CN108750073A - A kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance - Google Patents
A kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance Download PDFInfo
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- CN108750073A CN108750073A CN201810531329.9A CN201810531329A CN108750073A CN 108750073 A CN108750073 A CN 108750073A CN 201810531329 A CN201810531329 A CN 201810531329A CN 108750073 A CN108750073 A CN 108750073A
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- wing
- edge
- leading edge
- leading
- movable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
Abstract
The invention discloses a kind of variable geometry leading edges for taking into account subsonic speed and supersonic speed aeroperformance, belong to flight vehicle aerodynamic design field.The variable geometry leading edge by above and below the leading edge of a wing both sides respectively by connecting rod install one piece of movable leading-edge baffle formed, when carrying out supersonic flight, two pieces of movable leading-edge baffles contact with each other to form the sharp leading edge of a wing, when carrying out subsonic flight, two pieces of movable leading-edge baffles are respectively forwardly translated and are rotated, keep the leading edge of a wing exposed, slotting structure is formed between two pieces of movable leading-edge baffles and the leading edge of a wing.The variable geometry leading edge provided through the invention, the shape of the leading edge of a wing can rationally be changed using two pieces of movable leading-edge baffles according to varying environment during aircraft flight, so that aircraft is obtained higher lift resistance ratio under supersonic speed and subsonic state of flight respectively, advantageously reduces use cost.
Description
Technical field
The invention belongs to flight vehicle aerodynamic design field, it is related to a kind of subsonic speed and supersonic speed aeroperformance taken into account
Variable geometry leading edge, and in particular to a kind of to use the leading edge of a wing of variable-geometry shape to improve aircraft to subsonic speed and Supersonic
The adaptability of fast flying condition takes into account the design of different flying condition pneumatic efficiencies.
Background technology
The influence that the sonic boom generated when in order to reduce flight lives to people, aircraft must not expressly provide to be gathered in the mankind
It occupies area overhead and carries out supersonic flight, therefore in view of Asia-Europe course line and near airports are mostly the land in Close-knit Habitation area, have
The aircraft of supersonic flight ability can only carry out subsonic flight in such region.The ability of aircraft supersonic flight is big
Mostly it is that wing is embodied using the sharp leading edge of a wing, this leading edge of a wing radius using sharp leading edge of a wing wing can be regarded as
It is infinitely small.When aircraft is with subsonic speed state flight, the air-flow being located above sharp leading edge of a wing surface flow stationary point must
It moves upwards around the sharp leading edge of a wing, the infinitesimal sharp leading edge of a wing of leading edge of a wing radius can lead to air-flow and sharp machine
The surface of nose of wing detaches, and generates leading edge and detaches bubble, and leading edge separation bubble can generate under the minimum angle of attack, therefore
Subsonic lift resistance ratio with such sharp leading edge of a wing aircraft is also comparable low, and aircraft is caused to fly in progress subsonic speed
Pneumatic efficiency when row declines, and lift resistance ratio is only capable of reaching the part of the wing using the blunt nosed leading edge of a wing, aircraft flight
Fuel consumption greatly increase, be unfavorable for reduce aircraft use cost.
Therefore, a kind of leading edge of a wing that can effectively take into account subsonic speed and supersonic gas efficiency of movement of exploration is for reducing progress
The aircraft use cost of supersonic flight is significantly.
Invention content
Aircraft is carrying out the drag due to shock wave that the when of can reducing flight using the sharp leading edge of a wing when supersonic flight generates,
Improve lift resistance ratio；And raising lift resistance ratio is more advantageous to using the blunt nosed leading edge of a wing when carrying out subsonic flight.The present invention is from gas
Dynamic design angle sets out, and proposes a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance.By before wing
The mode that two pieces of movable leading-edge baffles are installed in the both sides up and down of edge enables the leading edge of a wing to be converted to the sharp leading edge of a wing, effectively simultaneous
Pneumatic efficiency of the aircraft when carrying out supersonic flight and subsonic flight is cared for.
