Abstract: A ground-air-water craft comprises a fuselage body with a passenger compartment mounted thereon, a box-type main wing connected to the fuselage and extending outwardly on both sides thereof, the main wing comprising an upper wing and a lower wing which are substantially horizontal and which have a total wing span in the range of 5 to 10 feet, as well as a right side member and a left side member, each side member extending substantially vertically and connected between the lateral ends of the upper and lower wings on the respective right and left sides of the craft. The craft also comprises a control or canard wing connected to the fuselage and extending outwardly on both sides of the fuselage with a wing span no greater than 10 feet.

Abstract: A convertible airplane to automobile and visa versa, having a fuselage and three wings, including a forward canard wing, a foldable main wing and a secondary lift wing. The foldable wing is capable of folding to a size for safely driving the automobile on a roadway. All wings are used as ground effect airfoils for roadway use.

Abstract: An aircraft having paired aerofoils 12, 14 and 24, 26, the wing tips 16 and 18 being joined in the same plane one behind the other. The trailing edge of the forward wings and the leading edge of the rearward wings being substantially coincidental in plan view at the wing tip. The minimum angle between the wings 12 and 24 is 4 degrees at the tips of the wing. The substantial part of the forward wings is higher than the rearward wings.

Abstract: A twin-engine supersonic airplane having an arrow-shaped wing and an elongated fuselage extending approximately equally forward and rearward of the wing. The fuselage is configured for six passengers in a staggered two-abreast seating arrangement and for two pilots seated in tandem. A forebody section of the fuselage, which extends substantially forward of the wing, is of a specific geometric cross-sectional design, i.e., it is an egg-shaped cross section with opposite sidewalls sloping vertically inward in an upward direction. The sidewalls are only of a single curvature in a fore-and-aft direction, and this substantially flat surface has windows installed therein which have an optically flat surface in order that a minimum of visual distortion is produced due to thermal expansion during supersonic flight. Twin vertical stabilizers are spaced apart and each is mounted near a wing tip; and the stabilizers extend both vertically above and below the wing chord plane for functioning as wing tip end plates.

Abstract: An ultralight aircraft having a generally rectangular, swept-back, single-surface wing. The wing, which is formed by fabric mounted on exposed spars and ribs, has a reflex profile to provide pitch stability which is further augmented by horizontal stabilizers projecting rearwardly from the wing adjacent the tips. Roll and yaw control are provided by a pair of rudders pivotally mounted at each wing tip. The forward ends of the rudders pivot inwardly to alter the magnitude of the wing's lift. The rudders pivoted simultaneously act as spoilers and speed brakes controlling the rate of descent. Pivoting one of the rudders individually moves the center of lift for one wing inwardly and increases the drag of that wing to roll the aircraft into that wing. The rudders tilt upwardly and outwardly in a dihedral configuration to provide roll stability. Stationary end plates mounted at each wing tip adjacent the rudders provide yaw stability.

Abstract: A system for deterring subsonic airplane stall-spin entry wherein a highly swept wing tip mounted lifting surface panel 18 (FIGS. 1-3) is attached to the tip of a main wing panel 14 and provides a stabilizing vortex lift to the aircraft at an angle of attack slightly greater than the normal angle of attack used in climbing flight. This vortex lift enhances roll damping at high angles of attack and serves to prevent airplane stall-spin entry. FIG. 4 shows an alternate form of the invention wherein the wing tip mounted lifting surface panel 48 is provided with a forward highly swept leading edge. For sharp leading edges a leading edge sweep for the wing tip mounted lifting surfaces is approximately forty-five degrees while, for blunt leading edge surfaces, a greater degree of sweep is employed to generate the vortex lift.

Abstract: A wingsail arrangement comprises a thrust wing having an upright leading airfoil having a leading edge and a trailing edge and an upright trailing airfoil having a leading edge and a trailing edge. The leading edge of the trailing airfoil is positioned closely behind the trailing edge of the leading airfoil. The trailing airfoil is mounted for pivoting movement about an upright axis relative to the leading airfoil from an aligned position in which the trailing airfoil is aligned with the leading airfoil to positions to each side of and angularly displaced from that aligned position. A slat has a leading edge and a trailing edge and is pivoted at its leading edge to the trailing edge of the leading airfoil and connected to the leading edge of the trailing airfoil by at least one cable so as to be moved in response to pivoting movement of the trailing airfoil to form a linear nozzle when the trailing airfoil is angularly displaced from the aligned position.

