CN103587678A - Thin-arc-shaped airfoil profile with upward convex structure - Google Patents
Thin-arc-shaped airfoil profile with upward convex structure Download PDFInfo
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- CN103587678A CN103587678A CN201310506604.9A CN201310506604A CN103587678A CN 103587678 A CN103587678 A CN 103587678A CN 201310506604 A CN201310506604 A CN 201310506604A CN 103587678 A CN103587678 A CN 103587678A
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Abstract
The invention discloses a thin-arc-shaped airfoil profile with an upward convex structure, which relates to the field of aerodynamics and hydromechanics, and solves the problems of low lift coefficient and high aerodynamic noise of an existing airfoil profile. The thin-arc-shaped airfoil profile consists of a front edge, a first upper surface arc, a first transitional fillet, a convex arc, a second transitional fillet, a second upper surface arc, a rear edge, a lower surface arc and a reinforcing rib, wherein the front edge, the first upper surface arc, the first transitional fillet, the convex arc, the second transitional fillet, the second upper surface arc, the rear edge, the lower surface arc and the front edge are connected in sequence to form a closed curve; the reinforcing rib is arranged between the convex arc and the lower surface arc; the connecting line of the vertexes of the front edge and the rear edge is a chord line. The thin-arc-shaped airfoil profile simultaneously has the characteristics of high lift coefficient, low aerodynamic noise, high structural strength, convenience in manufacturing and the like.
Description
Technical field
The present invention relates to aerodynamics and hydrodynamics technology field, be specifically related to a kind of thin circular arc aerofoil profile 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 various countries research institution and company.Rotor is the lifting surface of aircraft, is also controlsurface and propulsive force face, and 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, causes rotor to be operated under lower Reynolds number Airflow Environment, and 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 is not suitable for rotor under low reynolds number Airflow Environment and uses.Adopt low Reynolds number airfoil as flat profile, flat profile, the NACA series thin airfoil with camber are made 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 variation, affects the control quality 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 low reynolds number Airfoil that there is high lift coefficient, low pneumatic noise and high structural strength simultaneously and be convenient to manufacture to improving the overall performance of small-sized rotor craft, to expand the application of Microminiature rotorcraft most important.
Summary of the invention
The problem that lift coefficient is low, aerodynamics noise is high existing in order to solve existing aerofoil profile, the invention provides a kind of thin circular arc aerofoil profile with convex configuration that has high coefficient of lift combined, low pneumatic noise, high structural strength simultaneously and be convenient to manufacture.
The present invention is that the technical scheme that adopts of technical solution problem is as follows:
A kind of thin circular arc aerofoil profile with convex configuration, this aerofoil profile is comprised 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, order according to 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 is in turn connected to form loop curve, and 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 the first upper surface circular arc, the second upper surface circular arc and lower surface circular arc are circular arc;
The center of circle of described the first upper surface circular arc and the radius of curvature of the second upper surface circular arc and separately place circle is identical.
Described leading edge is comprised of the part ellipse that comprises a major semiaxis end points, and the summit of leading edge is an end points of the oval-shaped major semiaxis of this part;
The length c relation of the projected length m of described leading edge in string of a musical instrument direction and the string of a musical instrument meets: 0.08≤m/c≤0.15;
Between described leading edge and the first upper surface circular arc and lower surface circular arc, all have knuckle, 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 comprised of the part ellipse that comprises a major semiaxis end points, and the summit of trailing edge is an end points of the oval-shaped major semiaxis of this part, or trailing edge is comprised of two limits that comprise an acute angle, the summit that the summit of trailing edge is this acute angle;
The length c relation of the projected length n of described trailing edge in 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 in string of a musical instrument direction and the first upper surface circular arc and lower surface circular arc meets: 2≤n/t≤4;
Between described trailing edge and the first upper surface circular arc and lower surface circular arc, all have knuckle, 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 the 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 the 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, described protruding circular arc and the ultimate range in the center of circle of 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 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 radius of curvature of the length c of the described string of a musical instrument and the first upper surface circular arc and lower surface circular arc meets: 0.01≤t/c≤0.06, the same and t/c ratio of the relation of the length c of the string of a musical instrument and the second upper surface circular arc and the difference t of the radius of curvature of lower surface circular arc equates.
After the circle center line connecting of the center of circle of described protruding circular arc place circle and the first upper surface circular arc place circle, arrive the ratio k of the distance of leading edge and the length c of the string of a musical instrument with the intersection point of the string of a musical instrument
1meet: 0.15≤k
1≤ 0.75;
After the circle center line connecting of the center of circle of described protruding circular arc place circle and the second upper surface circular arc place circle, arrive the ratio k of the distance of leading edge and the length c of the string of a musical instrument with the intersection point of the string of a musical instrument
2meet: 0.15≤k
2≤ 0.75.