The variable geometry leading edge is formed by installing one piece of movable leading-edge baffle respectively in the both sides up and down of the leading edge of a wing, and two
Movable leading-edge baffle described in block is connect by respective connecting rod with the leading edge of a wing respectively；Aircraft flies in progress supersonic speed
When row, the rear of two pieces of movable leading-edge baffles fits closely respectively with the both side surface up and down of the leading edge of a wing, two pieces
The leading edge of the movable leading-edge baffle contacts with each other to form the sharp leading edge of a wing of sharp geometric shape；Aircraft is carrying out subsonics
When fast flight, two pieces of movable leading-edge baffles are respectively forwardly translated and are rotated in the case where the connecting rod is pushed outwardly effect, are made
The leading edge of a wing is exposed, and two pieces of movable leading-edge baffles are formed after translating forward and rotating between the leading edge of a wing
Slotting structure, the slotting structure make aircraft in the air-flow for flowed through when subsonic flight the blunt nosed leading edge of a wing surface
It obtains drainage to accelerate, improves lift resistance ratio when aircraft subsonic flight.
The advantage of the invention is that：
The present invention proposes a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance, in aircraft flight mistake
The shape of the leading edge of a wing can rationally be changed in journey using two pieces of movable leading-edge baffles according to varying environment.Fly carrying out supersonic speed
The sharp leading edge of a wing is formed when row reduces wave resistance, increases crack structure using the leading edge of a wing when carrying out subsonic flight, avoids
The leading edge that sharp leading edge of a wing subsonic flight generates detaches bubble, and aircraft is enable in supersonic speed and subsonic to fly respectively
Higher lift resistance ratio is obtained under row state, advantageously reduces use cost.
Description of the drawings
Fig. 1, which is the present invention, has side view of the up-front wing of variable geometry under supersonic mode；
Fig. 2, which is the present invention, has side view of the up-front wing of variable geometry under subsonic mode；
Fig. 3, which is the present invention, has the up-front wing overall top view of variable geometry；
Fig. 4, which is the present invention, has the up-front wing side sectional view of variable geometry；
Fig. 5 is air-flow streamline schematic diagram of the conventionally employed sharp leading edge of a wing under subsonic mode；
Fig. 6 is the air-flow streamline schematic diagram that subsonic flight is carried out using variable geometry leading edge of the present invention；
Fig. 7 is the pressure distribution schematic diagram under supersonic mode using traditional blunt nosed leading edge of a wing；
Fig. 8 is the pressure distribution schematic diagram that supersonic flight is carried out using variable geometry leading edge of the present invention；
In figure：
1, wing；2, the blunt nosed leading edge of a wing；3, movable leading-edge baffle；
4, connecting rod；5, the sharp leading edge of a wing；6, leading edge detaches bubble.
Specific implementation mode
Invention is further explained below in conjunction with the accompanying drawings.
The present invention provides a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance, in conjunction with Fig. 1, Fig. 2, figure
Shown in 3 and Fig. 4, the mode of two pieces of movable leading-edge baffles 3 is installed by using the both sides up and down of the wing 1 in the leading edge of a wing, is made
1 leading edge of wing is converted between the leading edge of a wing and the sharp leading edge of a wing 5, forms variable geometry leading edge.It will be suitable for Supersonic
The sharp leading edge of a wing 5 of speed flight is combined as a whole with the leading edge of a wing suitable for subsonic flight, has effectively taken into account aircraft
Pneumatic efficiency when carrying out supersonic flight and subsonic flight.
The wing 1 of the aircraft uses the leading edge of a wing, and the leading edge of a wing is the blunt nosed leading edge of a wing 2, described blunt nosed
One piece of movable leading-edge baffle 3 is installed in the both sides up and down of the leading edge of a wing 2 respectively, and two pieces of movable leading-edge baffles 3 pass through connecting rod 4
It is connected and fixed with wing 1.One end of the connecting rod 4 is connect with 3 inside of the movable leading-edge baffle, the other end and blunt nosed wing
2 internal slide of leading edge connects, telescopic slide and rotation of the connecting rod 4 relative to wing 1, realizes the translation of movable leading-edge baffle 3
And rotation.
When aircraft is when carrying out supersonic flight, the connecting rod 4 is withdrawn, after two pieces of movable leading-edge baffles 3
Up and down both side surface of the edge respectively with the blunt nosed leading edge of a wing 2 fits closely, the leading edge phase of two pieces of movable leading-edge baffles 3
Mutually contact forms the sharp leading edge of a wing 5.When carrying out subsonic flight, the connecting rod 4 is pushed outwardly aircraft, drives two pieces
The movable leading-edge baffle 3 is translated and is rotated forward, keeps the blunt nosed leading edge of a wing 2 exposed, two pieces of movable leading-edge baffles 3
After translating forward and rotating between the blunt nosed leading edge of a wing 2 the similar leading edge slat of formation slotting structure.Described opens
Crack structure makes aircraft when carrying out subsonic flight, and the air-flow for flowing through 2 surface of the blunt nosed leading edge of a wing obtains drainage acceleration,
Improve lift resistance ratio when aircraft subsonic flight.
