System and device to reduce turbulence in aircraft wake

FIELD: transport.

SUBSTANCE: set of inventions relates to aircraft engineering. Proposed system comprises a device secured to aircraft tail part to periodically rotating about the axis located at, approximately, right angle to flight direction. Said device is arranged on wing upper surface 4 and comprises stationary element 6 and first 7, 9 and second 8, 10 wing elements pivoted behind said stationary element 6 and can be spaced apart along flight direction. Method is distinguished by using aforesaid device that prevents swirling of airflow nearby outer wing in swinging about axis of rotation.

EFFECT: reduced turbulence in aircraft wake.

5 cl, 10 dwg

 

The technical FIELD

The invention relates to systems and methods reduce the vortices generated by the aerodynamic surfaces, in particular reducing turbulences, which occur on the wings of the aircraft and make a significant contribution to the turbulence in their Wake vortex.

BACKGROUND of INVENTION

Turbulence in Wake vortex is associated with the emergence of the necessary lifting force. On the lower surface of the wing, creating lift, the pressure is higher than its top surface. Accordingly, at the edges of the wing the air flow is directed from the bottom up, resulting in a strong vortex, the so-called "vortex aerodynamic surfaces". In addition, on the rear edge of the wing layers flow of fluid coming from the upper and lower surfaces of the wing, have different directions, so that there is free layer mixing, which in the direction of the wing span is associated with the corresponding vortex aerodynamic surfaces. This free layer blending together with the corresponding vortex aerodynamic surface coils in two separate vortex, which can rotate in opposite directions like a small horizontal tornadoes, the speed in which the Central part depending on the size of the aircraft can reach 360 km/h

Tour Wantnot in Wake vortex to its attenuation is observed behind the plane at a distance of several hundred dimensions wing span. This means that in case of heavy aircraft such turbulence may persist for several minutes, and the length of the turbulent boundary trace can reach 30 km

This can have dire consequences, especially for small aircraft, which are included in the turbulent Wake; for example, serious local fluctuations aerodynamic forces can cause the entire length of the track to the loss of stability of the aircraft included in the trail line.

For this reason, between aircraft should be maintained an appropriate distance, especially during takeoff and landing. Vortices aerodynamic surfaces, which are created by the wing and are the result of continuous coagulation of air flow, creating a hazard to following aircraft and are therefore the limiting factor for the frequency of take-offs and landings.

The INVENTION

The aim of the invention is to provide a system and corresponding method for reducing vortex aerodynamic surfaces that arise as a result of continuous clotting process air flow, and, accordingly, reduce the decay time of turbulent trace in the case of the aircraft.

This goal is achieved through proposed in the invention system, which contains at the end cha the t-wing aircraft device, you can swing with a certain period around the axis passing approximately perpendicular to the direction of flight, for violations of the clotting process air flow in the area of the wing. The process of coagulation occurs as a result of mixing of the air streams flowing upper and lower surfaces of the wing, the pressure at which vary.

Proposed in the present invention, the system can be integrated into existing designs, although you can also offer and offline design. In the alternative proposed in the invention, the system can be mounted to existing structural elements. In the following description of embodiments of the invention and the corresponding attached figures such devices are called "leaf wings" or "aerodynamic ridges on the wing". Currently, these aerodynamically efficient elements that are integrated into the end of the wings, are used in almost all large commercial aircraft.

In accordance with the invention, the device, download to a specific period, is placed on the upper surface of the wing and contains a fixed element, and first and second wing elements, which can be rotated around the axis of rotation. The first and second wing elements can be, for example, placed n the stream for a fixed element side by side, and they can take from each other. In accordance with that proposed in the invention to improve the rotatable elements of the wing can swing with a certain period when they are abstracted from each other around a rotation axis that is approximately perpendicular to the direction of flight, and the relative position of the elements of the wing relative to each other remains constant, or in accordance with one alternative is changed during the swing.

