A cross flow fan includes a plurality of vanes arranged around a rotation axis at predetermined intervals in the circumferential direction, a tongue section arranged on the outer circumferential side of the vanes, and jetting sections that jet a fluid along the wall surfaces of a discharge path into which the fluid is discharged from each of the vanes. A facing wall section is provided to a position facing the tongue section with the vanes therebetween. The facing wall section is provided with: an upstream wall section configured so as to be equivalent to the radius of curvature in the outer circumference of a path formed when the vanes rotate; a downstream wall section that is connected to the upstream wall section and in which the radius of curvature gradually becomes larger than that of the upstream wall section; and a diffuser wall section connected to the downstream wall section.

A first embodiment includes a circuit based unmanned aerial vehicle (UAV) including at least one enclosed air duct vertical z-force circuit, at least one enclosed air duct lateral y-force circuit, and at least one enclosed air duct longitudinal x-force circuit whereby each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The UAV utilizes a magnus effect at strategic points along each respective circuit to apply navigational force thereon. A second embodiment includes a circuit based unmanned aerial vehicle (UAV) including a first and second air duct circuit joined at a medial trunk. Each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The second embodiment also utilizes the magnus effect at strategic points along each respective circuit to apply navigational force thereon.

A fluid control system includes a deformable surface that covers a body in at least a first and second direction. The first direction is orthogonal to the second direction. The deformable surface includes a bottom side that faces the body and a top side that is opposite the bottom side. The fluid control system also includes at least one deformer between the deformable surface and the body. The at least one deformer is configured to modify a boundary layer of a fluid that is flowing over the deformable surface by selectively deforming the top side of the surface.

Fixed-wing short-takeoff-and-landing aircraft and related methods. The aircraft comprise an airframe comprising a rear wing assembly and a forward wing assembly positioned forward of the rear wing assembly, a rear plurality of blowing rotor assemblies operatively coupled to the rear wing assembly that are configured to blow air across the rear wing assembly to induce lift in the rear wing assembly, and a forward plurality of blowing rotor assemblies that are operatively coupled to the forward wing assembly and configured to blow air across the forward wing assembly to induce lift in the forward wing assembly. The methods comprise inducing lift in a forward wing assembly by blowing air across the forward wing assembly with a forward plurality of blowing rotor assemblies and inducing lift in a rear wing assembly by blowing air across a rear wing assembly with a rear plurality of blowing rotor assemblies.

Fixed-wing short-takeoff-and-landing aircraft and related methods. The aircraft comprise an airframe comprising a rear wing assembly and a forward wing assembly positioned forward of the rear wing assembly, a rear plurality of blowing rotor assemblies operatively coupled to the rear wing assembly that are configured to blow air across the rear wing assembly to induce lift in the rear wing assembly, and a forward plurality of blowing rotor assemblies that are operatively coupled to the forward wing assembly and configured to blow air across the forward wing assembly to induce lift in the forward wing assembly. The methods comprise inducing lift in a forward wing assembly by blowing air across the forward wing assembly with a forward plurality of blowing rotor assemblies and inducing lift in a rear wing assembly by blowing air across a rear wing assembly with a rear plurality of blowing rotor assemblies.

A lift control device actively controls the lift force on a lifting surface. The device has a protuberance near a trailing edge of its lifting surface, which causes flow to separate from the lifting surface, generating regions of low pressure and high pressure which combine to increase the lift force on the lifting surface. The device further includes an arrangement to keep the flow attached around the protuberance or to modify the position of the protuberance in response to a command from a central controller, so as to provide an active control of the lift between a maximum value and a minimum value.

A lift control device actively controls the lift force on a lifting surface. The device has a protuberance near a trailing edge of its lifting surface, which causes flow to separate from the lifting surface, generating regions of low pressure and high pressure which combine to increase the lift force on the lifting surface. The device further includes an arrangement to keep the flow attached around the protuberance or to modify the position of the protuberance in response to a command from a central controller, so as to provide an active control of the lift between a maximum value and a minimum value.

A lift nacelle may comprise an airflow generator; a sidewall system coupled to the airflow generator and spanning in a first direction, wherein the sidewall system defines a nacelle interior space, wherein the airflow generator defines one of a forward boundary or an aft boundary of the nacelle interior space; and a lift body disposed in the nacelle interior space and spanning substantially perpendicular to the first direction and substantially perpendicular to an upward lift direction. The airflow generator may be configured to accelerate airflow in an aft direction into the nacelle interior space through the forward boundary of the nacelle interior space. The airflow may contact and/or interact with the lift body creating lift in response.

The invention relates to aviation equipment. An object of this invention is to develop a new non-conventional aerodynamic apparatus that can increase the efficiency of the air flow power use to generate lifting force, control moments and the reactive thrust of the apparatus. For this purpose, the aerodynamic apparatus containing a body, fan blowers with drive motors (1, 22), wings (3, 7), a system for operating medium temperature control (28, 29, 30), an external communication unit (13, 14, 26, 27) with the openings in the external body (17), according to the invention, due to the principal design solutions connected with the use of the primary rotary wing (3) and the steering rotary wing (7) made in a petal-like shape, of the sphere shaped external (17), middle (19) and internal (20) bodies affecting the nature of the operating medium motion, for the operating medium flow segments, the optimum sphere shaped paths have been obtained, which minimizes losses by airflow friction. In so doing, the functions of the external communication unit are performed by the appropriate motor driven valves (13, 14, 26, 27). The structural parts of the present invention meet the special conditions.

A fluid control system includes a deformable surface that covers a body in at least a first and second direction. The first direction is orthogonal to the second direction. The deformable surface includes a bottom side that faces the body and a top side that is opposite the bottom side. The fluid control system also includes at least one deformer between the deformable surface and the body. The at least one deformer is configured to modify a boundary layer of a fluid that is flowing over the deformable surface by selectively deforming the top side of the surface.