Abstract: This invention relates to an aircraft having three lift surfaces, and precisely a main wing lift surface located in an intermediate position of the aircraft and two less extended lift surfaces positioned, respectively, in a position ahead of the main wing surface and astern thereof.

Abstract: Auxiliary winglets or control surfaces for aircraft wings are tiltable ab an axis extending in the flight direction and about an axis extending substantially perpendicularly to the flight direction. The auxiliary wing tips have a configuration which assure a wing surface continuity, especially when the tips are in their normal wing extending position, but also in any other position of the winglets. Additionally, at least the leading auxiliary winglets are located upstream of the elastic wing axis, as viewed in the flight direction and they have a forward sweep or negative sweepback. The combination of these features permits a simultaneous reduction of induced drag and of stress caused by wind gusts, and for increasing the effectiveness of the wing's ailerons. Thus, these auxiliary winglets have three advantages simultaneously.

Abstract: This invention relates to a transverse driving body, particularly an aircraft wing, the wing comprising a wing tip extending basic parts of the wing in the span direction for the purpose of increasing the aspect ratio, the wing tip being of triangular design with a sweptback leading edge, and the profile camber of each of the wing tip increasing at least over a portion of the extension thereof from a basic wing part to the wing tip.

Abstract: A high altitude, ultra lightweight aircraft has broad area relatively flat wings, and is provided with solar cells on its upper wing surfaces, and long wavelength, infrared responsive cells on its lower wing and fuselage surfaces, to provide enough power to maintain the aircraft aloft at high altitudes indefinitely. The aircraft is intended to fly at altitudes of about 60,000 feet to 110,000 feet, at speeds in the vicinity of 70 to 200 miles per hour. A battery or fuel cell and electrical system is provided to store excess electrical power and to supply electrical power when needed. A large, low speed, pusher propellor is driven by an electrical motor. The aircraft may be launched with an opaque balloon, which not only raises the aircraft to the desired elevation but also conceals it.

Abstract: An airplane having a number of airfoils including a delta nose wing, a winglet, a midspan wing, a V-tail delta wing without an upswept fuselage, a vertical tail and upper body stabilizer. These airfoils are coupled with a system of four jet engines and an aft center of gravity. Full control of the airplane is possible under high maneuverability conditions, extremely high accelerations and at large angles of attack. The delta nose wing creates swirling vortices that contribute substantially to the lift of the nose section. The winglet, an extension of the delta nose wing, allows the turbulent wake from the leading edge of the delta nose wing to flow over its upper surface to create additional lift while the midspan wing causes the turbulent flow over its upper surface to form a turbulent wake at its leading edge. The V-tail delta wing with a V-shaped underside and blunt leading edge gives additional lift and control to the airplane.

Abstract: This invention relates to aircraft designs with substantial trim drag reduction while maintaining commercially feasible low parasitic and induced drag. The stable or control configured aircraft utilizes controllable winglets to generate pitching, yawing, and rolling moments in flying wing or tailless airframe configurations which are preferably of a swept forward style.

Abstract: This invention relates to a tandem or multi-winged aircraft wherein a primary wing system is so designed and equipped that it is capable of being actuated in a manner to bring about a shift in the neutral point of the craft relative to its center of gravity and wherein a secondary wing system located ahead of the primary one and movable fore and aft relative to the latter is deployed and angled during its excursion so as to effectively counteract the neutral point shift that would be brought about by deploying the primary wing system alone thereby maintaining the neutral point at approximately its former location in at least both the cruise mode as well as the high-lift mode preferred for landing and take-off.

Abstract: A rotor having airfoil section shaped blades is set into a fluid stream. Over a connection or transmission means a propeller is connected to the rotor. The fluid stream whereinto the rotor is set gives airflow energy to the rotor and revolves the rotor. The propeller is driven by the rotor over the connection or transmission means. Since the propeller is revolved by the rotor in the fluid stream, the propeller provides a thrust. The thrust may be used to lift a weight or to drive a member. A suitable application of the arrangement is, for example, to transform a multibladed helicopter into a gliding craft which descends under a gliding angle towards the surface of the earth when the helicopter has a complete engine failure. Auto-rotation accidents can thereby be prevented. The device is also applicable to drive a vehicle or to lift a weight. Variable means can be applied to obtain variable thrusts in flying craft to improve their efficiencies or change from one flight system to another flight system.

