Protective finish for wing tip devices
AssigneeThe Boeing Company
InventorDarrell D. Campbell, Jr.
Life of this patent
Estimating the term…
Abstract
The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing.
Claims11
A method for reducing disruptions to laminar airflow on an airfoil, the method comprising:
- preventing airflow from contacting steps of paint layers on the airfoil via applying a sheath to a surface of the airfoil by wrapping the sheath around the surface of the airfoil from a leading edge of the airfoil towards a trailing edge of the airfoil, the sheath at least one of:
- covering, and eliminating the steps;
- and
- eliminating disruptions to laminar airflow generating from an edge of an erosion cap on a leading edge of the airfoil via replacing the erosion cap via the sheath covering approximately 50 percent to approximately 70 percent of a chord length of the airfoil.
A method for expanding an erosion control area and reducing disruptions to laminar airflow on an airfoil, the comprising:
- replacing an existing erosion cap apparatus, extending aft approximately 10% of a wing chord line, via applying a sheath comprising a shape contoured corresponding to a shape of the airfoil, to the airfoil via wrapping the sheath around the surface of the airfoil from a leading edge of the airfoil towards a trailing edge of the airfoil and covering approximately 50 percent to approximately 70 percent of a chord length of the airfoil, and positioning an edge of the sheath, nearest the trailing edge of the airfoil, aft from the leading edge at least to a last point, along the chord length, designed for natural laminar flow on the airfoil.
Dependencies are inferred from the claim text.