Hydrodynamically and aerodynamically optimized leading and trailing edge configurations

• US 20040007149A1
• Filed: 10/11/2002
• Published: 01/15/2004
• Est. Priority Date: 07/12/2002
• Status: Active Grant

• Current Assignee: Arthur Vanmoor
• Original Assignee: Arthur Vanmoor
• Inventors: Vanmoor, Arthur
• Granted Patent: US 7,017,508 B2
• Time in Patent Office: Days
• US Class Current: 102/501
• CPC Class Codes: F42B 5/025 characterised by the dimension of the case or the missile

Abstract

A novel concept for a hydrodynamically and aerodynamically improved leading edge and trailing edge structure is primarily suited for high-speed motion, such as near Mach 1 and above, but also for slow-speed motion and for stationary operation, where stationary structures are subjected to fluid flow. The configuration incorporates the model of the natural wave behavior. The leading edge of the aircraft, of the train, of the submarine, or the like, has a sharp tip which merges smoothly into a cylindrical or rectangular body. The merging segment from the tip to the cylinder may be defined with a tangent function. The rounding of the surfaces promote proper fluid sheet formation along the surface and to reduce undesirable vortice formation and thus to reduce the value of several drag factors.

Claims

1. A dynamically optimized structure, comprising:

a body segment;

a tip segment adjoining said body segment and smoothly merging from said body segment to a tip, said tip segment being defined, at least in one section, by a function y=s tan x, where x and y are Cartesian coordinates and y extends parallel to a direction from said body segment to said tip segment, and s is a real number greater than zero.

2. The structure according to claim 1, wherein said body segment is substantially cylindrical in a section orthogonal to a center axis thereof, and said tip segment is defined by the function y=s tan x in a multitude of sections through said center axis.

3. The structure according to claim 1, wherein s is a constant.

4. The structure according to claim 1, wherein s is a number greater than 1.

5. The structure according to claim 1, wherein s is a function of x and has a maximum value smaller than a maximum value of x.

6. The structure to claim 1, which comprises a tail segment adjoining said body segment opposite from said tip segment and smoothly merging from said body segment to a tail, said tail segment being defined, in at least one section through an axis connecting said tip to said tail, by a function mirroring the function y=s tan x of said tip segment.

7. The structure according to claim 6, wherein said body segment is substantially cylindrical in a section orthogonal to said axis, and said tail segment is defined by the function y=s tan x in a multitude of sections through said axis.

8. The structure according to claim 1, which comprises a tail segment adjoining said body segment opposite from said tip segment and having a backwall substantially orthogonal to said axis.

9. The structure according to claim 1, which comprises a tail segment adjoining said body segment opposite from said tip segment, said tail segment having an outline surface smoothly merging from said body segment inward to a further cylindrical tail segment having a smaller diameter than said cylindrical body segment, and having a backwall substantially orthogonal to said axis.

10. The structure according to claim 1, which comprises a tail segment having a material composition with a specific weight less than a specific weight of said tip segment.

11. An aerodynamically optimized aircraft body, comprising:

a body segment having a center axis and a substantially round periphery;

a nose segment adjoining said body segment and smoothly merging from said body segment to a tip, said nose segment being defined, at least in one section, by a function y=s tan x, where x and y are Cartesian coordinates and y extends parallel to said center axis, and s is a real number greater than zero.

12. The aircraft body to claim 11, which comprises a tail segment adjoining said body segment opposite from said nose segment and smoothly merging from said substantially round body segment to a tail, said tail segment being defined, in at least one section through said center axis, by a function mirroring the function y=s tan x of said nose segment.

13. An aerodynamically optimized train structure, comprising:

a body segment having a substantially rectangular periphery and a longitudinal extent defining a travel direction of the train structure;

a tip segment adjoining said body segment and smoothly merging from said body segment to a tip, said tip segment being defined, at least in one section, by a function y=s tan x, where x and y are Cartesian coordinates and y extends parallel to said longitudinal extent, and s is a real number greater than zero.

14. The train structure according to claim 13, wherein the function y=s tan x is defined by a substantially vertical section through said longitudinal extent.

15. The train structure according to claim 14, wherein the function y=s tan x is defined by a substantially horizontal section.

16. A hydro-dynamically optimized hull structure, comprising:

a body segment to be at least partially submersed during an operation of the hull structure;

a tip segment adjoining said body segment and smoothly merging from said body segment to a tip, said tip segment being defined, at least in one section, by a function y=s tan x, where x and y are Cartesian coordinates and y extends parallel to a direction from said body segment to said tip segment, and s is a real number greater than zero.

17. The hull structure according to claim 16, wherein said body segment is substantially cylindrical in a section orthogonal to a longitudinal axis thereof, and said tip segment is defined by the function y=s tan x in a multitude of sections through said longitudinal axis.

18. The hull structure according to claim 17, wherein said body segment, said tip segment and a tail segment together form a submarine hull.

19. The hull structure according to claim 16, which further comprises a tail segment adjoining said body segment opposite from said tip segment and smoothly merging from said body segment to a tail, said tail segment being defined, in at least one section through an axis connecting said tip to said tail, by a function mirroring the function y=s tan x of said tip segment.

20. The hull structure according to claim 19, wherein said body segment is substantially cylindrical in a section orthogonal to said axis, said tail segment is defined by the function y=s tan x in a multitude of sections through said axis, and said body segment, said tip segment and said tail segment together form a hydrodynamically optimized submarine hull.