The thickness of described reinforced rib is less than protruding circular arc to the ultimate range in the center of circle and the difference l of the first upper surface circular arc radius of curvature of the first upper surface circular arc place circle;
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 guarantee that under the required rigidity of structure condition of rotor, the thickness of 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 that adopts 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 cut down finished cost.
3, profile thickness is little, and aerofoil section is long-pending little, therefore adopts the volume of this aerofoil profile making rotor little, and quality is light, compares with the rotor of same performance, and quality is reduced by least 10%.
4, adopt the rotor of this aerofoil profile to there is high lift coefficient, low pneumatic noise, high structural strength, low quality and easily manufactured feature, be conducive to improve Microminiature rotorcraft overall performance, expand 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.
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
As shown in Figure 1, the thin circular arc aerofoil profile with convex configuration of the present invention is comprised of leading edge 1, the first upper surface circular arc 2, First Transition fillet 3, protruding circular arc 4, the second knuckle 5, the second upper surface circular arc 9, trailing edge 6, lower surface circular arc 7 and reinforced rib 8, order according to leading edge 1, the first upper surface circular arc 2, First Transition fillet 3, protruding circular arc 4, the second knuckle 5, the second upper surface circular arc 9, trailing edge 6, lower surface circular arc 7, leading edge 1 is in turn connected to form loop curve, and is 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, the second upper surface circular arc 9 and lower surface circular arc 7 are circular arc.
In present embodiment, the center of circle of the first upper surface circular arc 2 and the radius of curvature of the second upper surface circular arc 9 and separately place circle is identical.
In present embodiment, the radius of curvature of the first upper surface circular arc 2 and the second upper surface circular arc 9 is different from the radius of curvature of lower surface circular arc 7; The center of circle of the first upper surface circular arc 2 place circles, the second upper surface circular arc 9 place circles and lower surface circular arc 7 place circles 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, and t preferred value is 0.7mm and 0.8mm, 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 that connect between the first upper surface circular arc 2 and protruding circular arc 4, and First Transition fillet 3 is that smooth transition connects fillet; The 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, 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, preferably equals, and the radius of curvature preferred value while equating 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, the second upper surface circular arc 9 and lower surface circular arc 7.
In present embodiment, projection circular arc 4 and the first upper surface circular arc 2 ultimate ranges in the center of circle of 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 protruding circular arc 4 and the ultimate range in the center of circle of the second upper surface circular arc 9 place circles 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, concrete selective basis aerodynamics and rotor design characteristic requirements determine.
In present embodiment, leading edge 1 is comprised of the part ellipse that comprises a major semiaxis end points, and the summit of leading edge 1 is an end points of the oval-shaped major semiaxis of this part.
In present embodiment, 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 on, or the summit of leading edge 1 is positioned at the position with the close string of a musical instrument 10 of the first upper surface circular arc 2 and lower surface circular arc 7 equidistant circular arc line below.
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 comprised of the part ellipse that comprises a major semiaxis end points, and the summit of trailing edge 6 is an end points of the oval-shaped major semiaxis of this part, or, trailing edge 6 is comprised of two limits that comprise an acute angle, the summit that the summit of trailing edge 6 is this acute angle.
In present embodiment, 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 on, or the summit of trailing edge 6 is positioned at the position with the close string of a musical instrument 10 of the second upper surface circular arc 9 and lower surface circular arc 7 equidistant circular arc line below.
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, the same and t/c ratio of the relation of the length c of the string of a musical instrument 10 and the second upper surface circular arc 9 and the difference t of the radius of curvature of lower surface circular arc 7 equates.
In present embodiment, after the circle center line connecting of the center of circle of protruding circular arc 4 place circles and the first upper surface circular arc 2 place circles, arrive the ratio k of the distance of leading edge 1 and the length c of the string of a musical instrument 10 with the intersection point of the string of a musical instrument 10
1meet: 0.15≤k
1≤ 0.75, after the circle center line connecting of the center of circle of protruding circular arc 4 places circles and the second upper surface circular arc 9 places circles with the intersection point of the string of a musical instrument 10 ratio k to the distance of leading edge 1 and the length c of the string of a musical instrument 10
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, concrete selective basis aerodynamics and rotor design characteristic requirements determine.
In present embodiment, the length c relation of the projected length m of leading edge 1 in the string of a musical instrument 10 directions 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 in the string of a musical instrument 10 directions 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 in the string of a musical instrument 10 directions 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 radiuss of curvature of protruding circular arc 4 to first upper surface circular arc 2 place circles.
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 aerofoil profile erect-position.
The reynolds number range of thin circular arc aerofoil profile of the present invention work is 4000～10000,10000～100000,100000～200000.
