CN103587678B - A kind of thin circular arc airfoil with convex configuration - Google Patents
A kind of thin circular arc airfoil with convex configuration Download PDFInfo
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- CN103587678B CN103587678B CN201310506604.9A CN201310506604A CN103587678B CN 103587678 B CN103587678 B CN 103587678B CN 201310506604 A CN201310506604 A CN 201310506604A CN 103587678 B CN103587678 B CN 103587678B
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Abstract
There is a thin circular arc airfoil for convex configuration, relate to aerodynamics and field of fluid mechanics, solve the problem that lift coefficient is low, aerodynamics noise is high that existing aerofoil profile exists.This aerofoil profile is made up of leading edge, the first upper surface circular arc, First Transition fillet, protruding circular arc, the second knuckle, the second upper surface circular arc, trailing edge, lower surface circular arc and reinforced rib, loop curve is in turn connected to form according to the order of leading edge, the first upper surface circular arc, First Transition fillet, protruding circular arc, the second knuckle, the second upper surface circular arc, trailing edge, lower surface circular arc, leading edge, reinforced rib is arranged between protruding circular arc and lower surface circular arc, and the line on the summit of described leading edge and the summit of trailing edge is the string of a musical instrument.Thin circular arc airfoil of the present invention has high coefficient of lift combined, low pneumatic noise, high structural strength simultaneously and is convenient to the features such as manufacture.
Description
Technical field
The present invention relates to aerodynamics and hydrodynamics technology field, be specifically related to a kind of thin circular arc airfoil with convex configuration.
Background technology
Microminiature rotorcraft has the abilities such as vertical takeoff and landing, hovering and low-speed operations, is particularly suitable for completing appointed task under narrow environment, is subject to the extensive concern of research institution of various countries and company.Rotor is the lifting surface of aircraft, and be also controlsurface and propulsive force face, the performance of rotor directly affects the performance of whole aircraft.Aerofoil profile is the two dimensional cross-section of rotor, is to embody the root that rotor upper and lower surface produces difference of pressure, and it has material impact to the size of rotor lift or thrust, aerodynamics noise size and even aircraft performance.Microminiature rotor size is little, speed is low, and under causing rotor to be operated in lower Reynolds number Airflow Environment, Reynolds number is generally 10
4~ 10
6, even lower.Under low reynolds number Airflow Environment, the lift coefficient of conventional aerofoil profile sharply declines, and under not being suitable for low reynolds number Airflow Environment, rotor uses.Adopt low Reynolds number airfoil as flat profile, there is the flat profile of camber, NACA series thin airfoil makes rotor, in order to improve lift coefficient, profile thickness is less, but less profile thickness, causes the structural strength of rotor low, can produce bad pneumatic distortion during rotor High Rotation Speed, rotor lift reduces, aeroperformance is deteriorated, and affects the Control platform of aircraft and the raising of overall performance.In addition, tooling cost is also the problem that small-sized introducing to the market of rotor craft emphasis is considered.Therefore, develop a kind of there is high lift coefficient, low pneumatic noise and high structural strength simultaneously and be convenient to the low reynolds number Airfoil that manufactures to improve small-sized rotor craft overall performance, to expand the application of Microminiature rotorcraft most important.
Summary of the invention
In order to solve existing aerofoil profile exist the problem that lift coefficient is low, aerodynamics noise is high, the invention provides a kind of there is high coefficient of lift combined, low pneumatic noise, high structural strength simultaneously and be convenient to manufacture the thin circular arc airfoil with convex configuration.
The technical scheme that the present invention adopts for technical solution problem is as follows:
A kind of thin circular arc airfoil with convex configuration, this aerofoil profile is made up of leading edge, the first upper surface circular arc, First Transition fillet, protruding circular arc, the second knuckle, the second upper surface circular arc, trailing edge, lower surface circular arc and reinforced rib, be in turn connected to form loop curve according to the order of leading edge, the first upper surface circular arc, First Transition fillet, protruding circular arc, the second knuckle, the second upper surface circular arc, trailing edge, lower surface circular arc, leading edge, reinforced rib is arranged between protruding circular arc and lower surface circular arc;
The line on the summit of described leading edge and the summit of trailing edge is the string of a musical instrument;
Described First Transition fillet is identical with the radius of curvature of the second knuckle;
The radius of curvature of described First Transition fillet and the second knuckle is all more than or equal to the radius of curvature of protruding circular arc;
Described first upper surface circular arc, the second upper surface circular arc and lower surface circular arc are circular arc;
Described first upper surface circular arc is identical with the radius of curvature of the second upper surface circular arc and the center of circle of respective place circle.