Outboard wheel profile of the movable leading-edge baffle 3 in the section along aerofoil profile plane determines that the wing 1 is flying
Device carries out aerodynamic configuration when supersonic flight, when two pieces of movable leading-edge baffles 3 and the blunt nosed leading edge of a wing 2 up and down
When both side surface fits closely, outboard wheel profile of two movable leading-edge baffles 3 in the section along aerofoil profile plane, described in guarantee
The leading edge of a wing of wing 1 forms the sharp leading edge of a wing 5 of sharp geometric shape, and the sharp geometric shape is pointed shape, described
The wedge angle angle of pointed shape meets the aircraft when carrying out supersonic flight, and air-flow bypasses 5 shape of the sharp leading edge of a wing
At forward shock be possession state, the outboard wheel profiles of two pieces of movable leading-edge baffles 3 lateral profile with wing 1 respectively
Line keeps tangent at the upper and lower both side surface place of fitting closely or keeps continual curvature.Since wing 1 generally uses asymmetry up and down
Aerofoil profile, so the curvature of its upper front edge point and lower part also differs, two panels movable leading-edge baffle 3 should be according to respective position
It sets and is designed, need not be designed to completely the same shape and structure.
The inside contour line of two pieces of movable leading-edge baffles 3 by movable leading-edge baffle 3 structural strength size and can
Space size between dynamic leading edge baffle 3 and wing 1 is determined, non-interference between two pieces of movable leading-edge baffles 3 and wing 1,
The continuity that fairing processing ensures surface curvature is carried out respectively to the inside contour line of two pieces of movable leading-edge baffles 3 simultaneously, is avoided
There is the flow separation that broken line causes air-flow additional in the subsonic speed stage in the inner surface of two pieces of movable leading-edge baffles 3.
For aircraft when carrying out subsonic flight, two pieces of movable leading-edge baffles 3 are pushed outwardly work in the connecting rod 4
It respectively forwardly translates and rotates under, keep the blunt nosed leading edge of a wing 2 exposed, be located at the leading edge of a wing or more both side surface along spanwise
Different location on be respectively disposed at least two connecting rods 4, the movable leading-edge for being located at connecting rod 4 and the top of uper side surface is kept off
Plate 3 connects, and the connecting rod 4 for being located at downside surface is connect with the movable leading-edge baffle 3 of lower section, two pieces of movable leading-edge baffles 3
After respectively forwardly translating and rotating under the connecting rod 4 is pushed outwardly effect class is formed between the blunt nosed leading edge of a wing 2
Like the slotting structure of leading edge slat, the slotting structure that the variable geometry leading edge is formed makes aircraft when carrying out subsonic flight
The air-flow for flowing through 2 surface of the blunt nosed leading edge of a wing obtains drainage acceleration, improves lift resistance ratio when aircraft subsonic flight.
Aircraft is located at the blunt nosed leading edge of a wing 2 of about 1 both sides leading edge of a wing part of wing when carrying out supersonic flight
Formed the sharp leading edge of a wing 5 after being covered by two pieces of movable leading-edge baffles 3, the length of two pieces of movable leading-edge baffles 3 respectively with wing 1
Spanwise length it is equal, if for aircraft itself it is special structure arrangement demand and pneumatic details demand consider, can also
Using the length for being slightly less than the span.Connecting rod 4 is fully located at two pieces of 3 insides of movable leading-edge baffle, as shown in figure 3, arrow direction
Indicate air direction of flow.The thin in profile of two pieces of movable leading-edge baffles 3 and both ends are more sharp, in concrete application,
In the subsonic speed stage, setting angle after cracking is improper to cause 3 surface of movable leading-edge baffle to generate additional flow separation.Therefore
Leading edge caused by eliminating movable leading-edge baffle 3 should be followed when the position of design subsonic speed state movable leading-edge baffle 3 detaches this
Principle should control the established angle of movable leading-edge baffle 3 if can not eliminate the leading edge by adjusting setting angle detaches bubble 6
Leading edge separation bubble 6 is decreased to minimum by degree, is changed to the installation site of movable leading-edge baffle 3 as design considerations
In generation, determines.
