An STOL and/or VTOL aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator
An STOL and/or VTOL aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage with movable surfaces for controlling the aircraft; and (3) a wing on each side of the fuselage having a front edge, a trailing edge and an upper surface extending from the front edge to the trailing edge. A device for controlling the airflow over the upper surfaces of the wings comprises openings in these upper surfaces for the egress of air from interior spaces within the wings and air pump apparatus for pressurizing such interior spaces.
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1. An aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft;(b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elev
1. An aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft;(b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft;(c) a wing on each side of the fuselage, each wing having a leading edge, a trailing edge, an upper surface and a lower surface extending from the leading edge to the trailing edge thereof;(d) a first device for increasing the speed of the air stream flowing over the upper surface of each wing having at least one air blower disposed on each wing which includes: (1) at least one shaft mounted for rotation in the respective wing component and extending substantially parallel to said wing axis; and(2) a plurality of fan blades attached to each shaft and configured to cause movement of air over said upper surface in a direction toward the trailing edge of the respective wing component upon rotation of the respective shaft, at least a portion of said fan blades extending above said upper surface; and(e) a second device for controlling an air stream flowing over the upper surface of each wing, said device comprising: (1) a plurality of openings in the material forming the upper surface of the respective wing for the egress of air from at least one interior space within the respective wing to said upper surface thereof, said openings being disposed in said upper surface in a region between the leading edge and trailing edge of the wing and being configured to (i) emit air over an airflow surface formed by at least a portion of said upper surface, and (ii) entrain, with the emitted air, other air that moves over said upper surface; and(2) an air pump apparatus for pressurizing said at least one interior space within each wing in communication with said openings,wherein said openings are configured to direct airflow over the upper surface of each wing in a direction toward said trailing edges thereof and to entrain and control the flow of said other air that moves over said upper surface; andwherein at least a portion of said second device is arranged in said wing aft of said first device in the direction of flow of the air stream. 2. The aircraft recited in claim 1, further comprising openings in the material forming the lower surface of each wing for the egress of a from at least one interior space within the respective wing to said lower surface of said wing. 3. The aircraft defined in claim 1, wherein said air pump apparatus is operative to individually vary the pressure within said at least one interior space within each wing. 4. The aircraft defined in claim 1, wherein the fan blades are elongate and extend substantially parallel to the shaft to which they are attached. 5. The aircraft defined in claim 1, further comprising a shroud in each wing, disposed adjacent and above said fan blades, which directs the air rearward, thereby increasing the vertical lift of said aircraft wing. 6. The aircraft defined in claim 5, wherein at least a portion of said shroud is movable in the vertical direction. 7. The aircraft defined in claim 1, wherein the airspeed increasing device comprises two shafts mounted for rotation in each wing, said two shafts extending substantially in parallel to said wing axis and to each other, each of said two shafts being driven by a common prime mover and having a plurality of fan blades attached thereto for movement of air. 8. The aircraft definedis claim 7, wherein said two shafts mounted in each wing are driven in counter rotation by said prime mover. 9. The aircraft defined in claim 8, wherein said two shafts mounted sufficiently close together such that their respective fan blades are interleaved. 10. The aircraft defined in claim 9, wherein the fan blades are configured to inhibit air from passing between said two shafts, thereby forming a Roots-type blower configuration. 11. The aircraft defined in claim 8, wherein said two shafts are mounted sufficiently far apart such that their respective fan blades are not interleaved. 12. The aircraft defined in claim 11, wherein said two shafts are driven in counter rotation by said prime mover in a direction causing air to be directed rearward between said two shafts. 13. A personal aircraft (PAC) capable of short take-off and landing (STOL) or vertical take-off and landing (VTOL) and having a center of gravity, said aircraft comprising, in combination: (a) an elongate fuselage having two lateral sides and forming a passenger compartment, said fuselage being arranged along a longitudinal axis of said aircraft;(b) an elongate fixed wing having a leading edge and a trailing edge and a longitudinal wing axis between them, said fixed wing being attached to the fuselage and extending outward from the two lateral sides thereof with the wing axis substantially perpendicular to said longitudinal axis of said aircraft, the center of gravity of said aircraft being located in a region between the leading edge and the trailing edge of said wing, said wing having a first wing component extending outward from one lateral side of said fuselage and second wing component extending outward from an opposite lateral side of said fuselage, each said wing component having an upper surface;(c) a first device disposed on each wing component for increasing the speed of an air stream flowing over the upper surface of the respective wing component as compared to the speed of an air stream flowing over the lower surface thereof, said air speed increasing device comprising: (1) at least one shaft mounted for rotation in the respective wing component and extending substantially parallel to said wing axis; and(2) a plurality of fan blades attached to each shaft and configured to cause movement of air over said upper surface in a direction toward the trailing edge of the respective wing component upon rotation of the respective shaft, at least a portion of said fan blades extending above said upper surface; and(d) a second device for controlling an air stream flowing over the upper surface of each wing component, said device comprising: (1) a plurality of openings in the material forming the upper surface of the respective wing component for the egress of air from at least one interior space within the respective wing component to said upper surface thereof, said openings being disposed in said upper surface in a region between the leading edge and trailing edge of the respective wing component and being configured to (i) emit air over an airflow surface formed by at least a portion of said upper surface, and (ii) entrain, with the emitted air, other air that moves over said upper surface; and(2) an air pump apparatus for pressurizing said at least one interior space within each wing component in communication with said openings, wherein said openings are configured to direct airflow over the upper surface of each wing component in a direction toward said trailing edges thereof and to entrain and control the flow of said other air that moves over said upper surface; andwherein at least a portion of said second device is arranged in said wing component aft of said first device in the direction of flow of the air stream. 14. Th aircraft defined in claim 13, Where in the fan blades are elongate and extend outward substantially perpendicular to the shaft to which said fan blades are attached. 15. The aircraft defined in claim 13, further comprising a shroud in each wing component adjacent to and above said fan blades, which extends substantially parallel to the upper surface of said wing and constricts air that is moved by said fan blades to flow in a direction substantially parallel to said upper surface of said wing, thereby to increase the speed of airflow over said upper surface and enhance the vertical lift of said aircraft wing. 16. The aircraft defined in claim 15, wherein the shroud is configured to taper in the direction of the upper surface of the respective wing to form a nozzle for increasing the speed of air passing over the upper surface. 17. The aircraft defined in claim 13, wherein said airflow surface adjacent at least some of said openings is a Coanda surface. 18. The aircraft defined in claim 1, wherein said airflow surface adjacent at least some of said openings is a Coanda surface.
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