Described leading edge is made up of the part-elliptical comprising a major semiaxis end points, and the summit of leading edge is an end points of the major semiaxis of this part-elliptical;
The length c relation of the projected length m of described leading edge on string of a musical instrument direction and the string of a musical instrument meets: 0.08≤m/c≤0.15;
Described leading edge and all have knuckle between the first upper surface circular arc and lower surface circular arc, the radius of curvature of this knuckle is less than or equal to the radius of curvature of protruding circular arc.
Described trailing edge is made up of the part-elliptical comprising a major semiaxis end points, and the summit of trailing edge is an end points of the major semiaxis of this part-elliptical, or trailing edge is made up of two limits comprising an acute angle, and the summit of trailing edge is the summit of this acute angle;
The length c relation of the projected length n of described trailing edge on string of a musical instrument direction and the string of a musical instrument meets: 0.04≤n/c≤0.1;
The difference t of the radius of curvature of the projected length n of described trailing edge on string of a musical instrument direction and the first upper surface circular arc and lower surface circular arc meets: 2≤n/t≤4;
Described trailing edge and all have knuckle between the first upper surface circular arc and lower surface circular arc, the radius of curvature of this knuckle is less than or equal to the radius of curvature of protruding circular arc.
The center of circle of described first upper surface circular arc place circle, the second upper surface circular arc place circle and lower surface circular arc place circle overlaps;
The difference t of the radius of curvature of described first upper surface circular arc and lower surface circular arc meets: 0.5mm≤t≤1.2mm.
The ultimate range in the center of circle of described protruding circular arc and the first upper surface circular arc place circle and the difference l of the radius of curvature of the first upper surface circular arc meet: 0.15mm≤l≤0.4mm, and the ultimate range in the center of circle of described protruding circular arc and the second upper surface circular arc place circle and the difference of the radius of curvature of the second upper surface circular arc are also l.
Described protruding circular arc is circular arc, and radius of curvature R meets: 6mm≤R≤15mm;
The ratio h of the ultimate range between described protruding circular arc and the string of a musical instrument and the length c of the string of a musical instrument meets: 0.015≤h≤0.08;
The radius of curvature of described protruding circular arc is less than the radius of curvature of the first upper surface circular arc, the second upper surface circular arc and lower surface circular arc.
The length c of the described string of a musical instrument meets: 5mm≤c≤100mm.
The difference t relation of the length c of the described string of a musical instrument and the radius of curvature of the first upper surface circular arc and lower surface circular arc meets: 0.01≤t/c≤0.06, and the length c of the string of a musical instrument is with the second upper surface circular arc is the same with the relation of the difference t of the radius of curvature of lower surface circular arc and t/c ratio is equal.
With the ratio k of the intersection point of the string of a musical instrument to the length c of the distance of leading edge and the string of a musical instrument after the center of circle of described protruding circular arc place circle and the circle center line connecting of the first upper surface circular arc place circle
1meet: 0.15≤k
1≤ 0.75;
With the ratio k of the intersection point of the string of a musical instrument to the length c of the distance of leading edge and the string of a musical instrument after the center of circle of described protruding circular arc place circle and the circle center line connecting of the second upper surface circular arc place circle
2meet: 0.15≤k
2≤ 0.75.
The thickness of described reinforced rib is less than the protruding circular arc ultimate range in the center of circle round to the first upper surface circular arc place and the difference l of the first upper surface circular arc radius of curvature;
Described reinforced rib adopts Unidirectional fiber, glass or titanium alloy material to make.