In accordance with the embodiment of the invention it is possible to control the movement of the wing elements from the first state, in which they almost parallel to the flight direction, a second state in which the first element of the wing is rejected to the outside (away from the fuselage) at a first predetermined angle relative to the direction of flight, and the second wing element rejected inward (toward the body) at a second predetermined angle relative to the direction of flight. In this case, the drag coefficient of the aircraft increases by a given amount (depending on the configuration, and the lift force remains almost constant). Thus, in this case, you can provide a more abrupt decrease or dive without changing the thrust.

For managed violations of the clotting process air flows in the one wing in the second state elements of the wing dangle with a certain period at a predetermined speed between the extreme outer position and an extreme inner position. The swing speed can be constant or it can be modified.

When executing a swing with a particular period of the first and second inclination angles of the wing elements is chosen such that the drag coefficient aerodynamic surfaces remained constant, which avoids the adverse effects of this process on the passengers, because thirst is not changed.

In accordance with the invention, for example, during landing of the first and second wing elements can be transferred from a first state in which they are folded together and in which the first and second inclination angles are zero, the second condition in which the first element of the wing is turned outward at a first predetermined angle relative to the direction of flight, and the second wing element is turned inward at a second predetermined angle relative to the direction of flight. Further, in the second stage, the wing elements that are rotated, as indicated above, it is possible to download from a specific period (relative to the direction of flight) between the first extreme position and a second extreme position around an axis that is approximately perpendicular to the direction of flight, and in the process of swinging the first and second angles of deflection of the control so that the drag coefficient of the wing remained constant. In this case, vortices, with the given aerodynamic surface, violated, and thus the turbulence in the Wake vortex of the aircraft decreases.

Thus, in accordance with the invention, it is possible to reduce the time of the disturbance of the atmosphere of the aircraft, which is determined by its cocurrent then the decay time of this track. The term "time for outrage" for an aircraft refers to the minimum waiting time between takeoff (landing) aircraft and allowed a safe takeoff (landing) the next plane. The intensity and the size or length of the cocurrent track determines the time of its decay, according to which the aircraft are classified according to the level of disturbance of the atmosphere.

Thus, the invention allows construction of additional runways to improve the performance of airports by reducing time perturbation of the atmosphere by airplanes, among other things, using the proposed in the invention system and method.

BRIEF DESCRIPTION of DRAWINGS

Embodiments of the invention are described below with reference to the accompanying drawings. In the drawings shown:

Figure 1 - schematic partial perspective view of the aircraft in accordance with the first embodiment of the invention;

Figures 2a-2d is a schematic top system in accordance with the first embodiment of the invention in different designs for the x States;

Figure 3 - schematic partial perspective view of a wing in accordance with the second option proposed in the invention system;

Figures 3a-3d is a schematic top system in accordance with the second embodiment of the invention in different States.

In the following description of various types of shapes are used the same reference symbols to the same elements.

DETAILED description of the INVENTION

The figure 1 presents a schematic partial perspective view of a system 1 in accordance with the first embodiment of the invention.

The system 1 includes a device 2, which is the terminal area of the wing 3 of the aircraft (not shown).

As shown in figure 1, in accordance with the first embodiment of the invention, the device 2 is placed on top of the wing, in order to disrupt the air flow, which enters from the bottom surface 5 of the wing to the upper part 4 (the clotting process).

The device 2 in accordance with the first embodiment of the invention includes a stationary element 6, the first wing element 7 and the second element 8 of the wing. The figure 1 shows that the second element 8 of the wing is behind the first element 7 of the wing and covered them.

The first and second elements 7, 8 wing are placed behind (downstream) C is movable partition element 6 and pivotally attached thereto with the axis, which is almost perpendicular to the direction of flight. In figure 1 the axis of the hinge shown in dotted lines. The fixed element 6 and the elements 7, 8 wing are preferably in the direction of flight and are aerodynamic surfaces.

Figure 2A presents a top view of the system 1, presented in figure 1, in the first state.

In this first state, the first wing element 7 and the second element 8 wing folded together so that their respective inner surfaces facing each other and preferably touch each other. State 1 items 7, 8 wing is used, for example, during normal flight mode. In this state, which can be called the initial state, the drag coefficient and lift coefficient are almost constant values different for different aircraft types.

