CN102826216A - Aerodynamic configuration of aircraft - Google Patents
Aerodynamic configuration of aircraft Download PDFInfo
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- CN102826216A CN102826216A CN2012103338631A CN201210333863A CN102826216A CN 102826216 A CN102826216 A CN 102826216A CN 2012103338631 A CN2012103338631 A CN 2012103338631A CN 201210333863 A CN201210333863 A CN 201210333863A CN 102826216 A CN102826216 A CN 102826216A
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Abstract
The invention relates to the technical field of aerodynamic configuration design of aircrafts, in particular to an aerodynamic configuration of an aircraft. The aerodynamic configuration of the aircraft comprises an aircraft body (3), outer wing sections (1) and inner wing sections, and is characterized in that the surfaces of the outer wing sections (1) and the inner wing sections (2) are laminar flow airfoils; the inner wing sections (2) are wing-body transition sections, adopt back-swept wings with a moderate sweep back angle and a small span-chord ratio and are connected with the aircraft body; the wings and the aircraft body are fused together; and the outer wing sections (1) adopt forward-swept wings with a moderate sweep forward angle and a moderate span-chord ratio. Due to the aerodynamic configuration of the aircraft, not only can the requirement on high-altitude long-endurance high-subsonic-speed cruise of the aircraft be satisfied, but also the flight speed is improved and the problem of trimming difficulty is solved.
Description
Technical field
The present invention relates to the aerodynamic configuration of aircraft design field.
Background technology
Aircraft is the crystallization of contemporary advanced science and cutting edge technology, is a complicated system engineering, and wherein aerodynamic arrangement's design is the most important thing, is directly connected to the airplane synthetic effective utilization.
Wing is main aerodynamic force parts in the aircraft components, and it is the major part that aircraft produces aerodynamic lift.Buzzard-type wing is a kind of wing configuration design of swept wing, and is the same with swept wing, can improve the drag divergence Mach number, improves the speed ability of aircraft.Buzzard-type wing produces the interior sidewind to wing root, and the wing wing root is loaded, and wing is more reasonable than swept wing to distribution of load along exhibition.For example: the HFB 320 HANSA transport planes of U.S.'s development and X-29 technical identification machine just adopt this wing design.
The all-wing aircraft layout is that a kind of wing body merges, the part fuselage is hidden in the thick wing, and the aircraft configuration topological design of no horizontal tail and vertical fin, it simplifies housing construction greatly, has reduced the structural weight of aircraft.For example: the B2 bomber of the U.S., X45 unmanned plane and X47 unmanned plane have just adopted sweepback all-wing aircraft layout, see from aerodynamic configuration, and wing and fuselage combine together; Whole airplane is similar to a lifting surface, can reduce interference drag and induced drag significantly, simultaneously; Owing to removed horizontal tail and vertical fin; Reduced the quantity of corner reflector, do not had tangible fuselage, stealthy performance is promoted greatly.But still there is following technological deficiency in existing all-wing aircraft layout:
(1) speed issue.For the part fuselage better is hidden among the wing, the wing design of all-wing aircraft is much thicker than common wing.This influences limited when low speed, but the relative thicker part of wing can produce bigger drag effect when high subsonic speed, makes it be not suitable for high-speed flight, and more responsive more than normal arrangement to the variation of speed.
(2) trim problem.Existing all-wing aircraft layout in order to calibrate very little trim, needs to move the up-down rudder face, thereby increases the trim resistance in flat flying, and has also increased the pressure of fore-and-aft control face.
Summary of the invention
(1) the object of the invention
For the aircraft speed that solves in the above-mentioned all-wing aircraft layout is hanged down and the difficult problem of trim, thereby a kind of improved aerodynamic configuration of aircraft is proposed.
(2) technical scheme of the present invention
The present invention takes following technical scheme: a kind of aerodynamic configuration of aircraft; Comprise fuselage, outer panel, interior wing panel; The aerofoil of outer panel and interior wing panel adopts the laminar f1ow airfoil profile of high critical Mach number, little nose-down pitching moment, high lift-drag ratio, and interior wing panel is a wing body transition phase, adopts moderate sweep, low aspect ratio; And be connected with fuselage, realize that wing body merges; It is characterized in that outer panel adopts medium sweepforward angle, medium aspect ratio buzzard-type wing.
(3) beneficial effect of the present invention
The HAE high subsonic speed that the present invention not only the satisfies aircraft requirement of cruising has also improved flying speed and has solved the problem of trim difficulty.
Description of drawings
Fig. 1 is an aircraft profile schematic perspective view.
