Shape of wings (B64C3/10)

B64C3/10                     Shape of wings(59)

Aircraft configuration having spin resistance // 2640669
FIELD: aviation.SUBSTANCE: aircraft comprising of a fuselage, configuration with a T-tail assembly and a high wing, having a leading edge connected to the upper part of the fuselage, where the high wing comprises of the first region adjacent to the fuselage and the second region adjacent to the wing tip, with the first region being adjacent to the second region, and where, at large angles of attack, the stall element and a separate air flow, associated with it, are isolated by discontinuity at the leading edge of the wing within the first region and the air flow below the T-tail assembly in such a way as to stay away from the flight controls located within the second region and controls relating to the T-tail assembly. The wing of the aircraft contains the first region near the root of the wing and the second region near the wing tip. The first region and the second region adjoin each other along a continuous boundary. Discontinuity of the leading edge is done to form at high angles of attack aerodynamic partitions along the continuous boundary, isolating the stall element and separate air flow, associated with it, within the first region and air flow below T-tail assembly. The aircraft is characterized by the use of a wing.EFFECT: increase of spin resistance by isolating the stall element.22 cl, 6 dwg

System and method for minimizing wave resistance by two-sided asymmetrical structure // 2639354
FIELD: aviation.SUBSTANCE: aerial vehicle with a two-sided asymmetrical structure comprises a casing with a longitudinal axis and asymmetrically elongated engine nacelles. The method of minimizing wave resistance of aerial vehicle flight comprises the stage of providing by the air vehicle housing having a longitudinal axis oriented generally parallel to the forward flight direction and the stage of displacing the engine nacelles longitudinally by asymmetrically extending the engine nacelles of the mentioned air vehicle.EFFECT: minimization of wave resistance.13 cl, 10 dwg

Aircraft wing // 2601093
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering. Wing is made in form of variable cross-section tray converging from aircraft nose to tail. Wing consists of bearing frame, top and bottom skins, two lateral sections and two ailerons. Inside tray air flow divider is installed, on which four baffles are fixed, which lead part of air flow from tray through openings in side sections, thus creating additional negative pressure inside tray.EFFECT: invention is focused on increasing the lifting force.1 cl, 4 dwg

Aircraft wing // 2600413
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering. Wing consists of a center wing section, a cantilever and required functional systems. Wing is made with elongation λ= 7-11, taper η= 3-4.5, sweep to X=35o. Wing includes supercritical wing sections. Wing leading edge on top view is rectilinear and does not have front collar. Trailing edge is made with strake. Radii value of wing sections leading edges related to local chord is rh ≤ 0.7 %, middle line of wing profiles shaped has a concaved section in the range of profile leading edge and up to 60% of the chord apart from end sections of the wing and bent in the tail part of the profile. Shape of the upper surface of the wing sections is characterized by prolonged section of the lesser curvature in the section of 30-60 % of the profile chord, and the position of maximum ordinate of the upper surface near the 40 % of the profile chord. Shape of the bottom surface of the profile is made with a section of strong curvature (trim) in the tail part of the profile.EFFECT: invention is aimed at increase in aerodynamics and fuel efficiency at flight speeds of Mcruising= 0,84-0,86.1 cl, 5 dwg

Aircraft // 2597742
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft modelling. Aircraft comprises fuselage with cockpit, wings with ailerons and flaps, tail unit, engine and undercarriage. Each wing on portion of attachment to fuselage is divided into two parts, one of which is back-swept, and other is forward-swept.EFFECT: invention is aimed at improving compactness and reducing landing run.1 cl, 1 dwg

Device for improvement of aircraft lifting properties // 2556745
FIELD: aviation.SUBSTANCE: device for improvement of aircraft (A) lifting properties is a vortex generator designed as a lining pad installed on internal section of a slat. The device is designed as a profiled section of the slat continued to the wing fillet with a hull, it is formed along two sections of the wing leading edge: the first section - the internal plane of the slat; the second section - crossing of the part of the wing fillet leading edge with the hull and the plane parallel to the aircraft symmetry plane. The section is taken so that it continues the internal plane of the slat along the wing span without break. The device span size cover about 75% of the distance between the internal plane of the slat and the aircraft hull. The device has a cut in the lower part. The cut has a shape of semi-parabola limited by the plane parallel to the plane of an internal end face of the device, the cut is formed by crossing of internal and external surfaces of the device. The cut height is 34% from the dimensional height of the device.EFFECT: improvement of aircraft lifting properties at near-critical angles of attack.7 dwg

