CN110435873A - A kind of half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race cruised from trim - Google Patents
A kind of half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race cruised from trim Download PDFInfo
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- CN110435873A CN110435873A CN201910752594.4A CN201910752594A CN110435873A CN 110435873 A CN110435873 A CN 110435873A CN 201910752594 A CN201910752594 A CN 201910752594A CN 110435873 A CN110435873 A CN 110435873A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
Abstract
The present invention provides a kind of half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race that can be cruised from trim, including the first aerofoil profile, the second aerofoil profile and third aerofoil profile；First aerofoil profile, the exhibition of the second aerofoil profile and third aerofoil profile on wing are respectively as follows: the first aerofoil profile to position and are located at airfoil root, and the second aerofoil profile is located at wing and opens up at 28.1%, and third aerofoil profile is located at wing ending；The maximum relative thickness of first aerofoil profile, the second aerofoil profile and third aerofoil profile is respectively 14.00%, 11.00%, 11.90%；The relative position of maximum gauge is respectively 30.60%, 30.60%, 33.90%.Have the advantage that family of aerofoil sections provided by the invention is designed for the cruising condition of tailless configuration's unmanned plane, under low mach and low reynolds number, unmanned plane realizes that cruise from trim, has the characteristics that high-lift, lower resistance, high lift-drag ratio, stalling characteristics mitigate.
Description
Technical field
The invention belongs to aerodynamic configuration/Airfoil Design technical fields, and in particular to the half wing body that one kind can cruise from trim
Merge anury formula Unmanned Aerial Vehicle Airfoil race.
Background technique
Unmanned air vehicle technique worldwide flourishes, and it is wide to continue to bring out out different properties, technologically advanced and purposes
General unmanned plane.Unmanned plane has many advantages, such as that mobility strong, efficiency-cost ratio be high, using flexible, with the continuous development of modern technologies,
Unmanned plane is all widely used in civil and military field.In order to improve the cruise performance of unmanned plane, can cruise autogamy
Flat ability is particularly important in the use of unmanned plane.
Half wing body fusion type unmanned plane smoothly transits traditional fuselage with wing, adds wing cloth with traditional column fuselage
Office aircraft compare, have many advantages, such as that integrated molding, aerodynamic efficiency are high, have in dual-use field it is good before
Scape.
Aerofoil profile is the basis of craft wing design, and Airfoil Design success or not fundamentally determines the success or failure of airplane design.
And China carried out research without the high cruise performance aerofoil profile of systematically double of blended wing-body anury formula unmanned plane up to now.For
Further increase half blended wing-body anury formula unmanned plane operational performance and widely used property, currently, promoting it in cruise shape
Aeroperformance under state is particularly important.
Summary of the invention
In view of the defects existing in the prior art, the present invention provide it is a kind of can cruise from half blended wing-body anury formula of trim without
Man-machine family of aerofoil sections can effectively solve the above problems.
The technical solution adopted by the invention is as follows:
The present invention provides a kind of half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race that can be cruised from trim, including first wing
Type, the second aerofoil profile and third aerofoil profile；
First aerofoil profile, the exhibition of second aerofoil profile and the third aerofoil profile on wing are respectively as follows: described to position
First aerofoil profile is located at airfoil root, and second aerofoil profile is located at wing and opens up at 28.1%, and the third aerofoil profile is located at wing slightly
Portion；
The maximum relative thickness of first aerofoil profile, second aerofoil profile and the third aerofoil profile is respectively 14.00%,
11.00%, 11.90%；The relative position of maximum gauge is respectively 30.60%, 30.60%, 33.90%；Wherein, the maximum
The ratio of relative thickness maximum distance and the length of string between each aerofoil profile upper and lower surfaces, the chord length are that aerofoil profile leading edge arrives
The length of the string of rear；
First aerofoil profile, the opposite camber of the maximum of second aerofoil profile and the third aerofoil profile be respectively 2.168%,
2.167%, 1.598%, the relative position of maximum camber is respectively 18.00%, 17.90%, 36.80%；
The leading-edge radius of first aerofoil profile, second aerofoil profile and the third aerofoil profile is respectively 1.234%,
0.736%, 0.972%；
First aerofoil profile, second aerofoil profile and the third aerofoil profile are blunt trailing edge, and rear thickness is respectively
0.626%, 0.492%, 0.0%；
The torsion angle of first aerofoil profile, second aerofoil profile and the third aerofoil profile is respectively 1 degree, and 1 degree, -7 spend.
