A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction.

A blade is provided for the cycloidal marine propellers or cycloidal aerial rotors. Said blade is provided with the capabilities, in response to the control system commands to dynamically and in real time; flex itself along its chord in any required way, vary its relative pivot point position, change its planform by extending or retracting a trailing edge extension, differentially if needed on the right and left, turn the flap along the trailing edge in either direction or allow it to be turned by the flows. Said blade is also optionally provided with one or more elastic trailing edges whose stiffness is dynamically, and possibly differentially along the blade span, variable by the control system. For the reversal of the leading and trailing edges for operation in reverse airflow and other conditions the blades are provided with edges that can be made rigid when functioning as the leading edge and flexible if needed when functioning as the trailing edge. Also the blades are provided with the capability of varying their cross-sectional profile thickness and reshaping it. Finally the blades are given on command flow permeability along much of their surface. These capabilities will enable each control system controlled blade to continually optimally adjust to and make the best use of its immediate operating environment as it travels along its trajectory within each revolution.

A blade is provided for the cycloidal marine propellers or cycloidal aerial rotors. Said blade is provided with the capabilities, in response to the control system commands to dynamically and in real time; flex itself along its chord in any required way, vary its relative pivot point position, change its planform by extending or retracting a trailing edge extension, differentially if needed on the right and left, turn the flap along the trailing edge in either direction or allow it to be turned by the flows. Said blade is also optionally provided with one or more elastic trailing edges whose stiffness is dynamically, and possibly differentially along the blade span, variable by the control system. For the reversal of the leading and trailing edges for operation in reverse airflow and other conditions the blades are provided with edges that can be made rigid when functioning as the leading edge and flexible if needed when functioning as the trailing edge. Also the blades are provided with the capability of varying their cross-sectional profile thickness and reshaping it. Finally the blades are given on command flow permeability along much of their surface. These capabilities will enable each control system controlled blade to continually optimally adjust to and make the best use of its immediate operating environment as it travels along its trajectory within each revolution.

A blade for cycloidal rotor or propeller is provided with means to dynamically change within each revolution: its relative pivot point location along chord, extend or retract trailing edge, make actuated or passive turns of trailing edge flap, dynamically control stiffness of at least the flexible trailing edge, open or close strips covering much of blade surface area to allow flow through the blade. These features will enable the control system to continually adjust each blade to its immediate operating environment along the orbit.

A blade for cycloidal rotor or propeller is provided with means to dynamically change within each revolution: its relative pivot point location along chord, extend or retract trailing edge, make actuated or passive turns of trailing edge flap, dynamically control stiffness of at least the flexible trailing edge, open or close strips covering much of blade surface area to allow flow through the blade. These features will enable the control system to continually adjust each blade to its immediate operating environment along the orbit.

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.

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.

Embodiments of the invention relate to advanced propeller assemblies that include a pressure modifying element that modifies its aerodynamic characteristics. Embodiments of the invention may provide benefits including but not limited to: increased thrust per rotation, greater efficiency, modified aerodynamics, and the ability to use such propellers for novel applications. Practical applications for embodiments of propellers of the invention include use with aircraft, drones, watercraft, autogyros, fans, blowers, pumps, generators, compressors, mixers, and blenders.

Embodiments of the invention relate to advanced propeller assemblies that include a pressure modifying element that modifies its aerodynamic characteristics. Embodiments of the invention may provide benefits including but not limited to: increased thrust per rotation, greater efficiency, modified aerodynamics, and the ability to use such propellers for novel applications. Practical applications for embodiments of propellers of the invention include use with aircraft, drones, watercraft, autogyros, fans, blowers, pumps, generators, compressors, mixers, and blenders.

The invention relates to a profiled structure, elongated in a direction in which the structure has a length exposed to an airflow, and transversely to which the structure has a leading edge (164) and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations (28a) defined by successive teeth (30) and depressions (32).

Along the profiled leading edge and/or profiled trailing edge, the successive teeth (30) and depressions (32) extend only over a part of said length exposed to the flow over which the amplitude and/or spacing of the teeth varies monotonically except for the few teeth nearest each end of said part, a remaining part (280) of said length being smooth.