Aircraft wing // 2555079
FIELD: aircraft engineering.SUBSTANCE: wing is composed of a flute of variable cross-section converging from aircraft nose to tail. Wing structure consists of load-bearing carcass, top and bottom skins, two lateral sections and two ailerons. Short rods are arranged at and secured to bottom skin to kill airflow velocity.EFFECT: increased lift.4 dwg

Triangular wing of supersonic aircraft // 2550578
FIELD: aircraft engineering.SUBSTANCE: triangular wing of supersonic aircraft has a top and a central chord located in the symmetry plane of the wing, rectilinear leading edges, going off from the top, the rear edge located in the plane, perpendicular to the central chord, and a non-planar median surface limited by leading and rear edges. Non-planar median surface of the triangular wing is formed so that super-elliptic distribution of the local angle of attack along a wing span is provided.EFFECT: decrease of aerodynamic resistance at pre-set lifting capacity power in the supersonic range of speeds.4 dwg

Aircraft wing // 2540293
FIELD: aircraft engineering.SUBSTANCE: aircraft wing consists of centre-section and outer wing and features elongation λ=7-11, taper η=3-4.5, sweep χ=25-40° and includes supercritical wing sections. Wing leading edge is rectangular in top view. Wing trailing edge features strake while radii of wing section tips related to local chord rt≤0.8%. Shape of the sing section top surface features section of minor curvature making some 30-50% of profile cord and is defined by relationship Yt.s./Yt.s.max.≥0.75 and by position of maximum y-coordinate of top surface in the range of 35-45% of chord profile. Shape of the profile bottom surface features trim of the profile trailing part.EFFECT: better aerodynamics and fuel efficiency at high subsonic speeds.5 dwg

Aircraft wing // 2537348
FIELD: aircraft engineering.SUBSTANCE: aircraft wing comprises triangular body secured to fuselage and furnished with vertical oncoming airflow splitters arranged at body edge each having leading and trailing sections. Leading section is arranged ahead of body edge parallel about vertical plane extending along fuselage. One of trailing edges is attached to top airfoil and bent aside from fuselage. Another trailing section is secured to bottom airfoil and bent towards fuselage. Angle of the bend of splitter trailing section secured to top airfoil makes 5-15 degrees. Angle of the bend of splitter trailing section secured to bottom airfoil makes 5-15 degrees.EFFECT: increased lift.3 cl, 5 dwg

Aircraft wing tip // 2495787
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft wing tip has root profile with S-shape mid line and section of negative concavity of length making 20-70% of the chord. Tip curved and end profiles feature positive concavity. Wing tip has bulge at root section and bend in leading edge.EFFECT: better aerodynamics.7 dwg

Aircraft wing // 2494917
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Aircraft wing consists of center wing section and outer wing. Said wing features aspect ratio λ=9.6…10.5, taper η=3.5…4.0 and sweep χ=25…30°. Leading and trailing edges on top view are straight. Wing trailing edge is rounded at section of 30-50% of wing span. Magnitude of wing airfoil leading edges radii related to local chord equals rE≥0.,9%. Distribution of thickness on airfoil cross-sections features the position of maximum thickness at the section of 30-50% of airfoil chord increased to C70%>7% of tail airfoil thickness chord. Center line of wing airfoils has concave section extending from airfoil leading edge and to 60% of chord apart from wing trailing edges.EFFECT: higher lift.8 dwg