Abstract: A free flyable structure includes a wing formation (2) including an inflatable container of such form that when it is inflated the container (2) has an aerofoil shaped cross-section whereby relative displacement between the container and surrounding air enables free flight conditions. A substantially rigid means (19) carries the pay load from the wing formation (2). Flight path control of the flyable structure includes producing relative displacement between the load and wing formation. Additional flight path controls may be used. A canard wing assembly (82) is suggested. The structure is power driven and in the disclosure a power unit (85) having a propeller (86) is proposed.

Abstract: An aircraft intended to fly at supersonic Mach mnumbers is disclosed. The aircraft utilizes a double parasol wing arrangement, with a power plant nacelle located under the wing on each side of the fuselage. Each nacelle is located at the focus of a reflection parabola formed by the undersurface of each wing. In flight the shock wave pressure field created by the nacelles is reflected and redirected by the parabolic wing surface and thereby transformed into beneficial lift. The separation distance between each wing and its respective nacelle is arranged to maximize multiple reflections to thereby further enhance the lift created.

Abstract: An airplane airframe having wings connected to the fuselage by spars of smaller cross section than the wings. Movable winglets may be provided at the outboard ends of the wings. The fuselage may be an airfoil shaped lifting body structure with longitudinal splines at its edges. The splines may be movable in flight, and may be provided with flaps which are also movable in flight so that the splines can be readjusted to alter the aerodynamic characteristics of the airframe during flight. The undersurface of the fuselage may include cambers symmetrical about the center plane of the fuselage.

Abstract: The invention relates to an aircraft provided on either side of its fuselage with at least one lift structure constituted by at least two wings whose distal ends are connected either to each other or to at least one wing element, each structure forming in front elevation of said fuselage a closed polygon, and comprising an upper wing and a lower wing, the zone of attachment of the latter on the fuselage possibly being offset in the direction of the streamline flow with respect to the zone of attachment of the upper wing. According to the invention, each of the wings is made so that the values of the moment of inertia and of the lift, both varying as a function of the longitudinal distance, each take a maximum value at a zone of the wing other than the root. The invention is more particularly applicable to aircraft with multiple wing elements.

Abstract: An airfoil used in a ruddevator assembly for controlling movement of an aircraft refueling boom, where there are two airfoils (i.e. ruddevators) mounted to the boom, each at a dihedral angle of about 42.degree.. Each airfoil has an outboard section, which is an advanced technology cambered airfoil for high lift at transonic speeds, with a raked wing tip. The inboard portion of the airfoil has a forwardly extending strake-like member having a sharp leading edge which in planform comprises three sections. There is a curved forward edge section and two rearwardly extending edge sections, which in operation are positioned at high sweep angles. The side edge portions of the strake-like member create vortices which travel over the inboard portion of the airfoil to augment lift over a wide range of surface deflection of the airfoil (i.e., angle of attack).

Abstract: A gliding ring toy comprised of an annular airfoil angled in order to compensate for air downwash effects and to balance the aerodynamic lift, fore and aft, in gliding flight.

Abstract: Aircraft wing fatigue life and weight are strongly influenced by maximum wing root bending moment. The object of the invention is to augment the wing root bending moment relief that can be provided by the deflection of aircraft ailerons (12) in the conventional manner, while reducing or eliminating aileron induced wing torsional loading. To accomplish this, a movable aerodynamic control surface (14) is mounted on the outboard side of a contoured boom (13) situated at each wingtip. The exact size and location of the control surfaces (14) are determined by the particular aircraft application. Control surface size is a function of the aircraft aileron size, and each control surface (14) is located ahead of the elastic axis (10') of the wing (10). In addition to providing load alleviation, asymmetric deflection of the wingtip control surfaces (14) creates an aircraft rolling moment that adds to that produced by aileron deflection.

Abstract: A sound reducing combined low mid-wing and horizontal stabilizer airplane with near longitudinal center line thrust twin engines having intensified aileron, elevator and rudder control. Small jet engines rigidly attached to the ailerons intensify attitude control for low speed manuevers.

Abstract: Solar energy is focused by a paraboloidally curved, specularly reflective foil inside the wing of an aircraft having a transparent upper surface in whose rudder structure is disposed the radiation receiver. This particular reflector offers very low resistance to ambient wind forces.

