초록 ▼

This invention uses a novel shape of airfoil to achieve an improved lift to drag ratio and to improve performance at higher angles of attack. The airfoil has a three dimensional wave pattern that modifies the shape of a traditional airfoil to coordinate the airflow through channels on both the top a

This invention uses a novel shape of airfoil to achieve an improved lift to drag ratio and to improve performance at higher angles of attack. The airfoil has a three dimensional wave pattern that modifies the shape of a traditional airfoil to coordinate the airflow through channels on both the top and bottom sides. The uniquely shaped airfoil of this invention could have many uses including a wind turbine blade. This invention not only provides for a more efficient device by improving the effective angle of attack and lift/drag ratio, but also provides for a quiet airflow thus greatly reducing nuisance noise over conventional devices.

대표청구항 ▼

1. An airfoil comprising a leading edge, a trailing edge and upper and lower surfaces wherein said airfoil has a lateral wave-like shape forming a surface waveform comprised of a plurality of alternating peaks and troughs such that the airfoil surfaces are synchronized such that the upper surface pe

1. An airfoil comprising a leading edge, a trailing edge and upper and lower surfaces wherein said airfoil has a lateral wave-like shape forming a surface waveform comprised of a plurality of alternating peaks and troughs such that the airfoil surfaces are synchronized such that the upper surface peak, or convexity is directly over the lower surface trough, or concavity and the peaks and troughs extends substantially for the entire chord length of the airfoil from the leading edge to the trailing edge and said alternating peaks and troughs are integral to the waveform cross-section and not additions and subtractions to a flat airfoil. 2. The airfoil of claim 1 wherein said surface waveform is of a constant wavelength from one edge of the airfoil to the other. 3. The airfoil of claim 1 wherein said surface waveform is of a constant amplitude from one edge of the airfoil to the other. 4. The airfoil of claim 1 wherein said surface waveform is variable in either wavelength and/or amplitude from one edge of the airfoil to the other. 5. The airfoil of claim 1 wherein said airfoil provides means of increasing the lift over drag ratio and delaying boundary layer separation of an air stream over said airfoil delaying stall. 6. The airfoil of claim 1 wherein said airfoil is utilized as blades in a vertical axis wind turbine (VAWT) system. 7. The airfoil of claim 1 wherein said airfoil is utilized as blades in a horizontal axis wind (HAWT) turbine system. 8. The airfoil of claim 1 wherein said airfoil is utilized as wings for a fixed or rotary winged aircraft. 9. The airfoil of claim 1 wherein said airfoil is utilized as a propeller blade. 10. The airfoil of claim 6 wherein said VAWT airfoil blades have the waveforms at an angle of attack with respect to the wind of from 0 to 45 degrees. 11. The airfoil of claim 7 wherein said HAWT airfoil blades have the waveforms at an angle of attack with respect to the wind of from 0 to 45 degrees. 12. A method of delaying the boundary layer separation of airflow over an airfoil; said airfoil having a wave shape such that the upper and lower surfaces are aligned such that the convexity of one surface is aligned with the concavity of the other surface and said wave shape extends from the leading edge to the trailing edge and runs the entire chord length; wherein said concavities and convexities are integral with the airfoil cross-section and are not additions to a flat airfoil. 13. The method of claim 12 wherein said wave shaped surfaces reduce the propagation of stall along said airfoil surface. 14. The method of claim 12 wherein said wave shaped surfaces cause the air to be forced into troughs and away from peaks of the waveform resulting in a pressure differential between the trough on one surface and the peak on the other surface of the airfoil. 15. The method of claim 14 wherein said increased air pressure through the troughs on the upper and lower wavy surfaces of said airfoil cross at a distance slightly behind the trailing edge.