High-efficiency supersonic wing with laminar flow // 2494008
FIELD: transport.SUBSTANCE: transonic and supersonic wing with laminar flow comprises hybrid flat split flap connected with the wing and including flat flap deflected downward at the first angle, and split flap deflected at the second angle larger than the first one. Said wing may comprise buildup extending ahead of the wing inner spread, skewed wing tip, reverse fairing on joint between buildup or fuselage and wing leading edge, inner leading edge flap extending through at least 15% of wing span, and hybrid flat split flap arranged at training edge.EFFECT: decreased positive pressure gradient at flap top surface training edge.17 cl, 3 dwg

End airfoils with recesses and appropriate systems and methods // 2492111
FIELD: transport.SUBSTANCE: invention relates to end airfoils including surfaces with recesses and to method of rag reduction. Aircraft system comprises wing and end airfoil (winglet, end plates, Whitcomb endplate) connected with wing end outer section. End airfoil has first surface facing fuselage side and second surface directed outward. First surface comprises area with recess. Note here that the wing includes airfoil sections located from wing inner area to outer area. End airfoil is used with the wing that features no changes on common shapes of airfoil sections located nearby wing outer area.EFFECT: decreased influence of interferences caused by flows at wing-end airfoil transition, reduced drag.13 cl, 13 dwg

Wing tip configuration, in particular, that of aircraft wing // 2490171
FIELD: transport.SUBSTANCE: configuration of aircraft wing tip with wing section extending in wing span 1 and in width of said wing span from leading edge 8, 6, 10 to trailing edge 7. Said section is confined by comprises first skin 11 and second skin 12 with minor wing at wing end. Said minor wing 3 is flat and has transition area 2 located between wing 1 and minor wing 3. Said transition area 2 extends from joint 4 with wing 1 to joint 5 with minor wing 3. Curvature of local V-angle in transition area 2 increases in outboard direction from low lever or zero level nearby the joint 4 with wing.EFFECT: decreased inductive reactance at minimisation of interference at transition from wing to minor wing.15 cl, 4 dwg

Delta wing for supersonic aircraft // 2487050
FIELD: aircraft engineering.SUBSTANCE: delta wing has top and central chord arranged in wing mirror plane, straight leading edges extending from said top, and uneven mid surface. Said mid surface consists of two elements adjoining said mirror plane and feature elliptically taper shape bulged leeward and two elements adjoining leading edge and feature flat shape and are smoothly conjugated with elliptically taper elements along arms extending from wing top. Mid surface is expressed by mathematical relationship.EFFECT: lower drag in supersonic flight.4 dwg

Aircraft wing tip // 2481242
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Proposed wing tip has end plate with aerodynamic sweep of light elongation and sharp leading edge arranged at end plate end outer side. Aerodynamic surface trailing edge is aligned with end plate rear edge. Tip is located at end plate front edge, below rear edge while sweep make 60-85 degrees. There is lower vertical aerodynamic surface of small elongation coupled with end plate so that its leading edge coincides with leading edge of end plate aerodynamic surface. Angle between end plate aerodynamic surface and lower vertical aerodynamic surface makes 125-30 degrees.EFFECT: higher aerodynamic efficiency, decreased fuel consumption.3 dwg

Aircraft wing tip // 2481241
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. invention relates to aircraft engineering. Proposed wing tip has end plate with aerodynamic sweep of light elongation and sharp leading edge arranged at end plate end outer side. Tailing edge of extra aerofoil is aligned with rear edge of end plate while nose flap is located at leading edge of end plate under the level of tailing edge, sweep making 60-85 degrees. Proposed wing tip has end plate with aerodynamic sweep of light elongation and sharp leading edge arranged at end plate end outer side. Tailing edge of extra aerofoil is aligned with rear edge of end plate while nose flap is located at leading edge of end plate under the level of tailing edge, sweep making 60-85 degrees. Angle between end plate and aerofoil makes 175-180 degrees. Wing tip is arranged at 2 to 3 degrees to wing tip chord.EFFECT: higher aerodynamic efficiency, reduced fuel consumption.4 dwg