The invention has the beneficial effects as follows:
1, between the protruding circular arc of this aerofoil profile and lower surface circular arc, there is reinforcing rib structure, make aerofoil profile of the present invention ensure that under the rigidity of structure condition needed for rotor, the thickness comparing traditional low Reynolds number airfoil can be less.Because aerofoil profile is thinner, the aerodynamic characteristic of aerofoil profile is better, and lift coefficient is larger, 1ift-drag ratio is larger, and therefore, the rotor lift adopting this aerofoil profile to make is large, absorbed power is little, and mechanical characteristic good, be conducive to improve the aircraft flight time.
2, adopt this aerofoil profile to make rotor, technique is simple, easy to make, is conducive to cutting down finished cost.
3, profile thickness is little, and aerofoil section amasss little, and therefore adopt the volume of this aerofoil profile making rotor little, quality is light, compared with the rotor of same performance, and Mass lost at least 10%.
4, adopt the rotor of this aerofoil profile to have high lift coefficient, low pneumatic noise, high structural strength, low quality and easily manufactured feature, be conducive to improving the overall performance of Microminiature rotorcraft, expanding the application of Microminiature rotorcraft.
Accompanying drawing explanation
Fig. 1 is the airfoil structure schematic diagram with triangle front edge and oval trailing edge of the present invention;
Fig. 2 is the airfoil structure schematic diagram with oval leading edge and oval trailing edge of the present invention.
In figure: 1, leading edge, the 2, first upper surface circular arc, 3, First Transition fillet, 4, protruding circular arc, the 5, second knuckle, 6, trailing edge, 7, lower surface circular arc, 8, reinforced rib, the 9, second upper surface circular arc, 10, the string of a musical instrument.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail.
As shown in Figure 1, the thin circular arc airfoil with convex configuration of the present invention is made up of leading edge 1, first upper surface circular arc 2, First Transition fillet 3, protruding circular arc 4, second knuckle 5, second upper surface circular arc 9, trailing edge 6, lower surface circular arc 7 and reinforced rib 8, be in turn connected to form loop curve according to the order of leading edge 1, first upper surface circular arc 2, First Transition fillet 3, protruding circular arc 4, second knuckle 5, second upper surface circular arc 9, trailing edge 6, lower surface circular arc 7, leading edge 1, and be provided with reinforced rib 8 between protruding circular arc 4 and lower surface circular arc 7.
In present embodiment, the first upper surface circular arc 2, second upper surface circular arc 9 and lower surface circular arc 7 are circular arc.
In present embodiment, the first upper surface circular arc 2 is identical with the radius of curvature of the second upper surface circular arc 9 and the center of circle of respective place circle.
In present embodiment, the first upper surface circular arc 2 is different from the radius of curvature of lower surface circular arc 7 with the radius of curvature of the second upper surface circular arc 9; The center of circle of the first upper surface circular arc 2 place circle, the second upper surface circular arc 9 place circle and lower surface circular arc 7 place circle overlaps.
In present embodiment, the first upper surface circular arc 2 meets with the difference t of the radius of curvature of lower surface circular arc 7: 0.5mm≤t≤1.2mm, t preferred value is 0.7mm and 0.8mm, and the second upper surface circular arc 9 is also t with the difference of the radius of curvature of lower surface circular arc 7.
In present embodiment, First Transition fillet 3 is the fillets between connection first upper surface circular arc 2 and protruding circular arc 4, and First Transition fillet 3 is that smooth transition connects fillet; Second knuckle 5 is the fillets between connection bump circular arc 4 and the second upper surface circular arc 9, and the second knuckle 5 is that smooth transition connects fillet.
In present embodiment, First Transition fillet 3 is identical with the radius of curvature of the second knuckle 5.
In present embodiment, the radius of curvature R of protruding circular arc 4 meets: 6mm≤R≤15mm, and concrete size determines according to the rigidity of the size of reinforced rib 8 and aerofoil profile.
In present embodiment, the radius of curvature of First Transition fillet 3 and the second knuckle 5 is all more than or equal to the radius of curvature of protruding circular arc 4, and preferably equal, radius of curvature preferred value time equal is 6mm, 8mm, 10mm or 12mm.
