High-lift, low-drag, stall-resistant airfoil

• US 6,732,972 B2
• Filed: 02/21/2003
• Issued: 05/11/2004
• Est. Priority Date: 09/13/2002
• Status: Expired due to Fees

• Current Assignee: John R. Hanscomb
• Original Assignee: Frank S. Malvestuto Jr
• Inventors: Malvestuto, Frank S. Jr.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US10/370,740
• Publication Number:
  US 20040065772A1
• Time in Patent Office: 445 Days
• Field of Search: 244/12.1, 244/12.3, 244/12.4, 244/12.5, 244/23.B, 244/23.D, 244/207, 244/204, 244/205, 244/55, 244/56, 244/66, 244/65, 244/6, 244/7.R
• US Class Current: 244/12.3
• CPC Class Codes: B64C 21/04 for blowing
• CPC Class Codes: B64C 23/08 using Magnus effect
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

Method and apparatuse embodiments of the present invention are diclosed wherein wing-rotor configurations provide aerodynamically high lift-low drag capabilities and improvements over the prior art including increasing effective stall angles. In addition, wing-rotor-propeller configurations provide aerodynamically high lift-low drag and forward thrust capabilities and improvements over the prior art for all vehicles moving through gaseous fluids and particular including application for air vehicles and watercraft. Also, wing leading edge air blowing systems augment the example configurations for enhanced performance including substantially vertical take-off and landing of air vehicles.

Claims

1. An airfoil-rotor apparatus comprising:

a first wing having a leading edge, a trailing edge and a plane of the first wing interposed between a top side and a bottom side of the first wing wherein, in the plane of the first wing, the first wing has at least one arcuate recess having a chord co-linear with the trailing edge of the first wing; and

at least one rotor having a plurality blades, a center of planar rotation and an angle of planar rotation incline relative to the plane of the first wing wherein each of the plurality of blades has a pitch angle and a tip distal from the center of planar rotation and wherein the at least one rotor is positioned so that rotations of the plurality of blades about the center of planar rotation cause the rotor blade tips turning in an air flow to pass proximate to the at least one arcuate recess forward of the trailing edge of the first wing and wherein the center of planar rotation is aft of the chord co-linear with the trailing edge of the first wing.

2. The airfoil-rotor apparatus as claimed in claim 1 wherein the angle of planar rotation incline relative to the plane of the first wing is adjustable in a plane perpendicular to the plane of the first wing.

3. The airfoil-rotor apparatus as claimed in claim 1 wherein an angle is subtended by the at least one arcuate recess relative to a center or planar rotation of an associated at least one rotor and said angle is substantially less than 180 degrees.

4. The airfoil-rotor apparatus as claimed in claim 1 wherein at least one arcuate recess of the first wing has a vertical section having upper and lower boundaries and wherein rotations of the plurality of blades of the at least one rotor cause the rotor blade tips turning in air flow to pass within the upper and lower boundaries of the vertical section.

5. The airfoil-rotor apparatus as claimed in claim 4 wherein an adjustable angle of planar rotation incline relative to the plane of the first wing is constrained so that rotations of the plurality of blades of the at least one rotor cause the plurality of rotor blade tips turning in air flow to pass between the upper and lower boundaries of the vertical section.

6. The airfoil-rotor apparatus as claimed in claim 1 wherein the pitch of each rotor blade is adjustable.

7. The airfoil-rotor apparatus as claimed in claim 1 wherein the rotor further comprises a shaft wherein a motor linked to the shaft rotationally drives the rotor.

8. The airfoil-rotor apparatus as claimed in claim 1 wherein the motor driving the rotor shaft is disengages in the event of power failure.