Integrated technology of operation and production of maksinio vehicles hybrid aircraft (versions), turboprop jet engine, wing (versions), method of generating lift and method of turboprop jet engine operation // 2460672
FIELD: transport.SUBSTANCE: version of every hybrid aircraft consists of fuselage, turboprop and wings. First version incorporates bearing devices arranged on both sides of fuselage and consisting of aircraft transverse wing root with engine fan ahead of front edge at fuselage nose and wings arranged there behind, several wings at top or bottom side, along fuselage. Second version incorporates top and bottom pairs of cantilever straight wings with spacing between pairs for gas-air flow from engine nozzles. Turboprop et engine incorporates shaped confuser and diffuser sections of propfan ring inner surface. Wing versions feature availability of bearing section and airfoil section. Methods comprises using said aircraft and engine.EFFECT: higher safety, lower costs.13 cl, 8 dwg

Aircraft mixed-mode aerorodynamic and space flight and method for its piloting // 2441815
FIELD: aeronautics.SUBSTANCE: invention relate to an aircraft with a mixed solution with aerodynamic and space flight and how it is flying. The aircraft includes a fuselage, wing, air-jet engines and rocket engines. The wing holds still, essentially straight and elongated in the lateral direction fuselage. Wingspan makes the length of the fuselage. Wing tanks and rocket fuel are located in the rear fuselage. In front of the fuselage, located cabin. The method of piloting an aircraft contains four phases of flight. The first stage of aerodynamic flight at subsonic speeds, corresponds to 0.5 M-O, 8 M, with the use of jet engines without air refueling. In the second stage of exit in outer space rocket engines are used after giving the command to change the tilt of the aircraft between the first stage and second stage. In the third stage of descent by planning mode to the fuselage, oriented substantially perpendicular to the trajectory. The fourth step is provided by aerodynamic flight and landing after bringing the aircraft into position on the merits in the direction of the trajectory between the third phase of flight and the fourth stage of the flight. EFFECT: reduced fuel consumption.14 cl, 3 dwg

ukhamedov's wing // 2412861
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering. Wing 1 comprises wing center section made up of shaped bearing disk 2 with front and rear edges along generatrix of bearing disk. Panels 3 are jointed with wing center section bearing disk 2 on its sides so that the shape of front and rear edges of said disk 2 are unchanged along said generatrix in plan. Wing panels 3 feature trapezoidal and sweep and/or rectangular aerodynamic shape. Wing 1 has aerodynamic extensions 4 made along wing lengthwise axis at wing front on both sides that feature triangular and ogival aerodynamic shape in plan.EFFECT: higher maneuverability.5 cl, 7 dwg

ethod and device to move in gases or fluids // 2412082
FIELD: transport.SUBSTANCE: invention relates to device intended for generation of propellant forces for vehicles. Proposed method is characterised by drag effects on wing front surface or screw front surface wherein ram inflow on plane periphery is turned and tangential flow is created on rear plane with speed smaller than that of ram flow. Flow on rear surface front edge is directed from the root to plane lateral edge and intersect it with flow swirled long lateral edge of the plane read surface for their interaction to create force oriented along the plane. Ram flow is used to stabilise boundary layer on the plane rear surface rear edge. In compliance with the first version, aircraft cuts in propellers. Peripheral plane of propeller blade accommodates the structure of profiles with its elements. Another version of aircraft comprises wings. Structure of profiles is located on wing plane periphery.EFFECT: higher efficiency of converting drive power into propellant power.7 cl, 4 dwg

Aircraft and its swept wing // 2398709
FIELD: transport.SUBSTANCE: set of invention relates to aircraft engineering. Aircraft comprises airframe, swept wing, tail unit and jet engine. Airframe is characterised by selection of coordinates of outer surface outline points. Swept wing comprises cantilever parts and wing center section defined by coordinates of the upper and lower outlines of aerodynamic profiles located in wing basic sections.EFFECT: reduced weight, higher comfort for passengers.6 cl, 27 dwg, 13 tbl