Abstract: A design system for aircraft that allows wings of various different planforms to be mounted interchangeably on a common fuselage. Each of the wings has wing semi-spans joined by a center section torque box that mounts the wing in a cut-out in the aircraft fuselage. The torque box has a quadrilateral structure including front and rear main center section spars. These center section spars have their ends connected to the front and rear main spars of the semi-spans to transmit wing loads into the fuselage. The length of the main center section spars are designed in accordance with the invention such that they can connect with the main spars of the wing semi-spans to position the quarter chord of the wing properly with respect to the center of gravity of the aircraft irrespective of the wing planform. Thus, aft-swept, forward-swept, or straight wings can be routinely interchanged on a common fuselage without effecting the positive static longitudinal stability of the aircraft.

Abstract: A cruciform wing structure for a solar powered aircraft is disclosed. Solar cells 28 are mounted on horizontal wing surfaces 20, 22. Wing surfaces 24, 26 with spanwise axis perpendicular to surfaces 20, 22 maintain these surfaces normal to the sun's rays by allowing aircraft to be flown in a controlled pattern at a large bank angle.The solar airplane may be of conventional design with respect to fuselage, propeller and tail, or may be constructed around a core 70 and driven by propeller mechanisms 75, 76, 77, and 78 attached near the tips of the airfoils.

Abstract: A lightweight, man carrying aircraft including a skeletal fuselage assembly in combination with a primary arc-shaped lifting airfoil having variable camber, incidence angle, and pitching moment and a secondary stabilizing airfoil of a tubular, ring-like configuration. The arc-shaped primary airfoil is superior to traditional low speed airfoil forms due to its high aerodynamic efficiency, inherent design simplicity and strength. The ring-tail assembly, offering marginal aerodynamic lift, contributes significantly to the in-flight stability and safety of the aircraft. Both airfoil members are independently controllable and constructed of a fabric or like skin material which is fitted over a wing assembly and tensioned into an operable airfoil form by the aerodynamic forces of the air during flight. Typically, the wing assemblies are supported and maintained by a lightweight, tubular fuselage structure to which is affixed the propulsion system, control mechanisms and ground support assemblies.

Abstract: A wing structure for an aircraft designed for both STOL and supersonic flight conditions includes a biplanar wing arrangement in which the lower wing section is staggered behind the upper wing section and the lower wing section is designed for both translational and rotational displacements relative to the upper wing section. For short takeoff and landing capabilities, the lower wing section is rotated and translated relative to the upper wing section so that the leading edge of the lower wing section is adjacent to the trailing edge of the upper wing section. For high speed supersonic flight, the lower wing section is adjacent to the trailing edge of the upper wing section. For high speed supersonic flight, the lower wing section is rotated and translated relative to the upper wing section so that the wing sections are substantially parallel.

Abstract: A tandem wing aircraft having two wings of similar area wherein a lower first wing is located at the forward end of the fuselage attached directly to fuselage structure. A second higher wing is located at the aft end of the fuselage but is aerodynamically separated from the fuselage structure by strut structure. Pitch control is achieved by increasing or decreasing the lift on either wing; but downward acting load is not required. The two wings are preferably vertically separated by 25% to 50% of the span of the wings. Control redundancy for flight safety is achieved because of availability and location of control surfaces. Higher aspect ratio wings can be used because of inherently reduced bending moments on the wing; and overall aircraft gross weight is reduced due to structural and aerodynamic efficiency.

Abstract: An aircraft having, for example, a tailplane (4, 5) at least part of which is movable with reference to a fuselage (1) to effect control requires the control effect to be enhanced in a certain control position. Accordingly, fixed vanes (8, 9) are provided on the fuselage forward of the tailplane to form a substantially continuous leading edge root extension only when the tailplane is in a given control position.

Abstract: An aircraft having a fuselage and a pair of first airfoils in the form of wings extending outwardly from the vertical tail and a pair of second airfoils in the form of wings extending outwardly from the forward portion of the fuselage at a lower elevation than the first airfoils. The second wings extend rearwardly having a positive dihedral so that the tip ends of the second airfoil are located in close proximity to and may overlap the tip ends of the first wings. The pairs of wings along with the fuselage present a double triangle or diamond shape in both front elevational view and top plan view. A winglet structurally connects the tip ends of the corresponding first wings and second wings, and these winglets have airfoil surfaces which extend vertically substantially beyond the tip ends of the first and second wings in order to minimize the effects of induced drag and also to augment directional stability of the aircraft.

