CN201023655Y - Wing tip negative direction vortex device - Google Patents
Wing tip negative direction vortex device Download PDFInfo
- Publication number
- CN201023655Y CN201023655Y CNU2007201405443U CN200720140544U CN201023655Y CN 201023655 Y CN201023655 Y CN 201023655Y CN U2007201405443 U CNU2007201405443 U CN U2007201405443U CN 200720140544 U CN200720140544 U CN 200720140544U CN 201023655 Y CN201023655 Y CN 201023655Y
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- wing
- cover
- eddy flow
- air
- flow
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Abstract
A negative direction whirling device of a wing tip of a plane wing belongs to the aviation machinery field, which is characterized in that the end of the wing tip of the plane wing is equipped with a whirling cover, the inside of the whirling cover and an ejector nozzle of the shape of an outside strip are connected with a draw-off tube of an air compressor of an engine through an inner guiding tube of the plane wing, a small amount of compression air from the air compressor is led out and ejected out from the inner and outer ejector nozzles through a control valve and a guiding tube, the whirling air current and the downward shooting current are separately caused in the whirling cover and on the outside of the cover, the direction of the air currents is in an opposite position of the air current flowing from a lower wing surface of the plane wing to the upper wing surface around the wing tip, the opposite currents reduce and basically eliminate a free trailing vortex which is on the downstream of the wing tip, thereby the utility model reduces the induced resistance of the plane wings about 30% to 40% when in flight, also additionally produces the propulsion and the elevating force, increases the flight performance and economy. The utility model has the advantages of simple and reliable structure, small size, and lightness and little resistance. The utility model can reduce more than half of the present manufacturing cost, and can be widely applied in airplanes (with fixed wings) of various types with subsonic speed.
Description
Affiliated technical field:
The invention belongs to the aviation machine field, particularly relate to a kind of device that reduces the aircraft wing induced drag.
Background technology:
Aircraft awing, therefore the induced drag of its wing accounts for 40% of cruising flight resistance, reduces induced drag, aeroperformance and economy to improving whole aircraft are significant.General wing aspect ratio is bigger, and induced drag is littler, but structural weight also increases thereupon.Another kind of mode is to take better aerofoil profile.Produce the principle of induced drag according to wing, what have installs vertical end plate additional at the wing wingtip, forms free trailing vortex to suppress the wingtip downstream, plays a part necessarily, but effect is little.What have is contained in wing wingtip place with empennage (comprising yaw rudder), but drag-reduction effect is not remarkable yet.The seventies in 20th century, the RT Whitcomb proposes " winglet " drag reduction scheme.With after relevant development test, confirm the winglet of Reasonable Shape, structure and layout, can make induced drag reduce 20%--25%, this 1ift-drag ratio that roughly is equivalent to wing can improve about 7%, thereby the economy of corresponding raising aircraft has begun to be applied on the aircrafts such as transport plane, passenger plane.But still can not further reduce aloft induced drag significantly, winglet influences wing structure weight simultaneously, itself also has certain air resistance.
Summary of the invention:
Deficiency at existing wing fairing existence.The present invention studies and has innovated a kind of wing wingtip reversing sense swirl-flow devices, and the eddy flow that this device produces at wingtip is opposite to the mobile eddy flow direction of top airfoil around wingtip from lower aerofoil awing with former wing.Suppress the generation of wingtip downstream eddy current (trailing vortex) greatly, can further reduce its induced drag by a relatively large margin.
The technical scheme in the invention for solving the technical problem is: wingtip place, wing aircraft two ends, each connects a specific eddy flow cover, eddy flow cover open interior (strip seam hole) connecting duct, partly draw the small amount of compression air from driving engine (automotive gas turbine etc.) air compressor, by control cock and conduit, tangentially enter in the eddy flow cover through bar shaped seam hole, produce rotational flow, pressurized air is overlapped outer cover along eddy flow simultaneously, spray the formation jet downwards through outer spout, converge with eddy flow cover forward air inlet, form eddy flow, its direction and former wing are walked around wingtip from lower aerofoil, and to flow to the eddy flow direction of top airfoil opposite, suppress, eliminate the free trailing vortex in the wingtip downstream airflow, reach the purpose that reduces induced drag.
The beneficial effects of the utility model are: do not influence original wing and dynamic structure basically, install the eddy flow cover of simple tubulose, only partly draw very a spot of pressurized air (generally be no more than its total amount 1%) from the general gas turbo-compresser.To produce an amount of reverse eddy flow at the wingtip position, induced drag can reduce 30%--40% approximately, and its flow also generation certain additional thrust and lift, and whole device is simple, reliable, in light weight.