Fig. 2 is the aircraft plan sketch.
The specific embodiment
Embodiment of the present invention is following: shown in Fig. 1～2, a kind of aerodynamic configuration of aircraft comprises fuselage 3, outer panel 1, interior wing panel 2.Outer panel 1 should account for more than 65% of aerofoil area of conter as main lifting surface, and interior wing panel 2 is below 35%; The aerofoil of outer panel 1 and interior wing panel 2 adopts the laminar f1ow airfoil profile of high critical Mach number, little nose-down pitching moment, high lift-drag ratio, and interior wing panel 2 is a wing body transition phase, adopts moderate sweep, low aspect ratio, and is connected with fuselage, realizes that wing body merges; Outer panel 1 adopts medium sweepforward angle, medium aspect ratio buzzard-type wing.It is 6.5% ~ 10% laminar f1ow airfoil profile that outer panel 1 adopts little nose-down pitching moment, maximum ga(u)ge, and outer wing sweepforward angle 5 is that 15 ° ~ 40 °, aspect ratio are 7 ~ 15, trapezoidal ratio is 1.5 ~ 3; It is 8% ~ 12% laminar f1ow airfoil profile that interior wing panel 2 adopts little nose-down pitching moment, maximum ga(u)ge, and inner wing sweepback angle 4 is that 30 ° ~ 75 °, aspect ratio are 1.5 ~ 3, trapezoidal ratio is 1.0 ~ 1.5.
Embodiment 1:
Certain type machine aerodynamic arrangement be outer panel 1 to select little nose-down pitching moment maximum ga(u)ge for use be 8% laminar f1ow airfoil profile, outer wing sweepforward angle 5 is that 25 °, aspect ratio are 9, trapezoidal ratio is 2.27; It is that 10% laminar f1ow airfoil profile sweepback angle is that 42 °, aspect ratio are 1.75, trapezoidal ratio is 1.21 that interior wing panel is selected little nose-down pitching moment maximum ga(u)ge for use; Interior wing panel 2 is connected with fuselage 1, realizes that wing body merges.It is 3 ° that this aerodynamic arrangement's scheme moment balance point appears at the angle of attack, and when the angle of attack was 3 °, full machine lift coefficient was 0.244, and maximum lift-drag ratio is greater than 17, Mach Number Never To Be Exceeded 0.86; Show that this aerodynamic arrangement's scheme reaches basically from trim, promptly the corresponding angle of attack of maximum lift-drag ratio is the balance angle of attack, aerodynamic characteristic satisfies the requirement of cruising of HAE high subsonic speed simultaneously.
Claims (4)
1. aerodynamic configuration of aircraft; Comprise fuselage (3), outer panel (1), interior wing panel (2), it is characterized in that the aerofoil of outer panel (1) and interior wing panel (2) adopts laminar f1ow airfoil profile, interior wing panel (2) is a wing body transition phase; Adopt moderate sweep, low aspect ratio; Be connected with fuselage, wing body merges, and outer panel (1) adopts medium sweepforward angle, medium aspect ratio buzzard-type wing.
2. a kind of aerodynamic configuration of aircraft according to claim 1 is characterized in that outer panel (1) accounts for more than 65% of whole aerofoil area of conter, and interior wing panel (2) is below 35%.
3. a kind of aerodynamic configuration of aircraft according to claim 1; It is characterized in that it is 6.5% ~ 10% laminar f1ow airfoil profile that outer panel (1) adopts little nose-down pitching moment, maximum ga(u)ge, outer wing sweepforward angle (5) is that 15 ° ~ 40 °, aspect ratio are 7 ~ 15, trapezoidal ratio is 1.5 ~ 3.