Abstract: An aircraft, either rigid-wing or a collapsible hang-glider, is provided which is a bi-plane of apparent annular-wing construction in plan view, but the wing tips of an anhedral foreplane are separated from and above the wing tips of a dihedral aftplane. In a hang-glider construction the wing tips of the foreplane may be supported above the wing tips of the aftplane by struts, the trailing edges of the foreplane wing tips being supported by the struts above the leading edges of the aftplane wings. Also in the hang-glider, the geometry of the fore and aftplanes can be varied by moving their points of connection to the keel therealong.

Abstract: Improvement to a fixed-wing airborne vehicle which results in significant delay drag rise well into the transonic regime. The fundamental features of the improvement include: fixedly skewing the wings at 45 degrees; shaping the outboard ends of the wing tips so that the trailing edge of the forwardly disposed wing is swept forwardly and the leading edge is straight relative to the trailing edge, and so that the leading edge of the rearwardly disposed wing is swept rearwardly and the trailing edge is straight relative to the leading edge; and, blending the leading and the trailing edges of the planform, so as to increase the local chord and control the longitudinal position of the maximum thickness in the root area (i.e., at the interface of the inboard tip end of each wing with the fuselage).

Abstract: A glider formed from a multi-sided tube open at its ends is disclosed. The body and lifting surfaces of the glider comprise a multi-sided tube including a top wall of planar configuration; a pair of opposed upper side walls of planar configuration integral with the top wall extending downward and outward a distance; a pair of opposed vertical side walls of planar configuration integral with the upper side walls; a pair of opposed lower side walls of planar configuration integral with the side walls extending downward and inward to a point inward of a vertical extension of the top wall and upper side wall intersections; a bottom wall extending between lower end walls and integral therewith enclosing the structure. The bottom wall includes a pair of upward extending planar sections meeting at a mid point between lower end walls to form a ridge.

Abstract: An upper and lower member are joined together near the tip. They are hinged near the front and back on the top member. This allows the wings to be opened for high speed, when cruising, and to be closed for take off and landing at a low speed. The exact size and shape of the moveable sections will be dictated by the size of the wing and the distance between the upper and lower wings where they join the fuselage. When the wing reaches a certain speed the drag forces will become more demanding creating a faster movement through the air passages causing a suction at the front of the wings. The ram affect on the front and the suction affect in the back will accomplish two things. It will dissipate the drag that tries to build up at the trailing edge and eliminate the pile up of air at the leading edges of the wing. The air passageways between the wings, when in the open position, will have to be the same size all of the way through the passageways.

Abstract: An aircraft engine is mounted above and spaced apart from the upper side of a wing by means of a supplemental wing being above and ahead of the main wing. Particular parameters for this mounting arrangement are given so that the jet clears the upper wing surface but accelerates the flow there above. The omission of a pylon on the wing is another drag reducing feature.

Abstract: A tandem wing aircraft is provided having two independent spaced apart fuselages and two wings of similar area, a lower forward wing and a higher aft wing. The lower forward wing is attached to the forward region of each of the spaced apart fuselages; the higher aft wing is aerodynamically spaced apart from and located above the aft region of the spaced apart fuselages. An aft strut member is disposed between the aft wing and each of the fuselages; each aft strut member has a length sufficient to cause the wing tips of the lower forward wing and the upper aft wing to be vertically spaced apart by a distance of at least 25% of the span of either of the wings.

Abstract: A model aircraft of the glider or motor-driven type can be provided with one or more different types of wing according to requirements by interposition between the respective pairs of wings and the fuselage of intermediate members adapted on the one hand to the fuselage of the aeroplane and on the other hand to the associated wings and ensuring an aerodynamically smooth transition from the fuselage to the wing. The fuselage can have a pair of lateral surfaces adapted in accordance with the cross-section of one specific wing construction so that intermediate members are only required if it is desired to employ wings differing from those having such a cross-section.

Abstract: Fore mounted aft swept and aft mounted forward swept wings extend from either side of a lifting body fuselage. Each lateral pair of the wings is joined at the tops by a wing tip vortex translating device to induce translation of the tip generated vortices along the trailing edge of the aft wings. End plates extend rearwardly from the maximum chord thickness of the fuselage to increase the effective lift of the fuselage. An elevator, mounted intermediate the rear top of the end plates, provides pitch control and structurally augments the wing root and fuselage junction of the aft mounted wings. A power plant disposed at the rear of the fuselage provides thrust and also dissipates, as useful thrust, the wing tip vortices translated from the tips to the power plant along the trailing edges of the aft wings.

