Boundary layer control system and methods thereof

摘要

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.

主权项

1. 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 relative to an airflow passing over said fuselage; anda hollow chamber defined in said tail cone; 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 second surface having a substantially concave shape and positioned a radial distance from said first surface such that a second hollow chamber is defined between said first surface and said second surface; and a conical aperture defined in said tail cone and in flow communication with said second hollow chamber.