Claims (10)
1. a thin circular arc aerofoil profile with convex configuration, it is characterized in that, this aerofoil profile is by leading edge (1), the first upper surface circular arc (2), First Transition fillet (3), projection circular arc (4), the second knuckle (5), the second upper surface circular arc (9), trailing edge (6), lower surface circular arc (7) and reinforced rib (8) form, according to leading edge (1), the first upper surface circular arc (2), First Transition fillet (3), projection circular arc (4), the second knuckle (5), the 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 the summit of described leading edge (1) and 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 the first upper surface circular arc (2), the second upper surface circular arc (9) and lower surface circular arc (7) are circular arc;
The center of circle of described the first upper surface circular arc (2) and the radius of curvature of the second upper surface circular arc (9) and separately place circle is identical.
2. thin circular arc aerofoil profile according to claim 1, is characterized in that, described leading edge (1) is comprised of the part ellipse that comprises a major semiaxis end points, and the summit of leading edge (1) is an end points of the oval-shaped major semiaxis of this part;
The length c relation of the projected length m of described leading edge (1) in the string of a musical instrument (10) direction and the string of a musical instrument (10) meets: 0.08≤m/c≤0.15;
Between described leading edge (1) and the first upper surface circular arc (2) and lower surface circular arc (7), all have knuckle, 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 aerofoil profile according to claim 1, it is characterized in that, described trailing edge (6) is comprised of the part ellipse that comprises a major semiaxis end points, the summit of trailing edge (6) is an end points of the oval-shaped major semiaxis of this part, or, trailing edge (6) is comprised of two limits that comprise an acute angle, the summit that the summit of trailing edge (6) is this acute angle;
The length c relation of the projected length n of described trailing edge (6) in 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) in 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;
Between described trailing edge (6) and the first upper surface circular arc (2) and lower surface circular arc (7), all have knuckle, 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 aerofoil profile according to claim 1, is characterized in that, the center of circle of described 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;
Described 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.
5. thin circular arc aerofoil profile according to claim 1, it is characterized in that, described protruding circular arc (4) meets with first ultimate range in the center of circle of 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, 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 aerofoil profile 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 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 aerofoil profile 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 aerofoil profile according to claim 1, it is characterized in that, the difference t relation of the radius of curvature of the length c of the described string of a musical instrument (10) and the first upper surface circular arc (2) and lower surface circular arc (7) meets: 0.01≤t/c≤0.06, the same and t/c ratio of the relation of the length c of the string of a musical instrument (10) and the second upper surface circular arc (9) and the difference t of the radius of curvature of lower surface circular arc (7) equates.
9. thin circular arc aerofoil profile according to claim 1, it is characterized in that, after the circle center line connecting of the center of circle of described protruding circular arc (4) place circle and the first upper surface circular arc (2) place circle, arrive the ratio k of the distance of leading edge (1) and the length c of the string of a musical instrument (10) with the intersection point of the string of a musical instrument (10)
1meet: 0.15≤k
1≤ 0.75;
After the circle center line connecting of the center of circle of described protruding circular arc (4) place circle and the second upper surface circular arc (9) place circle, arrive the ratio k of the distance of leading edge (1) and the length c of the string of a musical instrument (10) with the intersection point of the string of a musical instrument (10)
2meet: 0.15≤k
2≤ 0.75.
10. thin circular arc aerofoil profile according to claim 1, it is characterized in that, the thickness of described reinforced rib (8) is less than protruding circular arc (4) 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 the first upper surface circular arc (2) place circle;
Described reinforced rib (8) adopts Unidirectional fiber, glass or titanium alloy material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| CN103587678A true CN103587678A (en) | 2014-02-19 |
| CN103587678B CN103587678B (en) | 2015-09-09 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109878721A (en) * | 2019-04-04 | 2019-06-14 | 中南大学 | A kind of design method and product of microminiature rotor unmanned aircraft rotor-blade airfoil |
| CN114104281A (en) * | 2021-10-29 | 2022-03-01 | 西安交通大学 | Mute investigation aircraft |
Citations (5)
| 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 |
| CN102358416A (en) * | 2011-09-05 | 2012-02-22 | 西安交通大学 | Aerodynamic high-performance aerofoil for aircraft |
-
2013
- 2013-10-24 CN CN201310506604.9A patent/CN103587678B/en not_active Expired - Fee Related
Patent Citations (5)
| 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 |
| CN102358416A (en) * | 2011-09-05 | 2012-02-22 | 西安交通大学 | Aerodynamic high-performance aerofoil for aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109878721A (en) * | 2019-04-04 | 2019-06-14 | 中南大学 | A kind of design method and product of microminiature rotor unmanned aircraft rotor-blade airfoil |
| 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 |
| CN114104281A (en) * | 2021-10-29 | 2022-03-01 | 西安交通大学 | Mute investigation aircraft |
| CN114104281B (en) * | 2021-10-29 | 2024-05-07 | 西安交通大学 | Silence investigation aircraft |
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| CN103587678B (en) | 2015-09-09 |
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