As shown in figure 2A, the stationary element 6 and the folded elements 7, 8 wing is roughly in the direction of a flight, thus forming the aerodynamic node.

Figure 2b shows the second state of the elements 7, 8 of the wing. This second condition is used, for example, at the beginning of the landing. To control the elements 7, 8 of the wing so that they took this second condition, it is possible to use a centralized control system of the aircraft.

As shown in figure 2b, the first element 7 wing rejected by the angle δuoutward, away from the fuselage (not shown). The second element 8 wing rejected by the angle δ0inside, in the direction of the fuselage (not shown). The angles δuand δ0measured relative to the direction And flight. In this second state, the drag coefficient increases, while the lift coefficient remains the same. In the deflection elements 7, 8 wing at angles δuand δ0accordingly, there is a constant change cocurrent trail wing. Values of angles δuand δ0depend on a specific model of aircraft, and their optimal values can be determined in a wind tunnel.

Figure 2C shows a third state of the elements 7, 8 of the wing in which they are from the middle position shown in figure 2b, turned out in the extreme outer position, and their position relative to each other when the rotation is maintained. In accordance with figure 2C outermost position is achieved by rotation when the direction of the second element 8 is approximately coincides with the direction And flight. The rotation of the elements 7, 8 wing at a specified extreme outer position, with a given speed of rotation. The management of this rotational movement can be carried out with the help of the center is savannas control plane.

In the extreme outer position, shown in figure 2C, the direction of rotation is changed, and the elements 7, 8 wing turn in the extreme inner position shown in figure 2d. At this point, the direction of rotation is again changed, and a new cycle begins.

While performing the above sequence of moves from one extreme position to another extreme position angles δuand δ0preferably maintained so that the drag coefficient remained constant. As a result of this cyclic motion sequence elements 7, 8 of the wing is broken, the resistance of the coagulation process air flow at the posterior edge of the wing and, accordingly, reduces the turbulence created in the Wake vortex.

The figure 3 presents the second option proposed in the invention system 1, which represents the construction of a so-called aerodynamic crest at the end of the wing.

In accordance with this option proposed in the invention, the system 1 includes a first wing element 9 and the second element 10 of the wing, which is placed at the end of the wing 3 of the aircraft (not shown). In particular, the first wing element 9 is placed on the upper surface 4 of the wing, and the second element 10 of the wing is placed on the bottom surface 5 of the wing. At the point In the stop elements 9, 10 wing can be rotated about an axis approximately perpendicular to the direction of flight, as shown in figures 3a-3d.

In figures 3a-3d shows the top of the upper surface 4 of the wing 1, presented in figure 3. As can be seen in figure 3a, in many ways, similar to figure 2A, related to the first embodiment, in the first state, the elements 9, 10 are in their initial position, in which they are not rejected, neither outward nor inward direction And flight. In figure 3A in the top view you can only see the wing element 9 and item 10 of the wing, which is located on the lower surface of the wing, the shape is not visible.

Figure 3b shows the elements 9, 10 wings, rejected the angles δuand δ0about the same as the elements 7, 8 in this state, the first variant embodiment of the invention.

Figure 3c shows a third state, in which the elements 9, 10 of the wing from the middle position turned out in the end position, and their position relative to each other when the rotation is stored (as well as the elements 7, 8 in the third state the first option).

Figure 3d shows the elements 9, 10 of the wing in the fourth state, in which they turned inward. Aerodynamic processes in conditions 1-4, shown in figures 3a-3d correspond to the processes of conditions 1-4 of the first variant and therefore are not described.

Although sabreena been described on the example of the preferred variants of its implementation, however, it is clear that the experts in this field of technology can be introduced into the system changes and additions within the scope of protection of the invention.

For example, can be used more than two elements of the wing, which can be rotated with a certain period at different speeds around the direction of flight, while aged specified position of the elements relative to each other. Although in accordance with a preferred variant embodiment of the invention, it was stated that the wing elements are translated into state 3 and 4 with maintaining given their position relative to each other, but of course possible ways in which the position of the elements relative to each other changes during cyclic rotational movement. The approximate constancy of the coefficient of drag in the circular rotational motion of the wing is a specified requirement in the degree to which the passengers of the aircraft will not be subject to appreciable forces of braking and acceleration.