In present embodiment, protruding circular arc 4 is circular arc, and the radius of curvature of protruding circular arc 4 is less than the radius of curvature of the first upper surface circular arc 2, second upper surface circular arc 9 and lower surface circular arc 7.
In present embodiment, the ultimate range in the center of circle of protruding circular arc 4 and the first upper surface circular arc 2 place circle and the difference l of the radius of curvature of the first upper surface circular arc 2 meet: 0.15mm≤l≤0.4mm, l preferred value is 0.15mm, and the ultimate range in the center of circle of protruding circular arc 4 and the second upper surface circular arc 9 place circle and the difference of the radius of curvature of the second upper surface circular arc 9 are also l.
In present embodiment, the string of a musical instrument 10 is the line on the summit of leading edge 1 and the summit of trailing edge 6, and the length c of the string of a musical instrument 10 meets: 5mm≤c≤100mm, and concrete selection determines according to aerodynamics and rotor design characteristic requirements.
In present embodiment, leading edge 1 is made up of the part-elliptical comprising a major semiaxis end points, and the summit of leading edge 1 is an end points of the major semiaxis of this part-elliptical.
In present embodiment, the summit of leading edge 1 is positioned at on the first upper surface circular arc 2 and the equidistant circular arc line of lower surface circular arc 7, or, the summit of leading edge 1 be positioned at the first upper surface circular arc 2 and the equidistant circular arc line of lower surface circular arc 7 below near the position of the string of a musical instrument 10.
In present embodiment, between leading edge 1 and the first upper surface circular arc 2, all have knuckle between leading edge 1 and lower surface circular arc 7, the radius of curvature of this knuckle is less than or equal to the radius of curvature of protruding circular arc 4.
In present embodiment, trailing edge 6 is made up of the part-elliptical comprising a major semiaxis end points, and the summit of trailing edge 6 is an end points of the major semiaxis of this part-elliptical, or, trailing edge 6 is made up of two limits comprising an acute angle, and the summit of trailing edge 6 is the summit of this acute angle.
In present embodiment, the summit of trailing edge 6 is positioned at on the second upper surface circular arc 9 and the equidistant circular arc line of lower surface circular arc 7, or, the summit of trailing edge 6 be positioned at the second upper surface circular arc 9 and the equidistant circular arc line of lower surface circular arc 7 below near the position of the string of a musical instrument 10.
In present embodiment, between trailing edge 6 and the first upper surface circular arc 2, all have knuckle between trailing edge 6 and lower surface circular arc 7, the radius of curvature of this knuckle is less than or equal to the radius of curvature of protruding circular arc 4.
In present embodiment, the length c of the string of a musical instrument 10 and the first upper surface circular arc 2 meet with the difference t relation of the radius of curvature of lower surface circular arc 7: 0.01≤t/c≤0.06, and the length c of the string of a musical instrument 10 is with the second upper surface circular arc 9 is the same with the relation of the difference t of the radius of curvature of lower surface circular arc 7 and t/c ratio is equal.
In present embodiment, with the ratio k of the intersection point of the string of a musical instrument 10 to the length c of the distance of leading edge 1 and the string of a musical instrument 10 after the center of circle of protruding circular arc 4 place circle and the circle center line connecting of the first upper surface circular arc 2 place circle
1meet: 0.15≤k
1≤ 0.75, with the ratio k of the intersection point of the string of a musical instrument 10 to the length c of the distance of leading edge 1 and the string of a musical instrument 10 after the center of circle of protruding circular arc 4 place circle and the circle center line connecting of the second upper surface circular arc 9 place circle
2meet: 0.15≤k
2≤ 0.75.
In present embodiment, the ratio h of the ultimate range between protruding circular arc 4 and the string of a musical instrument 10 and the length c of the string of a musical instrument 10 meets: 0.015≤h≤0.08, and concrete selection determines according to aerodynamics and rotor design characteristic requirements.
In present embodiment, the length c relation of the projected length m of leading edge 1 on the string of a musical instrument 10 direction and the string of a musical instrument 10 meets: 0.08≤m/c≤0.15.