Below in conjunction with accompanying drawing and example, structure of the present utility model and principle are described further.
In the utility model, (Fig. 1), eddy flow cover (7) is positioned at the two ends of aircraft wing (5), and conduit (6) is housed in the wing, and conduit one end is connected with driving engine (gas turbine etc.) air compressor fairlead by control cock (2).The conduit other end connects the outer cover (8) of eddy flow cover (7) and top thereof.Formation is drawn from air compressor, through control cock (2), conduit (6) connecting pipe to eddy flow cover (7).Driving engine (1) air compressor is drawn the small amount of compression air, and (flow velocity is V
R), flow into space between eddy flow cover (7) and the outer cover (8) through pipeline thus, (Fig. 1--Fig. 4), air-flow divides two-way, and one the tunnel flow to the interior spout (10) of eddy flow cover gap-shaped, tangentially with speed V
ASpurt into the eddy flow cover.Make air-flow rotation (eddy flow) in the eddy flow cover.Then continue to flow along space between outer cover and the eddy flow cover in another road, spout is with speed V outside gap-shaped
BEjection downwards forms bar seam wall-attached jet (direction shown in each arrow among the figure).According to the wall-attached jet characteristic, it is mobile that a large amount of air attached eddy flow cover overcoat near this stream will be induced and be entrainmented.Direction just in time with wing lower aerofoil (4) and top airfoil (3) difference of pressure, the cause is around the wingtip flow direction (V among Fig. 3 on the contrary that makes progress
CArrow), eddy flow cover (7) eddy flow is also opposite with former wing wingtip trailing edge free trailing vortex flow direction downstream simultaneously.The place ahead is converged together with the air-flow that speed V flows to eddy flow cover in addition, makes to produce eddy effect and weaken, and disappears near basic, makes near the wingtip and the rear portion air-flow, forms with speed V
XFlow backward with more straight abreast.Effect more flows through the situation of infinite wing near air.The angle of downwash that the relative incoming flow in each wing section is directed downwards deflection reduces.The total aerodynamic force direction of vertical therewith incoming flow degree of deflection is backward also dwindled, and more approaching how much angles of attack of actual angle of attack are that induced drag reduces thereupon to the component that heads on flow path direction to produce as a result.Suitable design can make this induced drag reduce 30%--40%, is equivalent to the actual 1ift-drag ratio of wing and improves about 10%--15%.
Simultaneously, by the air-flow of eddy flow cover, can produce certain additional thrust, and the downward blast injection of eddy flow cover overcoat gap-shaped spout also produces certain additional lift.
The compressed-air actuated flow that enters eddy current cover (7) and outer cover (8) thereof in-flight is by control cock (2) control, its air consumption generally less (generally be no more than engine compressor flow 1%).Handle the different switching degree of two control cock of both sides wing, can make flow, the flow velocity difference of both sides wing tip vortex covering device, it is also different that the both sides wingtips produces additional thrust, side lift, and state of flight that thus can further more accurate operating aircraft improves the road-holding property of aircraft.
The utility model first feature is: two eddy flow covers (7) are positioned at wing wingtip two ends, the eddy flow jacket wall has spout (10) in the gap-shaped, its outer jacket (8) has the outer spout (11) of gap-shaped, and inside and outside spout links to each other with driving engine (1) air compressor fairlead by conduit (6), control cock (2).
Second feature is: it is peripheral that outer cover (8) is positioned at eddy flow cover top, overlaps gap-shaped spout (10) to eddy flow in the outer cover and be tangential direction, and outer spout (1) direction of outer cover gap-shaped down.
The 3rd feature is: eddy flow overlaps cylindrical hollow tubular.Admission port is positioned at front end, and exhausr port is positioned at the rear end.
Description of drawings:
Fig. 1 is the birds-eye view of driving engine, wing section, internal pipeline and wingtip eddy flow covering device, and another is that its V is to view.
Fig. 2 is A--A longitudinal profile (amplification) figure of eddy flow cover (5) device among Fig. 1.
Fig. 3 is the B--B section-drawing of Fig. 2 eddy flow cover (5).
Fig. 4 overlaps each road air-flow direction and fundamental diagram by eddy flow in-flight.