9. The airfoil-rotor apparatus as claimed in claim 1 wherein the rotor tips have inverse tapers.

10. The airfoil-rotor apparatus as claimed in claim 9 wherein the rotor tips are swept.

11. The airfoil-rotor apparatus as claimed in claim 1 further comprising an air-blowing means substantially contained within the first wing, wherein the first wing has a top side vent proximate to the first wing and a bottom side vent proximate to the first wing leading edge wherein the air-blowing means blows air aft over the top side of the first wing and aft over the bottom side of the first wing.

12. The airfoil-rotor apparatus of claim 1 further comprising:

a second wing having a leading edge, a tailizg edge and a plane of the second wing interposed between a top side and a bottom side of the second wing;

a propeller having a plurality of blades, each of the plurality of blades having a tip, the propeller having a center of rotation and being substantially perpendicular with and interposing between the first wing and the second wing wherein each of the tips of the propeller, when rotating about a propeller center of rotation, pass in close proximately to the leading edge of the first wing and in close proximately to the trailing edge of the second wing.

13. The airfoil-rotor apparatus of claim 12 further comprising a propeller motor rotationally driving the propeller.

14. The airfoil-rotor apparatus of claim 12 further comprising mechanical linkage between the rotor drive shaft and the propeller motor.

15. An aircraft airfoil assembly comprising:

a first wing having a first starboard wing portion and a first port wing portion, the first wing having a leading edge, a trailing edge and a plane of the first wing interposed between a top side and a bottom side of the first wing, wherein, in the plane of the first wing the first wing has at least one starboard arcuate recess and at least one port arcuate recess each arcuate recess having a chord co-linear with the trailing edge of the first wing; and

at least one starboard rotor and at least one port rotor, each rotor having a plurality blades, a center of planar rotation and an angle of planar rotation incline relative to the plane of the first wing wherein each of the plurality of blades has a pitch angle and a tip distal from the center of planar rotation and wherein rotations of the plurality of blades of the at least one starboard rotor cause the starboard rotor blade tips turning in an air flow to pass proximate to the at least one starboard arcuate recess of the first wing and wherein rotations of the plurality of blades of the at least one port rotor cause the port rotor blade tips turning in the air flow to pass proximate to the at least one port arcuate recess of the first wing and wherein the center of planar rotation of the starboard rotor and the center of planar rotation of the port rotor are aft of the respective chord co-linear with the trailing edge of the first wing.

16. The aircraft airfoil assembly as claimed in claim 15 wherein for each rotor, each of the angles of planar rotation incline relative to the plane of the first wing are adjustable in a plane perpendicular to the plane of the first wing.

17. The airfoil-rotor assembly as claimed in claim 15 wherein for each arcuate recess an angle is subtended by each arcuate recess relative to a center of planar rotation of an associated rotor and said angle is substantially less than 180 degrees.

18. The aircraft airfoil assembly as claimed in claim 15 wherein the at least one starboard arcuate recess and the at least one starboard arcuate recess of the first wing each have a vertical section having upper and lower boundaries and wherein rotations of the plurality of blades of the at least one starboard rotor and of the at least one port rotor cause the rotor blade tips turning in air flow to pass within the upper and lower boundaries of each of the vertical sections.

19. The aircraft airfoil assembly as claimed in claim 18 wherein an adjustable angle of planar rotation incline relative to the plane of the first wing is constrained so that rotations of the plurality of blades of the at least one starboard rotor and of the plurality of blades of the at least one port rotor cause the plurality of rotor blade tips turning in air flow to pass between the upper and lower boundaries of each of the vertical sections.

20. The aircraft airfoil assembly as claimed in claim 15 further comprising:

a second wing having a leading edge, a trailing edge and a plane of the second wing interposed between a top side and a bottom side of the second wing;

at least one starboard propeller and at least one port propeller, each propeller having a plurality of blades, each of the plurality of blades having a tip, the at least one starboard propeller and the at least one port propeller each having a center of rotation and a plane of rotation, each plane of rotation being substantially perpendicular with and interposing between the first wing and the second wing wherein each of the tips of the starboard propeller, when rotating about at least one starboard propeller center of rotation, and each of the tips of the port propeller, when rotating about the at least one port propeller center of rotation, pass in close proximately to the leading edge of the first wing and in close proximately to the trailing edge of the second wing.