Embodiment 1：When free stream Mach number 0.3, Reynolds number 6.5 × 10 is flowed6, when 6 ° of the incoming angle of attack, to the machine of aircraft
Nose of wing carries out calculating verification.As known by the technical knowledge, aerofoil profile is that wing is parallel to each of the aircraft plane of symmetry in the spanwise direction
The section of wing in a plane is equal to aerofoil profile progress flow analysis and analyzes flowing of the wing in some section.
Fig. 5 is air-flow streamline schematic diagram of the conventionally employed sharp leading edge of a wing under subsonic mode, 5 surface of the sharp leading edge of a wing
It generates leading edge and detaches bubble 6, lift resistance ratio is low when aircraft carries out subsonic flight, is existed using traditional sharp leading edge of a wing 5
The lift coefficient of state of flight is 0.77124 under the conditions of provided in this embodiment, and resistance coefficient 0.022767, lift resistance ratio only has
33.8；As shown in fig. 6, to carry out the air-flow streamline schematic diagram of subsonic flight using variable geometry leading edge of the present invention, before movable
Edge baffle 3 is in stretching state, and the installation site and angle of movable leading-edge baffle 3 are set in method provided by the invention
Meter allows the leading edge on 3 surface of movable leading-edge plate washer to detach bubble 6 and is eliminated and is ensuring that leading edge do not occur in movable leading-edge baffle 3
Keep movable leading-edge baffle 3 minimum at a distance from 1 surface of wing under the premise of separation bubble 6.It is learnt by design underlying
The leading edge cusp of movable leading-edge baffle is 0.049 times of main wing chord length apart from blunt nosed leading edge of a wing point length, with airfoil chord wire clamp angle
It it is 29 °, the length of the leading edge cusp of the movable leading-edge baffle being located above apart from blunt nosed leading edge of a wing point is 0.070 times of main wing string
It is long, it is 33 ° with airfoil chord wire clamp angle, result of calculation, which is shown, is using the up-front airfoil lift coefficient of variable geometry of the present invention
0.85875, resistance coefficient 0.011249, lift resistance ratio is up to 76.3, while the leading edge separation bubble 6 on leading edge of a wing surface is disappeared
It removes, air-flow becomes attachment state.By comparison it is found that under the same terms, when aircraft carries out subsonic flight, this hair is used
The bright up-front wing lift resistance ratio of variable geometry is using 2.3 times of traditional sharply wing lift resistance ratio of the leading edge of a wing, this shows this
The variable geometry leading edge design of invention is effective.According to the prior art it is found that the wing of the blunt nosed leading edge of a wing of tradition flies herein
Lift resistance ratio when subsonic flight is carried out under row environment 80 or so, using the up-front wing of variable geometry of the present invention in this state
It is lower carry out subsonic flight lift resistance ratio be sufficiently close to traditional wing using the blunt nosed leading edge of a wing in this case into
The lift resistance ratio of row subsonic flight.
Embodiment 2：When free stream Mach number 2.2, Reynolds number 3.2 × 10 is flowed7, when 2 ° of the incoming angle of attack, to the machine of aircraft
Nose of wing carries out calculating verification.It is illustrated in figure 7 pressure of the conventionally employed blunt nosed leading edge of a wing under supersonic mode point
Cloth schematic diagram, the apparent pressure line of demarcation in leading edge of a wing front is shock wave, and shock wave shows bowed shape, brings larger
Drag due to shock wave be using lift coefficient of the wing of the blunt nosed leading edge of a wing in aircraft supersonic flight in this case
0.13917, resistance coefficient 0.17941, lift resistance ratio 0.78；Fig. 8 is to carry out supersonic speed using variable geometry leading edge of the present invention
The pressure distribution schematic diagram of flight will keep it close using the withdrawal of movable leading-edge baffle 3 of the wing of variable geometry leading edge design
It is fitted in the surface of the leading edge of a wing, forms 45 degree of wedge angles between upper and lower 2 pieces of movable leading-edge baffles 3, profile of shock wave is and object table
The wedge shape of face contact, shock wave become oblique shock wave, and drag due to shock wave is reduced, in this case, existed using the up-front wing of variable geometry
Lift coefficient when aircraft supersonic flight is 0.21949, resistance coefficient 0.077297, lift resistance ratio 2.84, is to use
3.6 times of the wing lift resistance ratio of the blunt nosed leading edge of a wing of tradition.Therefore, provided by the invention to take into account subsonic speed and the pneumatic property of supersonic speed
The variable geometry leading edge of energy can effectively enhance aircraft to two kinds of flight speed of subsonic speed and supersonic speed by change shape
The adaptability of degree.