1. A system for reducing the turbulence in the Wake vortex of the aircraft, containing the device attached to the end portion of the wing (3) of the aircraft, which is performed periodically rotated around an axis passing approximately at right angles to the direction of flight, when it is the specified device is placed on the top surface (4) of the wing and contains a fixed element (6) and pivotally attached to the first (7, 9) and second (8, 10) elements of the wing, which is set to flow for a fixed element (6) side by side and can be abstracted from each other in the direction of flight.

2. The system according to claim 1, in which the elements (7, 8; 9, 10) of the wing in the first state set so that they are approximately parallel to the direction of flight, and in the second state the first element (7; 9) wing turn out at the first given angle (δu) deviation from the direction of flight, and the second element (8, 10) wing turn inward at the second given angle (δ0) deviation from the direction of flight.

3. The system according to claim 2, in which for violations of the clotting process air stream in the console pane of the wing in the second state, the wing elements (7, 8; 9, 10) is turned to a specific period at a given speed between the extreme outer position and an extreme inner position.

4. The system according to claim 3, in which during the swing of the first and second inclination angles (δu, δ0) is chosen such that the drag coefficient of the wing (3) remained constant.

5. The way to reduce turbulence in the Wake vortex of the aircraft using the system according to one of claims 1 to 4, containing the following stages:
moving the first and second elements (7, 8; 9, 10) wing from a first state in which the wing elements stacked together and pass p is essentially parallel to the axis (A), which runs along the flight direction, a second state in which the first element (7; 9) wing reject out at the first given angle (δuand the second element (8; 10) wing deflect inward at the second given angle (δ0) about the axis (A)passing in the direction of flight; and
turn with a certain period around the axis of rotation of the elements (7, 8; 9, 10) in the second state between the first extreme position and a second extreme position, and when rotated around the axis of rotation of the first and second angles (δu, δ0) deviations are chosen so that the drag coefficient of the wing (3) remained constant.



 

Same patents:

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Aircraft wing tip comprises generator of vortex with direction of rotation originating at wing and casing. Vortex generator represents nacelle with inlet and outlet swirlers. Casing represents a thin-wall structure with constant-radius inner surface extending along wing end chord with unclosed cross section that forms lengthwise cutout. Swirler is furnished with diffuser. Said casing lengthwise cutout is made so that cutout top edge forms central angle on casing axis, while its bottom edge forms that on casing axis. Inlet device can have confuser deflected from wing chords lane downward, while casing tail end is inclined upward.

EFFECT: higher aerodynamics and ring load bearing properties.

10 cl, 7 dwg

Aircraft wing tip // 2385265

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Aircraft wing tip comprises channel with inlet and outlet holes. Inlet hole represents an air intake arranged on lower front surface and communicated with conical channel with end cross section with diametre of 0.05 to 0.2 of the length of chord of wing tip section and is located at the distance of 0 to 0.2 of chord length from rear edge along flow direction. Channel axis is located on 0 to 0.2 of chord length above the plane of chords. Channel midsection accommodates disk-like rotary flap with its axis perpendicular to channel axis. Flap can be rotated by airflow.

EFFECT: higher lift and reduced drag.

3 cl, 7 dwg

FIELD: aircraft engineering.

SUBSTANCE: device to control vortex street comprises control device (8) mounted on clamping element (11) of elongated element (5) and on control surface (4) so that its base (12) comes in contact with front edge (6) of its aforesaid control surface. Said control device (8) features triangular shape in the plane perpendicular to its lengthwise axis and having two adjacent sides forming lateral surfaces interconnected by rounded edge. Aircraft incorporates vortex street control device.

EFFECT: reduced drag.

6 cl, 6 dwg

FIELD: mechanics; aircraft construction.