21. The aircraft airfoil assembly as claimed in claim 15 further comprising at least one starboard propeller motor rotationally driving the at least one starboard propeller and at least one port propeller motor rotationally driving the at least one port propeller.

22. The aircraft airfoil assembly as claimed in claim 15 further comprising mechanical linkage between the at least one starboard rotor drive shaft and at least one starboard propeller motor and mechanical linkage between the at least one port rotor drive shaft and at least one port propeller motor.

23. The aircraft airfoil assembly as claimed in claim 15 wherein the pitch of each propeller blade is adjustable.

24. The aircraft airfoil assembly as claimed in claim 15 further comprising a starboard air-blowing means and a port air-blowing means, each air-blowing means being substantially contained within the first wing, wherein the first wing has a starboard top side vent proximate to the first wing and a starboard bottom side vent proximate to the first wing leading edge and a port top side vent proximate to the first wing and a port bottom side vent proximate to the first wing leading edge wherein the starboard air-blowing means and port air-blowing means each blow air aft over the top side of the first wing and aft over the bottom side of the first wing.

25. A watercraft airfoil assembly comprising:

a first wing having a leading edge, a trailing edge and a plane of the first wing interposed between a top side and a bottom side of the first wing wherein, in the plane of the first wing, the first wing has at least one arcuate recess having a chord co-linear with the trailing edge of the first wing; and

at least one rotor having a plurality blades, a center of planar rotation and an angle of planar rotation incline relative to the plane of the first wing wherein each of the plurality of blades has a pitch angle and a tip distal from the center of planar rotation and wherein rotations of the plurality of blades of the at least one rotor cause the rotor blade tips turning in an air flow to pass proximate to the at least one arcuate recess of the first wing and wherein the center of planar rotation is aft of the chord co-linear with the trailing edge of the first wing.

26. The watercraft airfoil assembly as claimed in claim 25 wherein the angle of planar rotation incline relative to the plane of the first wing is adjustable in a plane perpendicular to the plane of the first wing.

27. The watercraft airfoil assembly as claimed in claim 25 wherein for each arcuate recess an angle is subtended by each arcuate recess relative to a center of planar rotation of an associated rotor and said angle is substantially less than 180 degrees.

28. The watercraft airfoil assembly as claimed in claim 25 wherein at least one arcuate recess of the first wing has a vertical section having upper and lower boundaries and wherein rotations of the plurality of blades of the at least one rotor cause the rotor blade tips turning in air flow to pass within the upper and lower boundaries of the vertical section.

29. The watercraft airfoil assembly as claimed in claim 28 wherein an adjustable angle of planar rotation incline relative to the plane of the first wing is constrained so that rotations of the plurality of blades of the at least one rotor cause the plurality of rotor blade tips turning in air flow to pass between the upper and lower boundaries of the vertical section.

30. The watercraft airfoil assembly as claimed in claim 25 wherein the pitch of each rotor blade is adjustable.

31. The watercraft airfoil assembly as claimed in claim 25 wherein the rotor further comprises a shaft wherein a motor linked to the shaft rotationally drives the rotor.

32. The watercraft airfoil assembly as claimed in claim 25 wherein the motor driving the rotor shaft disengages in the event of power failure.

33. The watercraft airfoil assembly as claimed in claim 25 wherein the rotor tips have inverse tapers.

34. The watercraft airfoil assembly as claimed in claim 25 wherein the rotor tips are swept.

35. The watercraft airfoil assembly as claimed in claim 25 wherein the watercraft airfoil assembly is mounted on the aft portion of a watercraft.