Preferably, the dimensionless geometric coordinate of first aerofoil profile are as follows:
Wherein, x/c value indicate on Curve of wing certain point on string direction relative to up-front position, y/c value indicate from
The height that certain is put on string to Curve of wing, is positive above string, is negative below string.
Preferably, the dimensionless geometric coordinate of second aerofoil profile are as follows:
Wherein, x/c value indicate on Curve of wing certain point on string direction relative to up-front position, y/c value indicate from
The height that certain is put on string to Curve of wing, is positive above string, is negative below string.
Preferably, the dimensionless geometric coordinate of the third aerofoil profile are as follows:
Wherein, x/c value indicate on Curve of wing certain point on string direction relative to up-front position, y/c value indicate from
The height that certain is put on string to Curve of wing, is positive above string, is negative below string.
One kind provided by the invention can cruise have from half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race of trim it is following excellent
Point:
It is 11.00%~14.00% the invention proposes a kind of maximum relative thickness, lays particular emphasis on the aerofoil profile of cruising characteristics
Race.The family of aerofoil sections has ability of the cruise from trim, determines pitching moment when lift coefficient is 0.35 in cruise point and is only
0.0003275, torque inflection point is greater than 12 degree.
Family of aerofoil sections provided by the invention is designed for the cruising condition of tailless configuration's unmanned plane, in low mach and low
Under Reynolds number, unmanned plane realizes that cruise from trim, has the characteristics that high-lift, lower resistance, high lift-drag ratio, stalling characteristics mitigate.
Detailed description of the invention
Fig. 1 is half blended wing-body anury formula unmanned plane of anury swept-wing layout provided by the invention under an angle
Model line chart；To be respectively each aerofoil profile open up in the unmanned plane wing to using position view thick line in figure；
Fig. 2 is half blended wing-body anury formula unmanned plane of anury swept-wing layout provided by the invention under another angle
Model line chart；To be respectively each aerofoil profile open up in the unmanned plane wing to using position view thick line in figure；
Fig. 3 is the model entity figure of half blended wing-body anury formula unmanned plane of anury swept-wing layout provided by the invention；
Fig. 4 is the combination of half blended wing-body anury formula unmanned plane special airfoil race of anury swept-wing layout of the invention
Figure；
Fig. 5 is first wing in half blended wing-body anury formula unmanned plane special airfoil race of anury swept-wing layout of the invention
The silhouette contrast figure of type and initial aerofoil profile；
Fig. 6 is second wing in half blended wing-body anury formula unmanned plane special airfoil race of anury swept-wing layout of the invention
The silhouette contrast figure of type and initial aerofoil profile；
Fig. 7 is the third wing in half blended wing-body anury formula unmanned plane special airfoil race of anury swept-wing layout of the invention
The silhouette contrast figure of type and initial aerofoil profile；
Fig. 8 is first wing in half blended wing-body anury formula unmanned plane special airfoil race of anury swept-wing layout of the invention
The lift coefficient C of first aerofoil profile in type and original configuration family of aerofoil sectionsLWith angle of attack variation curve graph；
Fig. 9 be anury swept-wing layout of the invention half wing body fusion type unmanned plane special airfoil race in the first aerofoil profile with
The resistance coefficient C of first aerofoil profile in original configuration family of aerofoil sectionsDWith angle of attack variation curve graph；
Figure 10 is the first aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
With the pitching moment coefficient C of the first aerofoil profile in original configuration family of aerofoil sectionsmWith angle of attack variation curve graph；
Figure 11 is the first aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
Lift resistance ratio K with the first aerofoil profile in original configuration family of aerofoil sections is with angle of attack variation curve graph；
Figure 12 is the second aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
With the lift coefficient C of the second aerofoil profile in original configuration family of aerofoil sectionsLWith angle of attack variation curve graph；
Figure 13 is the second aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
With the resistance coefficient C of the second aerofoil profile in original configuration family of aerofoil sectionsDWith angle of attack variation curve graph；
Figure 14 is the second aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
With the pitching moment coefficient C of the second aerofoil profile in original configuration family of aerofoil sectionsmWith angle of attack variation curve graph；