In conclusion the present invention proposes a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance, flying
Can rationally change the shape of the leading edge of a wing using two pieces of movable leading-edge baffles according to varying environment in row device flight course, into
The sharp leading edge of a wing is formed when row supersonic flight reduces wave resistance, forms the blunt nosed leading edge of a wing when carrying out subsonic flight, keeps away
The leading edge separation bubble that sharp leading edge of a wing subsonic flight generates is exempted from, has enable aircraft respectively in supersonic speed and subsonic speed
State of flight under obtain higher lift resistance ratio, advantageously reduce use cost.
It is studied just for embodiment example, for the aerofoil profile of other design conditions and other aircraft, is answered above
The installation site and rotation angle for determining movable leading-edge baffle according to design method again are made a concrete analysis of, it is overall to obey as far as possible
Make the leading edge separation bubble collapse or minimum design rule that movable leading-edge baffle generates.
As known by the technical knowledge, the present invention can not depart from the embodiment party of its theoretical essence or essential feature by others
Case is realized.Therefore, concrete scheme mentioned above is merely illustrative, not the only.The design method of the present invention is suitable
The design of the leading edge of a wing of the aircraft with supersonic flight ability for any size, it is all in the claims in the present invention
Protection domain in or the change that is equal in protection scope of the present invention be included in the invention.
Claims (5)
1. a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance, which is characterized in that before the variable geometry
Cause both sides above and below the leading edge of a wing are installed one piece of movable leading-edge baffle and are formed respectively, the inside of two pieces of movable leading-edge baffles
It is connect respectively with the leading edge of a wing by respective connecting rod；When carrying out supersonic flight, two pieces of movable leading-edge gears
Up and down both side surface of the rear of plate respectively with the blunt nosed leading edge of a wing fits closely respectively, two pieces of movable leading-edge baffles
Leading edge contact with each other, form the sharp leading edge of a wing of sharp geometric shape；When carrying out subsonic flight, two pieces described movable
Leading edge baffle is respectively forwardly translated and is rotated in the case where the connecting rod is pushed outwardly effect, keeps the leading edge of a wing exposed, described in two pieces
Slotting structure is formed between movable leading-edge baffle and the leading edge of a wing.
2. a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance as described in claim 1, feature exist
In the leading edge of a wing is the blunt nosed leading edge of a wing.
3. a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance as described in claim 1, feature exist
In, two pieces of movable leading-edge baffle sections outboard wheel profile respectively with the outboard wheel profile of wing profile, in upper and lower both sides
The surface place of fitting closely keeps tangent or keeps continual curvature.
4. a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance as described in claim 1, feature exist
When, two pieces of movable leading-edge baffles movements non-interference, two pieces of movable leading-edge baffles between the leading edge of a wing
The inside contour line of section distinguishes continual curvature.
5. a kind of variable geometry leading edge for taking into account subsonic speed and supersonic speed aeroperformance as described in claim 1, feature exist
In, two pieces of movable leading-edge baffles length no more than wing spanwise length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201810531329.9A CN108750073B (en) | 2018-05-29 | 2018-05-29 | Variable wing leading edge with both subsonic and supersonic aerodynamic performance |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810531329.9A CN108750073B (en) | 2018-05-29 | 2018-05-29 | Variable wing leading edge with both subsonic and supersonic aerodynamic performance |
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| CN108750073A true CN108750073A (en) | 2018-11-06 |
| CN108750073B CN108750073B (en) | 2020-06-23 |
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Cited By (4)
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| CN111734678A (en) * | 2020-06-24 | 2020-10-02 | 西北工业大学 | Design method for asymmetric leading edge of compressor blade profile |
| CN114987735A (en) * | 2022-08-08 | 2022-09-02 | 中国空气动力研究与发展中心计算空气动力研究所 | Method for determining wide-speed-range low-sonic-explosion low-resistance wing profile and state configuration |
| CN115946842A (en) * | 2023-03-10 | 2023-04-11 | 中国空气动力研究与发展中心计算空气动力研究所 | Damping device of aircraft and aircraft |
| WO2023109154A1 (en) * | 2021-12-15 | 2023-06-22 | 北京航空航天大学宁波创新研究院 | Wing and method for improving control efficiency of two-dimensional airfoil rudder surface |
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| Publication number | Publication date |
|---|---|
| CN108750073B (en) | 2020-06-23 |
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