36. The watercraft airfoil assembly as claimed in claim 25 further comprising an air-blowing means substantially contained within the first wing, wherein the first wing has a top side vent proximate to the first wing and a bottom side vent proximate to the first wing leading edge wherein the air-blowing means blows air aft over the top side of the first wing and aft over the bottom side of the first wing.

37. The watercraft airfoil assembly as claimed in claim 25 further comprising:

a second wing having a leading edge, a trailing edge and a plane of the second wing interposed between a top side and a bottom side of the second wing, wherein the bottom side of the second wing proximate to the leading edge is substantially conformal to the aft topside of a watercraft;

at least one propeller, each propeller having a plurality of blades, each of the plurality of blades having a tip, the at least one propeller having a center of rotation and a plane of rotation, the plane of rotation being substantially perpendicular with and interposing between the first wing and the second wing wherein each of the tips of each propeller, when rotating about each respective propeller center of rotation, pass in close proximately to the leading edge of the first wing and in close proximately to the trailing edge of the second wing.

38. The watercraft airfoil assembly as claimed in claim 37 further comprising at least one propeller motor rotationally driving the at least one propeller.

39. The watercraft airfoil assembly as claimed in claim 38 further comprising mechanical linkage between the at least one rotor drive shaft and at least one propeller motor.

40. The watercraft airfoil assembly as claimed in claim 37 wherein the pitch of each propeller blade is adjustable.

41. A watercraft airfoil assembly comprising:

a first wing having a first starboard wing portion and a first port wing portion, the first wing portion having a leading edge, a trailing edge and a plane of the first wing interposed between a top side and a bottom side of the first wing wherein, in the plane of the first wing, the first wing has at least one starboard arcuate recess and at least one port arcuate recess, each arcuate recess having a chord co-linear with the trailing edge of the first wing; and

at least one starboard rotor and at least one port rotor, each rotor having a plurality blades, a center of planar rotation and an angle of planar rotation incline relative to the plane of the first wing wherein each of the plurality of blades has a pitch angle and a tip distal from the center of planar rotation and wherein rotations of the plurality of blades of the at least one starboard rotor cause the starboard rotor blade tips turning in an air flow to pass proximate to the at least one starboard arcuate recess of the first wing and the at least one port arcuate recess of the first wing and wherein rotations of the plurality of blades of the at least one port rotor cause the port rotor blade tips turning in the air flow to pass proximate to the at least one port arcuate recess of the first wing and wherein the center of planar rotation is aft of the respective chord co-linear with the trailing edge of the first wing.

42. The watercraft airfoil assembly as claimed in claim 41 wherein for each rotor, each of the angles of planar rotation incline relative to the plane of the first wing are adjustable in a plane perpendicular to the plane of the first wing.

43. The watercraft airfoil assembly as claimed in claim 41 wherein for each arcuate recess an angle is subtended by each arcuate recess relative to a center of planar rotation of an associated rotor and said angle is substantially less than 180 degrees.

44. The watercraft airfoil assembly as claimed in claim 41 wherein the at least one arcuate recess of the starboard portion of the first wing and the at least one arcuate recess of the port portion of the first wing each have a vertical section having upper and lower boundaries and wherein rotations of the plurality of blades of the at least one rotor of the starboard portion of the first wing cause the rotor blade tips turning in air flow to pass within the upper and lower boundaries of each vertical section of the starboard portion of the first wing and rotations of the plurality of blades of the at least one rotor of the port portion of the first wing cause the rotor blade tips turning in air flow to pass within the upper and lower boundaries of each vertical section of the starboard portion of the first wing.

45. The watercraft airfoil assembly as claimed in claim 44 wherein adjustable angles of planar rotation incline for each of the rotors relative to the plane of the first wing are constrained so that rotations of the plurality of blades of the at least one starboard rotor and of the at least one port rotor cause the plurality of starboard rotor blade tips turning in air flow and the plurality of port rotor blade tips turning in air flow to pass between the upper and lower boundaries of each respective vertical section.

