In one embodiment, a method of determining the onset of a stall condition in a vehicle is provided. The method comprises: measuring, with a stall detection system, data which would indicate the presence of turbulent fluid flowing proximate to a foil; determining from the data whether an onset of a stall condition has occurred; and upon determining the onset of the stall condition, performing at least one of: issuing an alert, and causing the vehicle to avoid or exit the stall condition, and cease such activity when the onset of the stall condition no longer exists.

A lifting foil having a configuration with a leading course and trailing course which is rotated about an axis of rotation into a fluid.

An aircraft includes a fuselage and a pair of channel wings which may vary incidence with respect to the fuselage and a pair of channel canards which can also vary incidence with respect to the fuselage and that can move independently of each other for the purpose of vertical takeoff and landing as well as forward and reverse flight. The wings may have multiple channels and may be powered by single propeller or contra-rotating propellers. The thrust to the propellers may be provided with an internal combustion engine or electric motors or a turbo prop or hybrid system. The channel wing allows the fuselage to maintain a level pitch with respect to the horizon. The aircraft will also have increased maneuverability in hover because it can independently vary the incidence of the wings and canards and be able to tightly turn about a point.

The herein invention is presenting a lift generating method based on a semi-open fluid jet flowing in a closed circuit around a lifting airfoil. A VTOL aircraft with maximized payload room and car-like shape is the preferred embodiment of the invention. The herein aircraft uses no wings, exposed propellers, hot gas jets or other high injury risk means for propulsion and lift, and it can be driven by ordinary skilled people. Furthermore the aircraft has a small footprint and can land, take off and even cruise on water in one of the preferred embodiments.

In at least some implementations, an aircraft includes a fuselage, a wing spar rotatably carried by the fuselage, a first wing element and a second wing element. The first wing element is carried by the wing spar, rotatable with the wing spar, and slidably moveable relative to the fuselage and wing spar. The second wing element is connected to the first wing element for pivoted movement of the second wing element relative to the first wing element. The second wing element at least partially overlaps the first wing element and the first and second wing elements are moveable to a plurality of positions wherein the amount that the second wing element overlaps the first wing element varies to vary the effective combined wing area of the wing elements.

A vehicle includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tad conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. One or more ejectors are fluidically coupled to the plenum via one or more valves. A nozzle is disposed within the output port and includes a set of vanes. The system operates in a first configuration in which the nozzle vanes are closed and the compressed ambient air exits the plenum only through the one or more valves into the one or more ejectors. The system operates in a second configuration in which the one or more valves are closed, the nozzle vanes are open and the compressed ambient air exits the plenum only through the output port.

A helicopter is described comprising a fuselage elongated along a first axis and extending between a nose and a tail boom; a tailplane with a pair of first aerodynamic surfaces elongated along a second axis; the first and second axis define a first plane; the helicopter comprises a pair of elements transversal to the first aerodynamic surfaces; and a pair of second aerodynamic surfaces generating respective second aerodynamic forces, connected to first elements, and facing and spaced from respective first aerodynamic surfaces; each second aerodynamic surface comprises one first root end connected to the respective said element, a second free end spaced from said tail boom, a first leading edge, a first trailing edge opposite to said first leading edge, a first chord at said first root end and a second chord at said second free end parallel to said first axis; the first and the second chord define a second plane tilted with respect to said first plane.

A vehicle includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tad conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. One or more ejectors are fluidically coupled to the plenum via one or more valves. A nozzle is disposed within the output port and includes a set of vanes. The system operates in a first configuration in which the nozzle vanes are closed and the compressed ambient air exits the plenum only through the one or more valves into the one or more ejectors. The system operates in a second configuration in which the one or more valves are closed, the nozzle vanes are open and the compressed ambient air exits the plenum only through the output port.