Fig. 1--among Fig. 4: spout, the outer spout of 11--outer cover gap-shaped in 1--driving engine, 2--control cock, 3--wing top airfoil, 4--wing lower aerofoil, 5--wing, 6--conduit, 7--eddy flow cover, 8--outer cover, 9--eddy flow cover admission port, the 10--eddy flow jacket wall gap-shaped.V, V
XIt is respectively the air-flow velocity that flows into, flows out the eddy flow cover.V
R--conduit compressed air flow velocity, V
A, V
BIt is respectively the flow velocity that spout (11) flows out air outside interior spout (10) of eddy flow cover and overcoat.V
C--lower aerofoil elevated pressures air lays out wingtip to top airfoil (pressure is lower) flowing velocity during flight.
The specific embodiment:
Two eddy current of the utility model overlap cylindrical tubulose, and simple in structure, conduit diameter is also less, is easy to arrange in wing, and is in light weight, do not influence wing structure, handle control only with two simple control cock, are convenient to processing and manufacturing and implement.
Below be an embodiment of the present utility model:
Title: wing wingtip reversing sense swirl-flow devices
Eddy flow cover quantity and shape: 2 cylindric hollow tubular
Eddy flow cover diameter and length (millimeter): diameter 95, length 750
Eddy flow cover admission port diameter (millimeter): 68
Diameter of outlet (millimeter): 92
Jet size (millimeter) in the eddy flow cover gap-shaped: long by 80, wide by 2
The outer jet size (millimeter) of eddy flow cover outer cover gap-shaped: long by 240, wide by 2
Inside and outside spout air-flow velocity (meter per second): 150
2 swirl-flow devices pressurized air total flows (2000 meters of height, control cock standard-sized sheet) (Kilograms Per Second) 2 * 0.12
Eddy flow cover and outer cover weight (kilogram) 1.85
The utility model has the advantages that:
1, this device can reduce 30%～40% of wing induced drag in-flight. In-Flight Performance and economy have been improved.
2, this device is positioned at the wing wingtip, does not affect wing structure, does not almost have projection, and is simple and reliable for structure, and production cost is approximately than correspondence Common winglet reduces more than 50%.
3, this plant bulk, weight and air drag are all less than the common winglet of correspondence.
4, this device also produces certain additional thrust and additional lift when flight, and by simple control valve control, it flies can to compare accurate adjustment The row attitude is conducive to improve its maneuverability.
This device can be widely used on interior all kinds (fixed-wing) aircraft of subsonic envelope.
Claims (3)
1. wing wingtip reversing sense swirl-flow devices, feature is that two eddy flow covers lay respectively at wing wingtip two ends, and the eddy flow jacket wall has spout in the gap-shaped, and the eddy flow cover is covered with the outer spout of gap-shaped, two spout connecting duct control cock and engine compressor fairlead.
2. wing wingtip reversing sense swirl-flow devices according to claim 1, feature are that outer cover is positioned at eddy flow cover top, pass to the interior spout of eddy flow cover gap-shaped in it and are tangential direction, and the outer spout direction of its outer cover gap-shaped down.
3. wing wingtip reversing sense swirl-flow devices according to claim 1, feature is that eddy flow overlaps cylindrical hollow tubular, and admission port is positioned at eddy flow cover front end, and exhausr port is positioned at eddy flow cover rear end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201405443U CN201023655Y (en) | 2007-03-16 | 2007-03-16 | Wing tip negative direction vortex device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007201405443U CN201023655Y (en) | 2007-03-16 | 2007-03-16 | Wing tip negative direction vortex device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201023655Y true CN201023655Y (en) | 2008-02-20 |
Family
ID=39097506
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007201405443U Expired - Fee Related CN201023655Y (en) | 2007-03-16 | 2007-03-16 | Wing tip negative direction vortex device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201023655Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107848619A (en) * | 2015-07-16 | 2018-03-27 | 四维航空科技有限公司 | The flow of fluid control of wing |
| CN110667820A (en) * | 2019-09-10 | 2020-01-10 | 河南理工大学 | Aircraft wing |
-
2007
- 2007-03-16 CN CNU2007201405443U patent/CN201023655Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107848619A (en) * | 2015-07-16 | 2018-03-27 | 四维航空科技有限公司 | The flow of fluid control of wing |
| US10919618B2 (en) | 2015-07-16 | 2021-02-16 | Fourth Dimensional Aerospace Technology Limited | Fluid flow control for an aerofoil |
| CN107848619B (en) * | 2015-07-16 | 2021-10-26 | 四维航空科技有限公司 | Fluid flow control of an airfoil |
| CN110667820A (en) * | 2019-09-10 | 2020-01-10 | 河南理工大学 | Aircraft wing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| DD01 | Delivery of document by public notice |
Addressee: Lei Liangyu Document name: Notification to Pay the Fees |
|
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080220 Termination date: 20100316 |