SUBSTANCE: inventions relate to aeromechanics, mainly to friction reduction method for axisymmetric body and related devices. Toroidal vortex with controlled parametres is generated in a boundary layer of axisymmetric body by periodic air flow blowing/suction through the circular slot available in axisymmetic body wall. The related device includes periodic vibrations source coupled with flow running over axisymmetric flow. The above mentioned circular slot in the wall of axisymmetric body is made so that it is directed to the longitudinal axis x at a negative angle. The longitudinal axis x is directed along generatix of axisymmetric body, wherethrough air is blown/drawn off at controlled amplitude and frequency by means of periodic vibrations source, for example dynamic loud-speaker.

EFFECT: reduced effect of superficial friction component in axisymmetric body by controlling vortex by frequency and intensity.

4 cl, 4 dwg, 1 ex

FIELD: transport.

SUBSTANCE: invention relates to aviation. The method of varying the lift of a body in flowing medium consists in affecting the flow by one or several flexible tape-like spaced elements extending from the body surface flown over by the said medium. The device is also proposed incorporating one or several flexible tape-like spaced elements extending from the body surface flown over by the flowing medium.

EFFECT: reduction of drag.

9 cl, 2 dwg

FIELD: aviation.

SUBSTANCE: aircraft (10) has fuselage (12) connected with wings, air intake (46), nose section (52) of fuselage of varying cross section and vortex generation control unit (72) located on leading-edge wing extension whose shape makes it possible to make symmetrical break of vortices on said extension and medium and large angles of attack; it is engageable with tail sections (44 and 38) spaced apart so that leading edge (36) of vertical fin (38) gets beyond trailing edges of each wing for maintenance of stability in transversal direction. Ratio of area of leading edge extension and height of vortex generation control unit is equal to 2.35 m and tolerance range changes from +100% to -50% of this magnitude.

EFFECT: improved aerodynamic properties at large angles of attack.

8 cl, 18 dwg

FIELD: aerodynamics; designing of flying vehicles, organization of aircraft motion in water.

SUBSTANCE: proposed method consists in forming regular structures for finding the conditions when axis of natural vortices is directed not in way of flow but at any angle required by conditions of flow. Infinite sequence of artificial vortices is similar to roller bearing located between body and medium. Proposed method provides for creating the lifting force for flying vehicle on base of proposed model of flowing around solid bodies by continuous media. Proposed method consists in forming the determined vortices on upper surface of wing which are directed to overwing flap where they are broken. Vortices rolling over upper surface of wing without sliding increase in size. Their destruction within overwing flap results in increase of pressure, thus creating lifting force for aircraft.

EFFECT: enhanced efficiency.

8 cl, 8 dwg

FIELD: aeronautical engineering; rocketry and space engineering; technology of control of flow around flying vehicle.

SUBSTANCE: proposed method consists in delivery of gas to incoming flow in front of nose section of flying vehicle. Density of this gas is lesser than density of medium; gas is fed to points of aerodynamic drag of flying vehicle where porous coat is formed; pores of this coat are open to surface; scale of these pores is lesser than that of vortex generation. Gas is delivered at periodicity of generation of turbulent vortices to turbulence generation zone at phase shifted by 45-135 degrees. In realization of this method coat may be formed at points where shock wave is formed. It is good practice to feed gas to porous coat from reservoir containing sorbent separating gas till gas desorption temperature has been attained. Gas is mainly fed to upper edge of wing. It is good practice to make coats from catalytically active heat-accumulating material and to realize endothermic process during passage of gas through it. Front surfaces of wings and nose sections of flying vehicles may be covered with coats of low electron emission energy from the following series: barium oxide, titanium carbide, zinc oxide, copper oxide rare-earth metal oxide and n-semiconductors.

EFFECT: possibility of changing aerodynamic properties in turbulence generation zone.

16 cl

Engine // 2270785

FIELD: devices for creation of aero- or hydrodynamic forces for transport facilities with the aid of rotating members.

SUBSTANCE: proposed engine has housing and two cones with surfaces rotating in opposite directions. Rotating surfaces are provided with cells in form of tooth spaces and teeth. Teeth on surface of front cone are bent in way of flow around the cell and teeth on surface of rear cone are bent towards incoming flow which is circular in shape and is caused by rotation of surfaces of cones. Surface of each tooth space has form of question-mark in section. As a result, reduced pressure is built-up in cells of rotating surface of front cone and increased pressure is built-up in cells of rotating surface of rear cone, thus creating the thrust along axis of rotation of cones.