Abstract: An aircraft having a fuselage provided with wing panels in staggered positions along the fuselage such that control surfaces of the forward wing panel are substantially closer to the center of gravity than are the control surfaces of the rearward wing panel. This arrangement results in reduced drag effects at transonic speeds, and provides a novel way of obtaining precise control of the aircraft position by using the control surfaces for vertical translation with minimum pitching moments.

Abstract: The vehicle is constructed from a flat disc recessed in a slot in a thin, pencil-like fuselage having aft and front propulsion engines and mounted for rotating about the center of the disc and about an axis extending transversely to the disc and to the direction of extension of the fuselage.

Abstract: An airplane having a fuselage, a high wing projecting from the upper part of the fuselage to either side first at an upward angle and then slightly downwardly whereby said wing presents a gull wing frontal contour, fins to either side and forward of and at the bottom of the fuselage with ducted fans nested to the wing under the high point of the gull wing frontal contour to be unobstructed thereby.

Abstract: This invention relates to an improvement in an airplane having two superposedly-arranged upper and lower sweptback wings which together form a closed frame, with reference to a front view thereof, the improvement comprising a rhombic shape of the frame with the upper wing having a negative V-position and the lower wing having a positive V-position, both of the wings being rearwardly sweptback, and the upper wing being more markedly sweptback than the lower wing, and at least the leading edge of the upper wing being positioned forward of the lower wing.

Abstract: A staggered channel aircraft having a forward pair of wings and a rearward pair of wings. The forward pair of wings are substantially horizontal and are swept backward from the fuselage to join at their tips the pair of rearward wings. The rearward wings are sloping and are swept backward from their tips to join the fuselage in a substantially triangular-like configuration.

Abstract: An aircraft has two concentric wings of substantially equal diameters, the wings being connected to each other and stayed by an elongated central corridor which is located beneath a central engine duct disposed in the plane of the upper wing.

Abstract: A short coupled airplane with variable wing lift comprising a fuselage that is free of the conventional tail assembly and has a wing structure comprising a plurality of short span wing segments spaced apart longitudinally of the fuselage with the forwardmost wing section being located forwardly of and above the level of the aircraft center of gravity, and the rearwardmost wing section being located rearwardly of, and below the level of the aircraft center of gravity. The wing sections at their projecting ends on either side of the airplane are connected by vertical airfoils each equipped with a rudder. The wing sections along their trailing edges are each equipped, on either side of the fuselage, with full span, vertically swingable members that combine the functions of flaps and elevators (and are thus called eleflaps). The eleflaps and rudders are respectively moved in unison to elevate, lower, and steer the aircraft.

Abstract: Disclosed is a staggered channel wing-type aircraft comprising a reverse staggard lower and upper wing which relates to aircraft of the type generally described as a short takeoff and landing vehicle (STOL) and more particularly to an improved version thereof having superior low speed handling characteristics in both takeoff and landing and an economical high speed cruise configuration. Also having an improved gliding characteristic and easy storage because the wingspan is reduced to a minimum but keeping still rather large wing area.

Abstract: An aircraft of the Canard type in which a first airfoil is attached to an aft fin portion of the fuselage at a higher elevation than a second airfoil which is attached to the fore portion of the fuselage. The second airfoil extends outwardly and rearwardly to meet the first airfoil whereby a triangular configuration is formed in plan view and in front elevation view. The airfoils may be flexible; simple cable controls may be provided to control the aircraft so that even inexperienced pilots can easily operate the aircraft. The triangular configuration ensures a lightweight and inexpensive yet rugged and strong aircraft. The aircraft may also include a split rudder and may be hinged for folding to facilitate storage and transportation.

Abstract: A dual-function aircraft is disclosed having a fuselage shaped like an airfoil, a series of airfoils of shorter chord length arranged in tandem and disposed below the fuselage to provide additional aerodynamic lift, and a downwardly movable rear wall and a pivoted forward airfoil which forms a plenum chamber under the fuselage and produce a cushion of air during the ground mode. Transition from the ground effect mode to the flight mode is made in flight by simultaneously lowering the tandem of airfoils, lifting the rear wall and altering the angle of attack of the forward airfoil.