Omni-directional airfoil and method for reducing wind damage to structures

• US 7,765,747 B1
• Filed: 02/16/2006
• Issued: 08/03/2010
• Est. Priority Date: 10/17/2005
• Status: Expired due to Fees

• Current Assignee: Arthur L. Smalley III
• Original Assignee: Arthur L. Smalley III
• Inventors: Smalley, Arthur L. III
• Primary Examiner(s): Chilcot, Jr.; Richard E
• Assistant Examiner(s): Gilbert; William V
• Application Number:
  US11/355,755
• Time in Patent Office: 1,629 Days
• Field of Search: 52/84, 521/98, 521/99, 52 24- 26, 454/365, 454/366, 2961801-1805, 343/705, 343/711, 343/713, 180/903, 105/1.02, D14/230, D14/231
• US Class Current: 52/84
• CPC Class Codes: B61D 17/02 reducing air resistance by modifying contour ; Constructional features for fast vehicles sustaining sudden variations of atmospheric pressure, e.g. when crossing in tunnels
• CPC Class Codes: B62D 35/007 Rear spoilers B62D35/001 takes precedence
• CPC Class Codes: B62D 37/02 by aerodynamic means
• CPC Class Codes: B65D 90/22 Safety features floating covers B65D88/34; arrangements of indicating or measuring devices B65D90/48; fire-fighting A62C
• CPC Class Codes: E04H 9/14 against other dangerous influences, e.g. tornadoes, floods
• CPC Class Codes: Y02A 50/00 in human health protection, e.g. against extreme weather
• CPC Class Codes: Y02T 10/82 Elements for improving aerodynamics
• CPC Class Codes: Y02T 30/00 Transportation of goods or passengers via railways, e.g. energy recovery or reducing air resistance
• CPC Class Codes: Y10S 180/903 Airstream reactive vehicle or vehicle structure

Abstract

A method and apparatus for producing a downward, wind-induced lift force on a structure including attaching one or more omni-directional mushroom-shaped airfoil assemblies to the top of the structure which create a downward lift force as they are subjected to wind flow.

Claims

1. An omni-directional airfoil assembly (10) for mounting to a top of a structure (11) and creating a downward lift force thereon, comprising:

a generally planar airfoil (20) characterized by having a circular planform and symmetry about an axis (12) normal to a first plane containing a circumference of said circular planform; and

a base (30) having an upper-end connected to and carrying said airfoil;

said airfoil further characterized in that each planar airfoil section, which is parallel to said axis, which defines an upper airfoil surface (21) connecting a leading edge point (22) and a trailing edge point (24), and which defines a lower airfoil surface (23) connecting said leading edge point and said trailing edge point, defines a mean camber line (28) that is located closer to said lower airfoil surface than a chord line (26);

wherein said mean camber line connects said leading edge point and said trailing edge point and is formed by the locus of points halfway between said upper airfoil surface and said lower airfoil surface, as measured perpendicular to the mean camber line itself; and

wherein said chord line is a straight line segment that connects said leading edge point and said trailing edge point;

wherein said airfoil is substantially solid.

2. The airfoil of claim 1 wherein:

said base is symmetric about said axis.

3. The airfoil of claim 1 wherein:

said top of said structure is attached to a lower end of said base.

4. The airfoil of claim 1 wherein, said base is generally cylindrical and is coaxially located with said axis (12).

5. A method for producing a downward lift force on a portion of a top of a structure (70), the method comprising the steps of:

attaching an omni-directional airfoil (10A) to said portion of said top, said omni-directional airfoil characterized by having a circular planform and symmetry about an axis (12) normal to a first plane containing a circumference of said circular planform, said airfoil further characterized in that for each of all possible planar airfoil sections that can be defined which are parallel to said axis, which define an upper airfoil surface (21) between a leading edge point (22) and a trailing edge point (24), and which define a lower airfoil surface (23) between said leading edge point and said trailing edge point where said lower airfoil surface is not obstructed, a mean camber line (28) is defined by the locus of points halfway between said upper airfoil surface and said lower airfoil surface, as measured perpendicular to the mean camber line itself, so that said mean camber line is located closer to said lower airfoil surface than a chord line (26), wherein said chord line is a straight line that connects said leading edge point and said trailing edge point;

wherein said airfoil is substantially solid;

subjecting said omni-directional airfoil to a wind; and

creating by said omni-directional airfoil a downward lift force directed to said portion of said top.

6. The method of claim 5 further, comprising the step of:

attaching a plurality of said omni-directional airfoils (10A, 10B, 10C) to said top.

7. The method of claim 5 further comprising the step of:

attaching said omni-directional airfoil to a flat top.

8. The method of claim 5 further comprising the step of:

attaching said omni-directional airfoil to a sloping top.

9. The method of claim 5 wherein:

said top is a rooftop of a building.

10. The method of claim 5 wherein:

said top is a vehicle top.

11. The method of claim 5 wherein:

said top is a container top.

12. The method of claim 5 wherein:

said top is a trailer top.

13. The method of claim 5 wherein:

said top is a camper top.

14. The method of claim 5 wherein:

said top is a rail car top.