46. The watercraft airfoil assembly as claimed in claim 41 wherein the pitch of each rotor blade is adjustable.

47. The watercraft airfoil assembly as claimed in claim 41 wherein each rotor furthers comprises a shaft and wherein at least one motor is linked to each shaft and thereby rotationally drives each rotor.

48. The watercraft airfoil assembly as claimed in claim 41 wherein the at last one motor driving each rotor shaft disengages in the event of motor power failure.

49. The watercraft airfoil assembly as claimed in claim 41 wherein the rotor tips have inverse tapers.

50. The watercraft airfoil assembly as claimed in claim 49 wherein the rotor tips are swept.

51. The watercraft airfoil assembly as claimed in claim 41 further comprising a starboard air-blowing means and a port air-blowing means, each air-blowing means being substantially contained within the first wing, wherein the first wing has a starboard top side vent proximate to the first wing and a starboard bottom side vent proximate to the first wing leading edge and a port top side vent proximate to the first wing and a port bottom side vent proximate to the first wing leading edge wherein the starboard air-blowing means and port air-blowing means each blow air aft over the top side of the first wing and aft over the bottom side of the first wing.

52. The watercraft airfoil assembly as claimed in claim 41 further comprising:

a second wing having a leading edge in an airstream, a trailing edge and a plane of the second wing interposed between a top side and a bottom side of the second wing;

at least one aft rotor having a plurality blades, a center of planar rotation and an angle of planar rotation incline relative to the plane of the second wing wherein each of the plurality of blades has a pitch angle and a tip distal from the center of planar rotation and wherein each aft rotor is positioned so that rotations of the plurality of blades about the center of planar rotation cause the aft rotor blade tips turning in air flow to pass proximate to the trailing edge of the second wing and wherein the center of planar rotation is aft of the trailing edge of the second wing; and

a third wing having a leading edge, a trailing edge and a plane of the third wing interposed between a top side and a bottom side of the third wing, wherein the bottom side of the third wing proximate to the leading edge is substantially conformal to the aft topside of a watercraft;

at least one propeller, each propeller having a plurality of blades, each of the plurality of blades having a tip, the at least one propeller having a center of rotation and a plane of rotation, the plane of rotation being substantially perpendicular with and interposing between the second wing and the third wing wherein each of the tips of each propeller, when rotating about each respective propeller center of rotation, pass in close proximately to the leading edge of the second wing and in close proximately to the trailing edge of the third wing.

53. The watercraft airfoil assembly as claimed in claim 52 wherein the angle of planar rotation incline relative to the plane of the second wing is adjustable in a plane perpendicular to the plane of the second wing.

54. The watercraft airfoil assembly as claimed in claim 52 further comprising in the plane of the second wing at least one arcuate recess having a chord co-linear with the trailing edge of the second wing wherein rotations of the plurality of blades of the at least one aft rotor cause the aft rotor blade tips turning in air flow to pass proximate to the at least one arcuate recess of the second wing.

55. The watercraft airfoil assembly as claimed in claim 54 wherein at least one arcuate recess of the second wing has a vertical section having upper and lower boundaries and wherein rotations of the plurality of blades of the at least one aft rotor cause the aft rotor blade tips turning in air flow to pass within the upper and lower boundaries of the vertical section.

56. The watercraft airfoil assembly as claimed in claim 55 wherein an adjustable angle of planar rotation incline relative to the plane of the second wing is constrained so that rotations of the plurality of blades of the at least one aft rotor cause the plurality of rotor blade tips turning in air flow to pass between the upper and lower boundaries of the vertical section.

57. The watercraft airfoil assembly as claimed in claim 52 wherein the pitch of each aft rotor blade is adjustable.

58. The watercraft airfoil assembly as claimed in claim 52 wherein the aft rotor further comprises a shaft wherein a motor linked to the shaft rotationally drives the aft rotor.