Supersonic aircraft (versions) // 2391254
FIELD: transport.SUBSTANCE: invention relates to long-range executive aircraft. Proposed aircraft comprises airframe, sweptback wing, vertical tail unit, running gear and power plant made up of engines, air intakes and nozzles. Airframe front has flatted nose cone smoothly aligned with cockpit and passenger cabin with circular sections. Wing root front edge is rounded and smoothly aligned with airframe. Wing root rear edge has a break. Vertical rudder integrated with horizontal tail unit is arranged on tip of vertical tail extension. Wing features crosswise V angle. Supersonic air intakes are arranged above wing top surface on both sides of airframe, while, ahead of air intakes, both wing and airframe are a bit contracted. Ahead of air intakes, there are perforated sections for intake of boundary layer. Supersonic air intakes comprise mechanism of controlled air cross flows from boundary layer discharge channel into channel feeding air into engine. Supersonic nozzle critical section is arranged above airframe top surface between two vertical tail fins. Flat nozzle has rotary top flap. Airframe tail section changes into flat surface to smoothly terminate in elevation rudder. Tail elevation rudder comprises mechanism of down-displacement in take-off-landing conditions. Reverse rotary panel is arranged ahead of elevation rudder above airframe top surface. Channels for reverse lower jets are arranged below said panel.EFFECT: minimised effects on ecology at high cruising speeds.14 cl, 5 dwg

Aircraft with low noise at take-off and landing // 2388651
FIELD: transport.SUBSTANCE: invention relates to aircraft with low noise at take-off and landing. Proposed aircraft comprises airframe, two wings arranged on both sides of airframe ant carrying engines, and tail unit. Vertical tale consists of at least two fins to make with airframe rear end a channel on airframe top. Airframe top accommodates at least one engine to make airflows created by it come into said channel and to engine rear noise is shut off by said channel in lateral and bottom directions. Sweep forward wings have their butt joints arranged behind airframe, nearby engine air intake, to shut off front noise in lateral and bottom directions by wings.EFFECT: aircraft reduced noise.2 dwg

Airplane, fast-speed arrow wing and fuel system // 2384472
FIELD: air transport.SUBSTANCE: airplane includes nose, front, central, rear and tail sections and fast-speed arrow wing with jet engines. Fast-speed arrow wing is characterised by change of maximum relative profile thickness, geometric twist angle, angle of lateral V wing under wing semispan and middle surface curvature both along semispan and profile chord. Fuel system includes reservoir of the airplane central section and reservoirs in outer wings near the central section at middle part and at the periphery. The central section is equipped with expandable walls. Fuel system provides initial use of fuel from central section reservoir, then from fuel tanks of outer wings located near central section and then from tanks at the periphery of outer wings, and after all the others - from the middle part of the wing by fuel transfer between tanks.EFFECT: improvement of aerodynamic characteristics for planes with different weight and hull length.22 cl, 54 dwg

Short-, mid-range main line aircraft // 2384463
FIELD: air transport.SUBSTANCE: aircraft is made in proportion L/C=1/1, where L - hull length with diametre df≥4.18 m, C - wing span, which is formed with supercritical sections and made with the following parametres: aspect ratio λ≥1.5, sweep in line 1/4 chord χ≥26.5°, setting angle α0=3°, local transverse wing V angle ψ=5.37°, taper aspect η=3.928 and mean aerodynamic chord ba=3.479 m.EFFECT: decreasing fuel consumption.5 dwg, 3 tbl

Aircraft wing tip // 2378154
FIELD: aircraft engineering.SUBSTANCE: invention relates to aircraft engineering. Aircraft wing tip features sweepback of leading edge with wing lower surface formed by smooth continuation of wing lower surface generatrix. Leading edge of wing tip end is made straight and sharp with sweepback of 70° to 85° at the point of intersection of nonlinear leading edge of wing tip with continuation of the line of maximum wing thickness. Profiles chords parallel to wing symmetry plane form lower surface. Transition from wing with profile blunt nose to sharp one of wing tip rear end, over lower surface, is made smooth. Upper surface of wing tip is formed by continuation of wing upper surface to smoothly terminate at sharp leading edge.EFFECT: improved aerodynamic properties.8 dwg