In present embodiment, the length c relation of the projected length n of trailing edge 6 on the string of a musical instrument 10 direction and the string of a musical instrument 10 meets: 0.04≤n/c≤0.1;
In present embodiment, the difference t of the radius of curvature of the projected length n of trailing edge 6 on the string of a musical instrument 10 direction and the first upper surface circular arc 2 and lower surface circular arc 7 meets: 2≤n/t≤4.
In present embodiment, be provided with a reinforced rib 8 between protruding circular arc 4 and lower surface circular arc 7, the thickness of reinforced rib 8 is less than or equal to the ultimate range in the center of circle and the difference l of the first upper surface circular arc 2 radius of curvature of protruding circular arc 4 to the first upper surface circular arc 2 place circle.
In present embodiment, reinforced rib 8 adopts Unidirectional fiber, glass or titanium alloy etc materials to make, and the width of reinforced rib 8 reduces with the increase of thin circular arc airfoil erect-position.
The reynolds number range of thin circular arc airfoil work of the present invention is 4000 ~ 10000,10000 ~ 100000,100000 ~ 200000.
Claims (10)
1. one kind has the thin circular arc airfoil of convex configuration, it is characterized in that, this aerofoil profile is by leading edge (1), first upper surface circular arc (2), First Transition fillet (3), protruding circular arc (4), second knuckle (5), second upper surface circular arc (9), trailing edge (6), lower surface circular arc (7) and reinforced rib (8) composition, according to leading edge (1), first upper surface circular arc (2), First Transition fillet (3), protruding circular arc (4), second knuckle (5), second upper surface circular arc (9), trailing edge (6), lower surface circular arc (7), the order of leading edge (1) is in turn connected to form loop curve, reinforced rib (8) is arranged between protruding circular arc (4) and lower surface circular arc (7),
The line on the summit of described leading edge (1) and the summit of trailing edge (6) is the string of a musical instrument (10);
Described First Transition fillet (3) is identical with the radius of curvature of the second knuckle (5);
The radius of curvature of described First Transition fillet (3) and the second knuckle (5) is all more than or equal to the radius of curvature of protruding circular arc (4);
Described first upper surface circular arc (2), the second upper surface circular arc (9) and lower surface circular arc (7) are circular arc;
Described first upper surface circular arc (2) is identical with the radius of curvature of the second upper surface circular arc (9) and the center of circle of respective place circle.
2. thin circular arc airfoil according to claim 1, is characterized in that, described leading edge (1) is made up of the part-elliptical comprising a major semiaxis end points, and the summit of leading edge (1) is an end points of the major semiaxis of this part-elliptical;
The length c relation of the projected length m of described leading edge (1) on the string of a musical instrument (10) direction and the string of a musical instrument (10) meets: 0.08≤m/c≤0.15;
Described leading edge (1) and all have knuckle between the first upper surface circular arc (2) and lower surface circular arc (7), the radius of curvature of this knuckle is less than or equal to the radius of curvature of protruding circular arc (4).
3. thin circular arc airfoil according to claim 1, it is characterized in that, described trailing edge (6) is made up of the part-elliptical comprising a major semiaxis end points, the summit of trailing edge (6) is an end points of the major semiaxis of this part-elliptical, or, trailing edge (6) is made up of two limits comprising an acute angle, and the summit of trailing edge (6) is the summit of this acute angle;
The length c relation of the projected length n of described trailing edge (6) on the string of a musical instrument (10) direction and the string of a musical instrument (10) meets: 0.04≤n/c≤0.1;
The difference t of the radius of curvature of the projected length n of described trailing edge (6) on the string of a musical instrument (10) direction and the first upper surface circular arc (2) and lower surface circular arc (7) meets: 2≤n/t≤4;
Described trailing edge (6) and all have knuckle between the first upper surface circular arc (2) and lower surface circular arc (7), the radius of curvature of this knuckle is less than or equal to the radius of curvature of protruding circular arc (4).
4. thin circular arc airfoil according to claim 1, is characterized in that, the center of circle of described first upper surface circular arc (2) place circle, the second upper surface circular arc (9) place circle and lower surface circular arc (7) place circle overlaps;
Described first upper surface circular arc (2) meets with the difference t of the radius of curvature of lower surface circular arc (7): 0.5mm≤t≤1.2mm.