59. The watercraft airfoil assembly as claimed in claim 52 wherein the motor driving the aft rotor shaft disengages in the event of power failure.

60. The watercraft airfoil assembly as claimed in claim 52 wherein the aft rotor tips have inverse tapers.

61. The watercraft airfoil assembly as claimed in claim 60 wherein the aft rotor tips are swept.

62. The watercraft airfoil assembly as claimed in claim 52 further comprising an air-blowing means substantially contained within the second wing, wherein the second wing has a top side vent proximate to the second wing leading edge and a bottom side vent proximate to the second wing leading edge wherein the air-blowing means blows air aft over the top side of the second wing and aft over the bottom side of the second wing.

63. The watercraft airfoil assembly as claimed in claim 52 further comprising a propeller motor rotationally driving the propeller.

64. The watercraft airfoil assembly as claimed in claim 52 further comprising the rotor drive shaft linked to the propeller motor.

65. A method of augmenting lift and reducing drag of an airfoil, the method comprising the steps of:

providing an airfoil having a leading edge, in ea airstrip, a trailing edge and a plane of the airfoil interposed between a top side and a bottom side of the airfoil wherein, in the plane of the airfoil, the first wine has at least one arcuate recess having a chord co-linear wit the trailing edge of the airfoil and at least one rotor having a plurality blades, a center of planar rotation and an angle of planar rotation incline relative to the plane of the airfoil wherein each of the plurality of blades has a pitch angle and a tip distal from the center of planar rotation; and

positioning the at least one rotor so that the center of planar rotation is aft of the chord co-linear with the principal trailing edge and wherein rotations of the plurality of blades about the center of planar rotation cause the rotor blade tips turning in air flow to pass proximate to the trailing edge of the first wing and wherein the center of planar rotation is aft of the trailing edge of the first wing;

wherein at least one arcuate recess of the airfoil has a vertical section having upper and lower boundaries and wherein rotations of the plurality of blades of the at least one rotor cause the rotor blade tips turning in an airflow to pass within the upper and lower boundaries of the vertical section.

66. The method of augmenting lift and reducing drag of an airfoil as claimed in claim 65 wherein an adjustable angle of planar rotation incline relative to the plane of the airfoil is constrained so that rotations of the plurality of blades of the at least one rotor cause the plurality of rotor blade tips turning in air flow to pass between the upper and lower boundaries of the vertical section.

67. A method of increasing angle-of-attack of an airfoil without stalling, the method comprising the steps of:

providing an airfoil having a leading edge it a trailing edge and a plane of the airfoil interposed between a top side and a bottom side of the airfoil wherein, in the plane of the airfoil, the first wing has at least one arcuate recess having a chord co-linear with the trailing edge of the airfoil and at least one rotor having a plurality blades, a center of planar rotation and an angle of planar rotation incline relative to the plane of the airfoil wherein each of the plurality of blades has a pitch angle and a tip distal from the center of planar rotation; and

positioning the at least one rotor so that rotations of the plurality of blades about the center of planar rotation cause the rotor blade tips turning in an air flow to pass proximate to the trailing edge of the first wing and wherein the center of planar rotation is aft of the chord co-linear with the trailing edge of the first wing;

wherein at least one arcuate recess of the airfoil has a vertical section having upper and lower boundaries and wherein rotations of the plurality of blades of the at least one rotor cause the rotor blade tips turning in airflow to pass within the upper and lower boundaries of the vertical section; and

wherein the at least one rotor is rotated thereby drawing a portion of the airstream so as to pass substantially over the top side of the airfoil.

68. The method of increasing angle-of-attack of an airfoil without stalling as claimed in claim 67 wherein an adjustable angle of planar rotation incline relative to the plane of the airfoil is constrained so that rotations of the plurality of blades of the at least one rotor cause the plurality of rotor blade tips turning in air flow to pass between the upper and lower boundaries of the vertical section.