Straight high-speed wing // 2314971
FIELD: aeronautical engineering.SUBSTANCE: proposed straight high-speed wing is made at aspect ratio λ=9-11 and taper ratio η=3.5-4.2. Wing is formed as integral spatial system on base of straight wing having zero sweep by rear spar and leading-edge wing extension with integral base profile; profiles from root one to tip one have maximum negative concavity f=0.015-0.02 in tail sections of profile at position in span changing from X=0.5 for root profile to X=0.9 for tip profile. Wing thickness ratio ranges from 0.165 to 0.13. Profile twist angles φi change from +1.5 to -1.5 degrees according to linear law; angles of inclination of upper surface at trailing edge is δ£6-7 degrees.EFFECT: enhanced lift and speed qualities; reduction of mass; increase of wing net volume.8 dwg

Straight high-speed wing // 2314970
FIELD: aeronautical engineering.SUBSTANCE: proposed wing is formed as integral spatial system on base of rear spar at zero sweep and integral base profile which is modified in span in such way that root profile is mounted at angle of plus 1.0-1.5 degrees ensuring maximum of magnitudes Mk* and Mzo at moderate magnitudes Cymax and tip profile is mounted at angle of minus 1.5-2 degrees ensuring maximum magnitude Cymax. Profiles have maximum negative concavity f=0.15-0.2 in tail sections of profile whose position changes in span from X=0.6 for root profile to X=0.9 for tip profile. Wing thickness ratio changes from 0.16 to 0.13.EFFECT: enhanced lift and speed qualities.8 dwg

Flying vehicle wing and under-wing pylon // 2312791
FIELD: aeronautical engineering.SUBSTANCE: proposed wing has skin and under-wing pylons. Skin is made from smoothly engageable parts at positive and negative curvature of median surface. At change from side section of wing to end section, profiles of sections are made at change of angle of geometric twist of sections, maximum thickness ratio of profiles, dihedral angle of wing and relative nose radius. Magnitude of dihedral angle of wing along its semispan has maximum between side section and plane of installation of engine. Under-wing pylon has inner side wall directed to fuselage and outer side wall which are flat in larger part of first half of pylon; they are located symmetrically relative to plane of installation of engine. Side walls of pylon are bent towards fuselage in its tail section. Maximum deflection of inner side wall from plane of installation of engine at change from lower sections of pylon to upper ones reduces and its position smoothly shifts in direction opposite to flight.EFFECT: improved aerodynamic characteristics.15 cl, 35 dwg

High-speed wing // 2311315
FIELD: aviation.SUBSTANCE: proposed high-speed swept wing consists of center-wing section and outer-wing panel. Wing is formed as single spatial system on base of non-planar middle surface having S-shaped profile of center lines at negative concavity in tail sections at X>0.7-0.8 and positive concavity f=0.015-0.02 at X> 0-0.7. At change from side sections in span, negative concavity disappears gradually and positions of maximum positive concavity smoothly shift backward by chord from magnitude X=0.3 at side to magnitude X=0.5 in end sections. Aspect ratio of wing λ=9-11, taper ratio η=3.5-4.2 and leading-edge sweep angle is up to Xl.ed.=35o. Upper generatrices of profiles are so made that at rated conditions, maximum rarefaction does not exceed permissible limits Cmax.perm.. Thickness ratio of profiles is formed according to two laws: from leading edge up to X=0.3, at range of C=0-8% and from X=0.3 to the trailing edge at range C=0-17%; maximum thicknesses of profiles are found at X=0.56-0.66.EFFECT: increased flying speed.8 dwg

Aircraft // 2283261
FIELD: aviation.SUBSTANCE: proposed aircraft has fuselage, engines, landing gear and control cabin. Aircraft is provided with trough-shaped wing, vertical fins with rudders, stabilizer and elevons. Wing is mounted on fuselage which has no tail section. Vertical fins with rudders are mounted underneath the wing. Stabilizer and elevons are mounted on trailing edge of wing.EFFECT: reduced mass; reduced drag; improved aerodynamic properties.3 dwg