4. a kind of aerodynamic configuration of aircraft according to claim 1; It is characterized in that it is 8% ~ 12% laminar f1ow airfoil profile that interior wing panel (2) should adopt little nose-down pitching moment, maximum ga(u)ge, inner wing sweepback angle (4) are that 30 ° ~ 75 °, aspect ratio are 1.5 ~ 3, trapezoidal ratio is 1.0 ~ 1.5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012103338631A CN102826216A (en) | 2012-09-11 | 2012-09-11 | Aerodynamic configuration of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012103338631A CN102826216A (en) | 2012-09-11 | 2012-09-11 | Aerodynamic configuration of aircraft |
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| CN102826216A true CN102826216A (en) | 2012-12-19 |
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| CN2012103338631A Pending CN102826216A (en) | 2012-09-11 | 2012-09-11 | Aerodynamic configuration of aircraft |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105486177A (en) * | 2016-01-13 | 2016-04-13 | 北京金朋达航空科技有限公司 | Target drone capable of achieving great maneuver |
| CN107284641A (en) * | 2017-07-03 | 2017-10-24 | 武汉华伍航空科技有限公司 | A kind of baby plane aerodynamic configuration suitable for supersonic flight |
| CN111003169A (en) * | 2019-12-24 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Flying wing capable of achieving short-distance take-off and landing |
| CN112537445A (en) * | 2020-12-16 | 2021-03-23 | 北京航空航天大学合肥创新研究院 | Rotor craft capable of tilting in flying wing layout |
| CN112606995A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Wide-speed-range pneumatic stability control characteristic structure for flying wing layout |
| CN112660381A (en) * | 2020-12-24 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow control technology-based wing body fusion layout passenger plane layout method |
| CN113626934A (en) * | 2021-08-16 | 2021-11-09 | 成都飞机工业（集团）有限责任公司 | Wing multi-configuration coordinated design method for flying wing layout unmanned aerial vehicle |
| CN114852299A (en) * | 2022-04-30 | 2022-08-05 | 西北工业大学 | Wing body fusion underwater glider with forward swept wing layout |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1435355A (en) * | 2002-12-04 | 2003-08-13 | 韩国庆 | Light buzzard-type wing jet plane and its use, and aircaft carrier using it as ship plane |
| CN201023653Y (en) * | 2007-04-24 | 2008-02-20 | 江西洪都航空工业集团有限责任公司 | Large aspect ratio sweep forward wings airplane pneumatic distribution |
| CN202783771U (en) * | 2012-09-11 | 2013-03-13 | 江西洪都航空工业集团有限责任公司 | Aircraft aerodynamic configuration |
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2012
- 2012-09-11 CN CN2012103338631A patent/CN102826216A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1435355A (en) * | 2002-12-04 | 2003-08-13 | 韩国庆 | Light buzzard-type wing jet plane and its use, and aircaft carrier using it as ship plane |
| CN201023653Y (en) * | 2007-04-24 | 2008-02-20 | 江西洪都航空工业集团有限责任公司 | Large aspect ratio sweep forward wings airplane pneumatic distribution |
| CN202783771U (en) * | 2012-09-11 | 2013-03-13 | 江西洪都航空工业集团有限责任公司 | Aircraft aerodynamic configuration |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105486177A (en) * | 2016-01-13 | 2016-04-13 | 北京金朋达航空科技有限公司 | Target drone capable of achieving great maneuver |
| CN105486177B (en) * | 2016-01-13 | 2017-03-01 | 北京金朋达航空科技有限公司 | A kind of target drone enabling high maneuver |
| CN107284641A (en) * | 2017-07-03 | 2017-10-24 | 武汉华伍航空科技有限公司 | A kind of baby plane aerodynamic configuration suitable for supersonic flight |
| CN107284641B (en) * | 2017-07-03 | 2023-09-08 | 安徽国援智能科技有限公司 | Pneumatic appearance of small-size aircraft suitable for supersonic flight |
| CN111003169B (en) * | 2019-12-24 | 2023-07-21 | 中国航空工业集团公司西安飞机设计研究所 | Flying wing capable of realizing short-distance take-off and landing |
| CN111003169A (en) * | 2019-12-24 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Flying wing capable of achieving short-distance take-off and landing |
| CN112537445A (en) * | 2020-12-16 | 2021-03-23 | 北京航空航天大学合肥创新研究院 | Rotor craft capable of tilting in flying wing layout |
| CN112537445B (en) * | 2020-12-16 | 2024-04-23 | 北京航空航天大学合肥创新研究院 | Flying wing layout tilting rotor aircraft |
| CN112606995A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Wide-speed-range pneumatic stability control characteristic structure for flying wing layout |
| CN112660381A (en) * | 2020-12-24 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow control technology-based wing body fusion layout passenger plane layout method |
| CN113626934A (en) * | 2021-08-16 | 2021-11-09 | 成都飞机工业（集团）有限责任公司 | Wing multi-configuration coordinated design method for flying wing layout unmanned aerial vehicle |
| CN113626934B (en) * | 2021-08-16 | 2023-12-08 | 成都飞机工业（集团）有限责任公司 | Multi-configuration coordination design method for unmanned aerial vehicle wing with flying wing layout |
| CN114852299A (en) * | 2022-04-30 | 2022-08-05 | 西北工业大学 | Wing body fusion underwater glider with forward swept wing layout |
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Application publication date: 20121219 |