Figure 15 is the second aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
Lift resistance ratio K with the second aerofoil profile in original configuration family of aerofoil sections is with angle of attack variation curve graph；
Figure 16 is third aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
With the lift coefficient C of third aerofoil profile in original configuration family of aerofoil sectionsLWith angle of attack variation curve graph；
Figure 17 is third aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
With the resistance coefficient C of third aerofoil profile in original configuration family of aerofoil sectionsDWith angle of attack variation curve graph；
Figure 18 is third aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
With the pitching moment coefficient C of third aerofoil profile in original configuration family of aerofoil sectionsmWith angle of attack variation curve graph；
Figure 19 is third aerofoil profile in the half wing body fusion type unmanned plane special airfoil race of anury swept-wing layout of the invention
Lift resistance ratio K with third aerofoil profile in original configuration family of aerofoil sections is with angle of attack variation curve graph；
Figure 20 is the lift coefficient C of the full mechanism type being made of family of aerofoil sections of the invention and initial full mechanism typeLWith the angle of attack
The comparison diagram of variation；
Figure 21 is the resistance coefficient C of the full mechanism type being made of family of aerofoil sections of the invention and initial full mechanism typeDWith the angle of attack
The comparison diagram of variation；
Figure 22 is the pitching moment coefficient C of the full mechanism type being made of family of aerofoil sections of the invention and initial full mechanism typemWith
The comparison diagram of angle of attack variation；
Figure 23 is the lift resistance ratio K for the full mechanism type and initial full mechanism type being made of family of aerofoil sections of the invention with angle of attack variation
The comparison diagram of curve；
Figure 24 is the full mechanism type being made of family of aerofoil sections of the invention, the initial complete resulting swirl distribution of mechanism type and ellipse
The comparison diagram of swirl distribution, in figure abscissa be opened up along wing to relative position, ordinate is true circular rector.
Specific embodiment
In order to which the technical problems, technical solutions and beneficial effects solved by the present invention is more clearly understood, below in conjunction with
Accompanying drawings and embodiments, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
It explains the present invention, is not intended to limit the present invention.
Half blended wing-body anury formula unmanned plane can reduce resistance using anury swept-wing layout, improve lift resistance ratio, improve
Its aeroperformance.Meanwhile the half wing body fusion type unmanned plane of anury swept-wing layout Challenge in the design process: flight
Device need to awing keep good stability and control, and tailless configuration causes due to not having horizontal tail to provide trim ability
Aircraft cannot cruise in flight course from trim.Present invention is generally directed to aircraft cruising condition autogamy square faces to be changed
Into.The present invention provides a kind of half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race that can be cruised from trim, which, which lays particular emphasis on, patrols
Boat characteristic, under the premise of meeting cruise from trim, in cruise point lift coefficient with higher and a lift resistance ratio performance.
Specifically, the invention enables family of aerofoil sections to meet cruise from trim by using advanced Airfoil Design technology
Under the premise of, can have higher under lower design lift coefficient, lower flight Mach number and lower flight Reynolds number
Lift resistance ratio for cruising condition, carry out family of aerofoil sections design, index request to improve cruise efficiency are as follows:
1. pitching moment C under cruising conditionm≈0±0.015；
2. the working condition of the half wing body fusion type unmanned plane of anury swept-wing layout is as follows:
Cruising condition: Ma=0.1, Re=2.33E6, CL=0.35；
According to above-mentioned design objective, the present invention uses computer hydrodynamic methods, and design point lays particular stress on cruise point, proposes
A kind of half wing body fusion type unmanned plane suitable for anury swept-wing layout lays particular emphasis on cruising characteristics, can cruise from trim, high
Lift, lower resistance, high lift-drag ratio family of aerofoil sections.
The geometric parameter of each aerofoil profile is as shown in Table 1 and Table 2 in family of aerofoil sections of the present invention and initial family of aerofoil sections:
Table 1: the geometric parameter of each aerofoil profile in family of aerofoil sections is improved
First aerofoil profile, second aerofoil profile and the third aerofoil profile provided by the invention, torsion angle are respectively 1 degree, and 1
Degree, -7 degree.
Table 2: the geometric parameter of each aerofoil profile in initial family of aerofoil sections
In description of the invention and attached drawing, improving aerofoil profile is the first aerofoil profile, the second aerofoil profile and that the present invention designs
Three aerofoil profiles.And initial aerofoil profile is aerofoil profile in the prior art.
First aerofoil profile, the second aerofoil profile and third aerofoil profile provided by the invention, the dimensionless number of each aerofoil profiles is according to such as following table
It is shown:
The dimensionless geometric coordinate of first aerofoil profile of the invention are as follows:
The dimensionless geometric coordinate of second aerofoil profile of the invention are as follows:
The dimensionless geometric coordinate of third aerofoil profile of the present invention are as follows:
Wherein, x/c value indicates that certain is put on string direction relative to up-front position on Curve of wing；Y/c value indicate from
The height that certain is put on string to Curve of wing, is positive above string, is negative below string.In table dimensionless coordinate order from
Aerofoil profile trailing edge (x/c=1) starts, and arrives forward along pressure leading edge (x/c=0), then return to trailing edge (x/c from leading edge along suction surface
=1) until.
- Fig. 3 referring to Fig.1, it is shown that each aerofoil profile the half wing body fusion type unmanned plane wing of anury swept-wing layout open up to
Position view, first aerofoil profile, the exhibition of second aerofoil profile and the third aerofoil profile on wing are respectively as follows: to position
One aerofoil profile is located at airfoil root, and the second aerofoil profile is located at wing and opens up at 28.1%, and third aerofoil profile is located at wing ending.Fig. 3 is shown
The half wing body fusion type unmanned plane model entity figure of anury swept-wing layout, is easier to find out wing and fuselage semi-fusion.
Referring to Fig. 4, Fig. 4 gives the constitutional diagram of each aerofoil profile in family of aerofoil sections of the present invention, at the same the present invention obtain it is different open up to
The silhouette contrast figure of aerofoil profile and initial aerofoil profile at position, as shown in Fig. 5~7.
Fig. 8-Figure 11, it is shown that the aerodynamic characteristic correlation curve of the first aerofoil profile and initial aerofoil profile of the invention.Figure 12-15 is shown
The aerodynamic characteristic correlation curve of the second aerofoil profile and initial aerofoil profile of the invention is shown.Figure 16-19, it is shown that third aerofoil profile of the present invention with
The aerodynamic characteristic correlation curve of initial aerofoil profile.It successively include: lift coefficient C for every group of aerodynamic characteristic correlation curveLWith the angle of attack
Change curve；Resistance coefficient CDWith angle of attack variation curve；Pitching moment coefficient CmWith angle of attack variation curve；Lift resistance ratio K becomes with the angle of attack
Change curve.
Figure 20-Figure 23, the pneumatic spy of the full mechanism type being respectively made of family of aerofoil sections of the invention and initial full mechanism type
Property comparison diagram (is successively: lift coefficient CLWith angle of attack variation curve；Resistance coefficient CDWith angle of attack variation curve；Pitching moment coefficient
CmWith angle of attack variation curve；Lift resistance ratio K is with angle of attack variation curve).As can be seen from Fig.: full mechanism type of the invention and initial complete
Mechanism type is compared, and after 0 degree of the angle of attack, resistance coefficient is reduced；In cruise point CLAt=0.35, resistance coefficient variation is little, but
Being pitching moment coefficient becomes 0.0003275 from -0.02654, and unmanned plane can realize that cruise from trim, reduces trim resistance.
Figure 24 gives initial full mechanism type and the full mechanism type being made of family of aerofoil sections of the invention in cruising condition, i.e., fixed
Lift CLOval swirl distribution in swirl distribution and ideal at=0.35, as can be seen from Figure 24, by the wing of the invention
The obtained swirl distribution of full mechanism type that type race is constituted is closer to oval swirl distribution, wherein opening up along wing to relative position
It is that swirl distribution within 0.6 is overlapped with oval swirl distribution substantially, therefore greatly reduces induced drag.
It can be seen that the half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race provided by the invention cruised from trim, is needle
The cruising condition of tailless configuration's unmanned plane is designed, under low mach and low reynolds number, unmanned plane, which is realized, to cruise from trim,
Have the characteristics that high-lift, lower resistance, high lift-drag ratio, stalling characteristics mitigate.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
Depending on protection scope of the present invention.