Flying vehicle wing // 2272745
FIELD: aeronautical engineering; lifting surfaces of various flying vehicles.SUBSTANCE: proposed flying vehicle wing has additional aerodynamic surface in form of plate mounted on it. Plane is triangular in plan and its end edge is sharp and is parallel to wing axis of symmetry. Plate is located at distance from tip chord equal to 0.05-0.1 of wing span and its length is equal to 0.1-0.15 of wing chord at point of location of end edge of additional aerodynamic surface. Trailing edge of additional aerodynamic surface is rectilinear in form. Its upper surface is formed by extension of upper surface of wing and lower surface is smoothly conjugated with lower profile of wing tail section.EFFECT: extended field of application; improved aerodynamic properties.10 dwg

Flying vehicle wing // 2266233
FIELD: aviation.SUBSTANCE: proposed swept-forward wing has tips of the same sweep. Tips are turned backward in flow to sweep-back position at retained parameters of swept wing and parallelism of tip chord of wing plane of symmetry.EFFECT: reduction of aeroelastic deformation and avoidance of divergence at high velocity heads on metal swept-forward wing.6 dwg

Flying vehicle lifting surface tip // 2264950
FIELD: aeronautical engineering; lifting surfaces of various-purpose flying vehicle.SUBSTANCE: proposed tip has swept aerodynamic surface whose lower plane is formed by smooth extension of generatrices of wing lower surface. Nose of root chord of end aerodynamic surface is located on lower contour of wing end profile at point of intersection with line of maximum thicknesses. Leading edge of end aerodynamic surface is sharp in contour and is located on one line with wing trailing edge; upper plane of end aerodynamic surface is made with smooth change at point of connection with wing. End aerodynamic surface has low aspect ratio and its sweep ranges from 60 to 85°.EFFECT: improved aerodynamic property at high subsonic flight speeds.10 dwg

Flying vehicle wing tip // 2264328
FIELD: aeronautical engineering; various flying vehicles.SUBSTANCE: proposed tip has end plate and is provided with additional swept aerodynamic surface of low aspect ratio with sharp leading edge mounted on the outside of end plate. Trailing edge of additional aerodynamic surface is combined with trailing edge of end plate. Nose is located on leading edge of end plate below level of trailing edge; sweep ranges from 60° to 85°.EFFECT: enhanced aerodynamic efficiency at high subsonic speeds.15 dwg

Flying vehicle wing // 2264327
FIELD: aviation.SUBSTANCE: proposed flying vehicle wing is sweep-back wing with tips of the same sweep. Tips are directed forward against flow in sweep-forward position Xt.l.ed.<0 at retained geometric parameters of wing: wing area, span, aspect ratio and parallelism of tip chord of wing plane of symmetry, where Xt.l.ed. is sweep angle over leading edge of wing tips.EFFECT: increased carrying properties of wing sweep over entire range of velocity head; enhanced efficiency of ailerons at moderate and high velocity heads.9 dwg

Aircraft wing // 2254266
FIELD: aviation.SUBSTANCE: proposed aircraft wing has inner load-bearing primary structure and upper and lower skins. Wing is made in form of chute of varying section in plan smoothly narrowing from aircraft nose to tail.EFFECT: updated wing differing from tear-shaped wing; enhanced efficiency of creating lifting force.4 dwg

Swept wing // 2216481
The invention relates to aeronautical engineering

Ending the bearing surface of the aircraft // 2216480
The invention relates to aviation

The plane // 2213023
The invention relates to aircraft construction

Training flight yak-54 // 2177895
The invention relates to aviation, in particular to the training of flight and airplanes

The wing tip of the aircraft // 2173655
The invention relates to aircraft and can be used on the aircraft, subsonic and transonic flight speeds

Aircraft short takeoff and landing // 2165867
The invention relates to aviation

Wing with supersonic free laminar flow (options) and control system laminar flow on the wing surface // 2133692
The invention relates to the triangular wings with reverse narrowing and their modifications, and in particular to the triangular wings with reverse narrowing for supersonic aircraft

Supersonic aircraft // 2100253

The plane with the arched wing // 2096262
The invention relates to the field of Aeronautics, in particular for heavier than air

Wing aircraft // 2086467
The invention relates to aircraft and can be used on various aircraft

The plane // 2067948
The invention relates to the field of aeronautical engineering and can be used in the construction of the articulated wing aircraft