Disclosed are methods and apparatuses for mitigating the formation of concentrated wake vortex structures generated from lifting or thrust-generating bodies and maneuvering control surfaces wherein the use of contour surface geometries promotes vortex-mixing of high and low flow fluids. The methods and apparatuses can be combined with various drag reduction techniques, such as the use of riblets of various types and/or compliant surfaces (passive and active). Such combinations form unique structures for various fluid dynamic control applications to suppress transiently growing forms of boundary layer disturbances in a manner that significantly improves performance and has improved control dynamics.

A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor. An aircraft structure, for example a wing, includes a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing).

An aerodynamic lift enhancing system for increasing aerodynamic lift generated by a body of an automotive flying vehicle is disclosed. The automotive flying vehicle includes a vehicle body enclosing a passenger compartment and having an upper surface at least partially defined by a hood, a roof extending over the passenger compartment, and a front windshield disposed between the hood and roof. The front windshield includes a leading edge positioned proximate a trailing edge of the hood and a trailing edge positioned adjacent the roof. The automotive flying vehicle includes wings extending laterally outward from the vehicle body. The aerodynamic lift enhancing system includes an air discharge nozzle located upstream from the leading edge of the front windshield, the air discharge nozzle operable to discharge a stream of air over the upper surface of the vehicle.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

A flow body and method for taking in and/or blowing out fluid through a plurality of openings in a flow surface section of a flow body is disclosed. In some aspects, the flow body includes a flow surface section that extends in a flow body wingspan direction and a flow body chord direction and with a plurality of fluid lines that lead into the flow surface section and respectively form an opening therein. In some aspects, the method includes taking in and/or blowing out fluid through at least one fluid line that leads into a flow surface section of a flow body and respectively forms an opening therein.

A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators.

A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.

A boundary-layer-influencing aerodynamic part comprises a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element, an air guiding layer disposed on the carrier element and a cover layer constituting at least a part of a flow surface and being configured to have air flow there through at least in sections. The air guiding layer is configured to have air flow there through with an air flow supplied to the part, at least in certain operating phases of the part, through the cover layer and flowing in the direction of the carrier element or through the air passage aperture of the carrier element and flowing in the direction of the cover layer. The cover layer is applied directly to the air guiding layer via an additive manufacturing method.

A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor. An aircraft structure, for example a wing, includes a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing).

The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings.