CN202783771U - Aircraft aerodynamic configuration - Google Patents
Aircraft aerodynamic configuration Download PDFInfo
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- CN202783771U CN202783771U CN201220460278.3U CN201220460278U CN202783771U CN 202783771 U CN202783771 U CN 202783771U CN 201220460278 U CN201220460278 U CN 201220460278U CN 202783771 U CN202783771 U CN 202783771U
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Abstract
The utility model relates to the technical field of aircraft aerodynamic configuration design. An aircraft aerodynamic configuration comprises an aircraft body (3), outer wing sections (1) and inner wing sections (2); and the aircraft aerodynamic configuration is characterized in that the wing surfaces of the outer wing sections (1) and the inner wing sections (2) adopt laminar wing types, the inner wing sections (2) are wing body transition sections, adopt medium sweepback angles and small span-chord ratios, are connected with the aircraft body and are integrated with the wing bodies, and the outer wing sections (1) adopt medium sweepforward angles and medium span-chord ratios and are sweepforward wings. The aircraft aerodynamic configuration not only satisfies the requirements of the high-altitude long-endurance aircrafts on high subsonic cruising, the flying velocity is also increased and the problem of difficult balancing is solved.
Description
Technical field
The utility model relates to the aerodynamic configuration of aircraft design field.
Background technology
Aircraft is the crystallization of contemporary advanced science and cutting edge technology, is the system engineering of a complexity, 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 it is more reasonable than swept wing that wing distributes along exhibition to load.For example: HFB 320 HANSA transport planes and the X-29 technical identification machine of U.S.'s development just adopt this wing design.
Flying-wing is that a kind of wing body merges, and the part fuselage is hidden in the thick wing, and without the aircraft configuration topological design of 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 the sweepback Flying-wing, from aerodynamic configuration, wing and fuselage combine together, whole airplane is similar to a lifting surface, can decrease interference drag and induced drag, simultaneously, owing to removed horizontal tail and vertical fin, reduced the quantity of corner reflector, without obvious fuselage, Stealth Fighter has been promoted greatly.But still there is following technological deficiency in existing Flying-wing:
(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 affects limited when low speed, but the part that wing is relatively thick when high subsonic speed can produce larger drag effect, makes it be not suitable for high-speed flight, and more responsive than normal arrangement to the variation of speed.
(2) trim problem.Existing Flying-wing in order to calibrate very little trim, needs the moving lifting rudder face in flat flying, thereby increases the trim resistance, has also increased the pressure of fore-and-aft control face.
Summary of the invention
(1) the purpose of this utility model
For the aircraft speed that solves in the above-mentioned Flying-wing is hanged down and the trim hard problem, thereby a kind of improved aerodynamic configuration of aircraft is proposed.
(2) the technical solution of the utility model
The utility model is taked 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, interior wing panel is wing body transition phase, adopt 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) the beneficial effects of the utility model
The HAE high subsonic speed that the utility model not only the satisfies aircraft requirement of cruising has also improved flying speed and has solved the trim hard problem.
Description of drawings
Fig. 1 is aircraft profile schematic perspective view.
Fig. 2 is the aircraft plan sketch.
The specific embodiment
Embodiment of the present utility model is as follows: 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 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 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; 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 substantially from trim, namely 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), the aerofoil that it is characterized in that outer panel (1) and interior wing panel (2) adopts laminar f1ow airfoil profile, interior wing panel (2) is 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 |
|---|---|---|---|
| CN201220460278.3U CN202783771U (en) | 2012-09-11 | 2012-09-11 | Aircraft aerodynamic configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201220460278.3U CN202783771U (en) | 2012-09-11 | 2012-09-11 | Aircraft aerodynamic configuration |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202783771U true CN202783771U (en) | 2013-03-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201220460278.3U Expired - Lifetime CN202783771U (en) | 2012-09-11 | 2012-09-11 | Aircraft aerodynamic configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202783771U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102826216A (en) * | 2012-09-11 | 2012-12-19 | 江西洪都航空工业集团有限责任公司 | Aerodynamic configuration of aircraft |
| CN109250105A (en) * | 2018-09-25 | 2019-01-22 | 成都飞机工业（集团）有限责任公司 | A kind of variable configuration supersonic speed flying wing layout plane and its flying method |
-
2012
- 2012-09-11 CN CN201220460278.3U patent/CN202783771U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102826216A (en) * | 2012-09-11 | 2012-12-19 | 江西洪都航空工业集团有限责任公司 | Aerodynamic configuration of aircraft |
| CN109250105A (en) * | 2018-09-25 | 2019-01-22 | 成都飞机工业（集团）有限责任公司 | A kind of variable configuration supersonic speed flying wing layout plane and its flying method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130313 |
|
| CX01 | Expiry of patent term |