5. thin circular arc airfoil according to claim 1, it is characterized in that, described protruding circular arc (4) meets with the ultimate range in the center of circle of the first upper surface circular arc (2) place circle and the difference l of the radius of curvature of the first upper surface circular arc (2): 0.15mm≤l≤0.4mm, and described protruding circular arc (4) is also l with the ultimate range in the center of circle of the second upper surface circular arc (9) place circle and the difference of the radius of curvature of the second upper surface circular arc (9).
6. thin circular arc airfoil according to claim 1, is characterized in that, described protruding circular arc (4) is circular arc, and radius of curvature R meets: 6mm≤R≤15mm;
The ratio h of the ultimate range between described protruding circular arc (4) and the string of a musical instrument (10) and the length c of the string of a musical instrument (10) meets: 0.015≤h≤0.08;
The radius of curvature of described protruding circular arc (4) is less than the radius of curvature of the first upper surface circular arc (2), the second upper surface circular arc (9) and lower surface circular arc (7).
7. thin circular arc airfoil according to claim 1, is characterized in that, the length c of the described string of a musical instrument (10) meets: 5mm≤c≤100mm.
8. thin circular arc airfoil according to claim 1, it is characterized in that, the length c of the described string of a musical instrument (10) and the first upper surface circular arc (2) meet with the difference t relation of the radius of curvature of lower surface circular arc (7): 0.01≤t/c≤0.06, and the length c of the string of a musical instrument (10) and the second upper surface circular arc (9) are with the relation of the difference t of the radius of curvature of lower surface circular arc (7) is the same and t/c ratio is equal.
9. thin circular arc airfoil according to claim 1, it is characterized in that, with the ratio k of the intersection point of the string of a musical instrument (10) to the length c of the distance of leading edge (1) and the string of a musical instrument (10) after the center of circle of described protruding circular arc (4) place circle and the circle center line connecting of the first upper surface circular arc (2) place circle
1meet: 0.15≤k
1≤ 0.75;
With the ratio k of the intersection point of the string of a musical instrument (10) to the length c of the distance of leading edge (1) and the string of a musical instrument (10) after the center of circle of described protruding circular arc (4) place circle and the circle center line connecting of the second upper surface circular arc (9) place circle
2meet: 0.15≤k
2≤ 0.75.
10. thin circular arc airfoil according to claim 1, it is characterized in that, the thickness of described reinforced rib (8) is less than protruding circular arc (4) ultimate range in the center of circle round to the first upper surface circular arc (2) place and the difference l of the first upper surface circular arc (2) radius of curvature;
Described reinforced rib (8) adopts Unidirectional fiber, glass fibre or titanium alloy material to make.
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| CN201310506604.9A CN103587678B (en) | 2013-10-24 | 2013-10-24 | A kind of thin circular arc airfoil with convex configuration |
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| CN201310506604.9A CN103587678B (en) | 2013-10-24 | 2013-10-24 | A kind of thin circular arc airfoil with convex configuration |
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| CN103587678B true CN103587678B (en) | 2015-09-09 |
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| CN109878721B (en) * | 2019-04-04 | 2023-11-21 | 中南大学 | Design method and product of rotor wing profile of micro rotor unmanned aerial vehicle |
| CN114104281B (en) * | 2021-10-29 | 2024-05-07 | 西安交通大学 | Silence investigation aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4434957A (en) * | 1982-03-30 | 1984-03-06 | Rolls-Royce Incorporated | Low drag surface |
| US4641796A (en) * | 1983-09-30 | 1987-02-10 | The Boeing Company | Airfoil |
| US5395071A (en) * | 1993-09-09 | 1995-03-07 | Felix; Frederick L. | Airfoil with bicambered surface |
| US6095457A (en) * | 1998-12-14 | 2000-08-01 | Vanmoor; Arthur | Airfoil and wing configuration |
| CN102358416B (en) * | 2011-09-05 | 2014-04-23 | 西安交通大学 | Aerodynamic high-performance aerofoil for aircraft |
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