structure containing a cavity into which the wing is inserted, said wing in its undeflected position bearing against the walls of the cavity at its leading and trailing edge and bearing against the side of the cavity in its fully deflected position, with the leading and trailing edges of the wing being made of relatively stiff material.

f) said flexible, elastic wing pivotably mounted on pivot axis mounting means incorporating sliding means having a deflection response w to a load P concentrated in the chordwise direction, and uniformly distributed along the spanwise direction along a line on the wing surface located midway between the leading and trailing edge pivot axis and located between the root and tip of the wing, said deflection w taken at a point Q on the surface of the airfoil section midway between the root and tip of the wing, point Q located on the loaded line on the wing surface, the deflection w being generally proportional to P for w between zero and the value such that the point Q passes through the undeflected centerline of the airfoil section located midway between root and tip, the ratio P/(s w) being the wing stiffness S_w.

50. A flexible elastic airfoil for generating lift as a result of cambered deflection under load in a moving fluid medium, mounted on a support structure attached to an apparatus operating in contact with a moving fluid medium, said flexible airfoil assembly comprising

a) a flexible, elastic airfoil section having a leading edge, a trailing edge, a chord c and an exterior profile of a general continuous streamlined shape such that adjacent points on said exterior surface remain in contact as the airfoil deflects in camber, the airfoil being generally made of flexible materials,

b) means for freely pivotably mounting the airfoil near its leading edge forming a leading edge pivot axis for allowing free pivotable action, said leading edge pivot axis mounting means attached to the support structure, the leading edge pivot axis being located a distance in the chordwise direction from the leading edge of the airfoil not exceeding 0.25 of the chord c of the airfoil,

c) means for freely pivotably mounting the airfoil near its trailing edge forming a trailing edge pivot axis for allowing free pivotable action, said trailing edge pivot axis mounting means attached to the support structure, the trailing edge pivot axis being located a distance in the chordwise direction from the leading edge of the airfoil of at least 0.6 of the chord c of the airfoil, with the distance between the leading edge pivot axis and the trailing edge pivot axis being at least 0.6 c,

d) means to permit the airfoil section to slide in a direction generally aligned with its undeformed centerline to permit proportional cambered deflection of the airfoil under load, the sliding means incorporated into one or both of the pivot axis mounting means.