Claims (4)
- The half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race from trim 1. one kind can cruise, which is characterized in that including the first aerofoil profile, Second aerofoil profile and third aerofoil profile；The exhibition of first aerofoil profile, second aerofoil profile and the third aerofoil profile on wing is respectively as follows: described first to position Aerofoil profile is located at airfoil root, and second aerofoil profile is located at wing and opens up at 28.1%, and the third aerofoil profile is located at wing ending；The maximum relative thickness of first aerofoil profile, second aerofoil profile and the third aerofoil profile is respectively 14.00%, 11.00%, 11.90%；The relative position of maximum gauge is respectively 30.60%, 30.60%, 33.90%；Wherein, the maximum The ratio of relative thickness maximum distance and the length of string between each aerofoil profile upper and lower surfaces, the chord length are that aerofoil profile leading edge arrives The length of the string of rear；First aerofoil profile, the opposite camber of the maximum of second aerofoil profile and the third aerofoil profile be respectively 2.168%, 2.167%, 1.598%, the relative position of maximum camber is respectively 18.00%, 17.90%, 36.80%；The leading-edge radius of first aerofoil profile, second aerofoil profile and the third aerofoil profile is respectively 1.234%, 0.736%, 0.972%；First aerofoil profile, second aerofoil profile and the third aerofoil profile are blunt trailing edge, rear thickness is respectively 0.626%, 0.492%, 0.0%；The torsion angle of first aerofoil profile, second aerofoil profile and the third aerofoil profile is respectively 1 degree, and 1 degree, -7 spend.
- The half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race from trim 2. one kind according to claim 1 can cruise, it is special Sign is, the dimensionless geometric coordinate of first aerofoil profile are as follows:Wherein, x/c value indicates that relative to up-front position on string direction, y/c value is indicated from string certain point on Curve of wing The height that certain is put on to Curve of wing, is positive above string, is negative below string.
- The half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race from trim 3. one kind according to claim 1 can cruise, it is special Sign is, the dimensionless geometric coordinate of second aerofoil profile are as follows:Wherein, x/c value indicates that relative to up-front position on string direction, y/c value is indicated from string certain point on Curve of wing The height that certain is put on to Curve of wing, is positive above string, is negative below string.
- The half blended wing-body anury formula Unmanned Aerial Vehicle Airfoil race from trim 4. one kind according to claim 1 can cruise, it is special Sign is, the dimensionless geometric coordinate of the third aerofoil profile are as follows:Wherein, x/c value indicates that relative to up-front position on string direction, y/c value is indicated from string certain point on Curve of wing The height that certain is put on to Curve of wing, is positive above string, is negative below string.
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| CN111348175A (en) * | 2020-01-13 | 2020-06-30 | 北京航空航天大学 | Special airfoil profile matched with high-universality large-loading small-sized unmanned aerial vehicle |
| CN111498085A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | High-altitude long-endurance unmanned aerial vehicle wing suitable for lower single-wing layout |
| CN112478127A (en) * | 2020-12-04 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Flying wing unmanned aerial vehicle with geometry twists reverse structure |
| CN112849387A (en) * | 2021-01-22 | 2021-05-28 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
| CN114572340A (en) * | 2022-04-18 | 2022-06-03 | 西北工业大学 | Family of underwater high-lift low-cavitation airfoil |
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| CN111348175A (en) * | 2020-01-13 | 2020-06-30 | 北京航空航天大学 | Special airfoil profile matched with high-universality large-loading small-sized unmanned aerial vehicle |
| CN111498085A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | High-altitude long-endurance unmanned aerial vehicle wing suitable for lower single-wing layout |
| CN112478127A (en) * | 2020-12-04 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Flying wing unmanned aerial vehicle with geometry twists reverse structure |
| CN112849387A (en) * | 2021-01-22 | 2021-05-28 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
| CN112849387B (en) * | 2021-01-22 | 2022-11-08 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
| CN114572340A (en) * | 2022-04-18 | 2022-06-03 | 西北工业大学 | Family of underwater high-lift low-cavitation airfoil |
| CN114572340B (en) * | 2022-04-18 | 2023-02-03 | 西北工业大学 | Family of underwater high-lift low-cavitation airfoil |
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| CN110435873B (en) | 2021-04-23 |
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