The present invention Aircraft Wing with Tiplet reflects a wing with two distinct sections including inner section for maximized lift production with long chords, high taper, and ultra-thin airfoils for substantial profile drag reduction, as well as a tiplet section with minimized area and maximized span to minimize aspect ratio penalty from the standpoint of increased induced drag mitigation due to large inner section lifting area. Long chords and large area of inner section are feasible from the standpoint of flight safety with the application of airfoils with forward center of pressure that provide for dynamic stability of aircraft in flight.

In one embodiment, an airfoil includes a first end and a second end opposite the first end. The airfoil also includes a first side and a second side opposite the first side. The airfoil includes a continuous panel coupled to the first side of the airfoil. The continuous panel includes a first edge having a first uneven edge pattern. The first edge has at least four vertices disposed thereon. The continuous panel extends from the first end of the airfoil to a second end of the airfoil.

Systems and methods for reducing or weakening the shocks acting on an airfoil, such as an airfoil of an airplane wing. In one embodiment, the length of an airfoil is increased by shifting the trailing edge aft by installing a trailing edge extender. In one embodiment, the length and shape of an airfoil is changed by shifting the trailing edge aft and downward by installing a trailing edge extender. In one embodiment, an airfoil is changed by removing a portion of the wing at the trailing edge and increasing the camber by installing a trailing edge modifier to adjust the circulation surrounding the wing and redistribute loading of the wing. Modifications of an airplane wing, including installing a trailing edge extender, are easy to implement, do not require span extensions or tip devices, and improve fuel efficiency.

Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.

This disclosure provides construction variants of a cruise miniflap of an aircraft wing that is added to trailing edge flap of an aircraft wing and can be used for improving the aerodynamic properties of an aircraft. In the rear edge of the cruise miniflap there is a cavity with a height of up to 1% of the wing chord.

Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.

An airfoil that comprises a chamber having a forward-facing chamber opening may result in increased lift and decreased drag relative to a standard airfoil having deployed flaps, for example on an airplane wing. In embodiments, the chamber opening is located on or near the pressure surface of the airfoil. The airfoil chamber may enhance the lift-generating ability of the airfoil due to increased pressure at the pressure surface.

Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary element and the secondary element, and an axial overlap between the first trailing edge and the second leading edge. The secondary element is deflectable with respect to the primary element about a fixed hinge point by a flap deflection angle. The secondary element is configured to operate in airbrake mode when deflected by a respective the flap deflection angle corresponding to a design airbrake deflection angle wherein to generate an airbrake drag. In at least some examples, the axial overlap is numerically greater than 0.5% of the aerofoil chord, at least for the design airbrake deflection angle. Also disclosed are methods for operating air vehicles, and methods for designing two-element aerofoils.

A complex-shaped, three-dimensional fiber reinforced composite trailing edge structure may be formed by using counteracting pressures applied to a structural lay-up of wetted fibers placed onto pressurizable members to form continuous fore and aft loops. In turn, the loops may be structurally functional to transfer loads from the trailing edge structure to a wing center section. The trailing structure may include may include fillers and/or a metallic insert, wherein the metallic insert may provide a lightening strike capability for the trailing edge structure.

In one embodiment, a vertical stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a vertical orientation. The airfoil structure comprises a leading edge and a trailing edge, wherein the trailing edge is configured to form a blunt shaped edge. The airfoil structure further comprises a root end and a tip end, wherein the airfoil structure is tapered from the root end to the tip end. The airfoil structure is also cambered. Finally, the airfoil structure is further configured to be mounted with a rotor, and is also further configured to house one or more internal components associated with the aircraft.