EFFECT: extended field of application of thrust creating devices for various vehicles running in air and water media.

6 dwg

FIELD: rocketry and space engineering.

SUBSTANCE: proposed device has nose section 1 and central and additional aerodynamic needles 3 made in form of thin cylindrical rods which are stowed in special passages made in nose section of flying vehicle. One passage is located along axis of symmetry and other passages are located at some distance from axis of symmetry smoothly over circumference whose center lies at axis of symmetry. Each passage is provided with mechanism for delivery of aerodynamic needles towards incoming flow; provision is made for extension of each needle through definite length for forming special configuration of set of needles which is necessary for their joint operation in airflow control.

EFFECT: possibility of obtaining constant coordinate of center of pressure of hypersonic flying vehicle; reduced force of drag; possibility of forming control forces and moments for manoeuvring in atmosphere.

4 dwg

FIELD: aircraft.

SUBSTANCE: device comprises vortex pipe with a scroll for supplying and accelerating air and cold and hot end sections. The cold end section of the vortex pipe is provided with a ring plate. The diameter of the inner opening in the plate should be chosen to allow it to be fit on the vortex pipe with interference for increasing the area of the face of the cold section. The vortex pipe can be mounted in the guiding member which defines the inclination of the vector of the propulsion to the horizon. The hot section of the vortex pipe should be provided with a valve.

EFFECT: improved design.

3 cl, 2 dwg

FIELD: reduction of vortices behind aircraft.

SUBSTANCE: aircraft has starboard and port wings for forming lifting force; wings are provided with landing flaps for forming considerable lifting force. Vortex generator for forming controllable disturbance vortex is made in form of additional flap whose base is located in area of 10-% semispan to the right and to the left from external end of landing flap and beginning at 60% of depth of lifting wing profile. During flight, additional flap is kept in extended position; it may be retracted in wing when not in use. Controllable vortex is formed with this device.

EFFECT: reduction of vortices behind aircraft at landing approach.

15 cl, 9 dwg

FIELD: rocketry and space engineering.

SUBSTANCE: proposed device has nose section 1 and central and additional aerodynamic needles 3 made in form of thin cylindrical rods which are stowed in special passages made in nose section of flying vehicle. One passage is located along axis of symmetry and other passages are located at some distance from axis of symmetry smoothly over circumference whose center lies at axis of symmetry. Each passage is provided with mechanism for delivery of aerodynamic needles towards incoming flow; provision is made for extension of each needle through definite length for forming special configuration of set of needles which is necessary for their joint operation in airflow control.

EFFECT: possibility of obtaining constant coordinate of center of pressure of hypersonic flying vehicle; reduced force of drag; possibility of forming control forces and moments for manoeuvring in atmosphere.

4 dwg

Engine // 2270785

FIELD: devices for creation of aero- or hydrodynamic forces for transport facilities with the aid of rotating members.

SUBSTANCE: proposed engine has housing and two cones with surfaces rotating in opposite directions. Rotating surfaces are provided with cells in form of tooth spaces and teeth. Teeth on surface of front cone are bent in way of flow around the cell and teeth on surface of rear cone are bent towards incoming flow which is circular in shape and is caused by rotation of surfaces of cones. Surface of each tooth space has form of question-mark in section. As a result, reduced pressure is built-up in cells of rotating surface of front cone and increased pressure is built-up in cells of rotating surface of rear cone, thus creating the thrust along axis of rotation of cones.

EFFECT: extended field of application of thrust creating devices for various vehicles running in air and water media.

6 dwg

FIELD: aeronautical engineering; rocketry and space engineering; technology of control of flow around flying vehicle.

SUBSTANCE: proposed method consists in delivery of gas to incoming flow in front of nose section of flying vehicle. Density of this gas is lesser than density of medium; gas is fed to points of aerodynamic drag of flying vehicle where porous coat is formed; pores of this coat are open to surface; scale of these pores is lesser than that of vortex generation. Gas is delivered at periodicity of generation of turbulent vortices to turbulence generation zone at phase shifted by 45-135 degrees. In realization of this method coat may be formed at points where shock wave is formed. It is good practice to feed gas to porous coat from reservoir containing sorbent separating gas till gas desorption temperature has been attained. Gas is mainly fed to upper edge of wing. It is good practice to make coats from catalytically active heat-accumulating material and to realize endothermic process during passage of gas through it. Front surfaces of wings and nose sections of flying vehicles may be covered with coats of low electron emission energy from the following series: barium oxide, titanium carbide, zinc oxide, copper oxide rare-earth metal oxide and n-semiconductors.

EFFECT: possibility of changing aerodynamic properties in turbulence generation zone.

16 cl

FIELD: aerodynamics; designing of flying vehicles, organization of aircraft motion in water.

SUBSTANCE: proposed method consists in forming regular structures for finding the conditions when axis of natural vortices is directed not in way of flow but at any angle required by conditions of flow. Infinite sequence of artificial vortices is similar to roller bearing located between body and medium. Proposed method provides for creating the lifting force for flying vehicle on base of proposed model of flowing around solid bodies by continuous media. Proposed method consists in forming the determined vortices on upper surface of wing which are directed to overwing flap where they are broken. Vortices rolling over upper surface of wing without sliding increase in size. Their destruction within overwing flap results in increase of pressure, thus creating lifting force for aircraft.

EFFECT: enhanced efficiency.

8 cl, 8 dwg

FIELD: aviation.

SUBSTANCE: aircraft (10) has fuselage (12) connected with wings, air intake (46), nose section (52) of fuselage of varying cross section and vortex generation control unit (72) located on leading-edge wing extension whose shape makes it possible to make symmetrical break of vortices on said extension and medium and large angles of attack; it is engageable with tail sections (44 and 38) spaced apart so that leading edge (36) of vertical fin (38) gets beyond trailing edges of each wing for maintenance of stability in transversal direction. Ratio of area of leading edge extension and height of vortex generation control unit is equal to 2.35 m and tolerance range changes from +100% to -50% of this magnitude.

EFFECT: improved aerodynamic properties at large angles of attack.

8 cl, 18 dwg

FIELD: transport.

SUBSTANCE: invention relates to aviation. The method of varying the lift of a body in flowing medium consists in affecting the flow by one or several flexible tape-like spaced elements extending from the body surface flown over by the said medium. The device is also proposed incorporating one or several flexible tape-like spaced elements extending from the body surface flown over by the flowing medium.

EFFECT: reduction of drag.

9 cl, 2 dwg

FIELD: mechanics; aircraft construction.

SUBSTANCE: inventions relate to aeromechanics, mainly to friction reduction method for axisymmetric body and related devices. Toroidal vortex with controlled parametres is generated in a boundary layer of axisymmetric body by periodic air flow blowing/suction through the circular slot available in axisymmetic body wall. The related device includes periodic vibrations source coupled with flow running over axisymmetric flow. The above mentioned circular slot in the wall of axisymmetric body is made so that it is directed to the longitudinal axis x at a negative angle. The longitudinal axis x is directed along generatix of axisymmetric body, wherethrough air is blown/drawn off at controlled amplitude and frequency by means of periodic vibrations source, for example dynamic loud-speaker.

EFFECT: reduced effect of superficial friction component in axisymmetric body by controlling vortex by frequency and intensity.

4 cl, 4 dwg, 1 ex

FIELD: aircraft engineering.

SUBSTANCE: device to control vortex street comprises control device (8) mounted on clamping element (11) of elongated element (5) and on control surface (4) so that its base (12) comes in contact with front edge (6) of its aforesaid control surface. Said control device (8) features triangular shape in the plane perpendicular to its lengthwise axis and having two adjacent sides forming lateral surfaces interconnected by rounded edge. Aircraft incorporates vortex street control device.

EFFECT: reduced drag.

6 cl, 6 dwg

Up!