Boundary layer control system and methods thereof
OwnerDavid Birkenstockinventor
Life of this patent
Estimating the term…
Abstract
An airfoil boundary layer control system may be provided. The airfoil boundary layer control system may include at least one airfoil that may include a first surface and a second surface coupled together at a leading edge and a trailing edge; at least one hollow chamber defined within the at least one airfoil; and an aperture defined in the airfoil and positioned substantially near the trailing edge, the aperture coupled in flow communication with the at least one hollow chamber; a pressure source coupled in flow communication with the at least one hollow chamber.
Claims24
An airfoil boundary layer control system comprising:
- at least one airfoil comprising:
- a first surface and a second surface coupled together at a leading edge and a trailing edge;
- at least one hollow chamber defined within said at least one airfoil;
- and
- an aperture defined in said at least one airfoil and positioned substantially near said trailing edge, said aperture coupled in flow communication with said at least one hollow chamber;
- and
- a pressure source coupled in flow communication with said at least one hollow chamber.
A fuselage boundary layer control system comprising:
- an aircraft comprising a fuselage;
- a tail cone having a substantially conical shape and coupled to said fuselage such that an inlet is defined between said tail cone and said fuselage, said tail cone comprising:
- a first surface having a substantially concave shape;
- and
- a hollow chamber defined in said tail cone;
- and
- a pressure source coupled to said tail cone and positioned within said hollow chamber, said pressure source coupled in flow communication with said inlet.
A method of removing at least a portion of boundary layer air passing over an airfoil, comprising:
- providing an airfoil that includes at least one hollow chamber defined therein and an aperture defined on the airfoil and coupled in flow communication with the hollow chamber;
- creating a pressure within the hollow chamber using a pressure source in flow communication to the hollow chamber;
- and
- channeling air through the aperture using the pressure source.
A method of removing at least a portion of boundary layer air passing over a fuselage of a craft, comprising:
- providing a substantially conical tail cone coupled to the fuselage, the tail cone includes a first concave surface and a pressure source coupled to the tail cone and positioned within a hollow chamber of the tail cone;
- and
- channeling at least a portion of a boundary layer air of an airflow into an inlet defined between the tail cone and the fuselage using the pressure source.
Dependencies are inferred from the claim text.