CN204197270U - A kind of HAE fixed wing aircraft Airfoil - Google Patents
A kind of HAE fixed wing aircraft Airfoil Download PDFInfo
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- CN204197270U CN204197270U CN201420652423.7U CN201420652423U CN204197270U CN 204197270 U CN204197270 U CN 204197270U CN 201420652423 U CN201420652423 U CN 201420652423U CN 204197270 U CN204197270 U CN 204197270U
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- aerofoil profile
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- gull
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Abstract
The utility model relates to a kind of for HAE fixed wing aircraft Airfoil.Its application reverse-engineering obtains the coordinate figure of the upper and lower surface of sea-gull wing aerofoil profile.The position that the position at imitative sea-gull aerofoil profile maximum ga(u)ge t place accounts for 9.1% ~ 9.7%, maximum camber f place of chord length accounts for 45.5% ~ 48.1% of chord length; Maximum ga(u)ge t reduces greatly than standard aerofoil profile, can prevent aerofoil profile from occurring too early separation like this, cause loss of lift; Maximum camber f is close with standard aerofoil profile, and the current difference of top and bottom is remained unchanged relatively, and the pressure reduction on top and bottom is certain, under similarity condition, obtain lift of the same size.Imitative sea-gull aerofoil profile of the present utility model has lower resistance and higher 1ift-drag ratio, and overall aerodynamic characteristic can be made to be improved.
Description
Technical field:
The utility model relates to a kind of aerofoil profile of HAE fixed wing aircraft wing.Be specifically related to the aerofoil profile of Altitude Long Endurance Unmanned Air Vehicle wing.
Technical background:
The outstanding performance of military unmanned air vehicle in the Gulf War, Afghan War and the Vietnam War, is subject to the attention of more and more national.Many countries are placed in precedence the development of military unmanned air vehicle.Major cause has the following aspects: one is in the modern and following war, and unmanned plane has the restriction of not climate condition, can go deep into overhead, dangerous zone and scout acquisition information for a long time.Two is that unmanned plane can consider human factor when designing.Three is the development cost of unmanned plane, productive costs and maintenance cost and lower than manned aircraft many, can also save a large amount of expenses of training aviator.Four is the today at energy shock, must seek the unmanned plane that oil consumption is less.Therefore military unmanned air vehicle is adopted must will to be following development tendency widely.
Altitude Long Endurance Unmanned Air Vehicle can be divided into (also to claim strategic unmanned plane according to cruise duration and voyage unmanned plane, as the U.S. " predator ", Israel " searcher " etc.) and low altitude short range unmanned plane (also claiming Micro Aerial Vehicle, " micro-V-type " unmanned plane as Israel).The wing of unmanned plane can be divided into fixed-wing, propeller type wing and folding wing.And in recent years, when heavy－duty, high-altitude, long boat, the low detectability development tendency that will be following unmanned plane, also become the hot issue of international airline circle research simultaneously.For the U.S. " global hawk ", aircraft have employed the straight wing (span reaches 35.4 meters) of high aspect ratio, its cruising altitude can reach 19800 meters, can at 5500 kilometers of (3000 nautical miles) target areas outward stagnant empty 24 hours, be greater than 42 hours maximum endurance, reconnaissance mission can be performed by weather-proof.Altitude Long Endurance Unmanned Air Vehicle is driven compared with strategic reconnaissance airplane with there being people, and its topmost advantage is: the safety problem need not considering people, when performing reconnaissance mission in hazardous location, both need not take one's life in one's hands, and also not need to send escort plane to be protected.Unmanned function continues to carry out aerial reconnaissance detection round the clock, and all someone drives less than strategic reconnaissance airplane for these.Altitude Long Endurance Unmanned Air Vehicle is compared with reconnaissance satellite, and with low cost is its maximum advantage, just satellite cost 1/tens, even more than one percent.
Altitude Long Endurance Unmanned Air Vehicle will in more than 20km high-altitude flight, and on the one hand due to rarefaction of air, flight dynamic pressure is little, and Reynolds number low (1,000,000 magnitude), meet the requirement of unmanned plane heavy－duty.On the other hand, due to flight during long boat, flight resistance must be reduced to reduce fuel oil consumption.Therefore Altitude Long Endurance Unmanned Air Vehicle will meet the such aeroperformance of high lift low resistance when designing.And wing to be aircraft produce the major part of lift, the aeroperformance of wing is the basis of research aircraft aeroperformance, affect the aeroperformance mainly plane parameter of wing and aerofoil profile decision.On the one hand for the plane parameter of wing only when aspect ratio and swirl distribution all reach optimum, aerofoil surface maintains more Laminar Flow region and avoids being separated the key factor just becoming less resistance, improve lift.Just require the feature adopting high lift aerofoil profile, little nose-down pitching moment and high lift-drag ratio on the other hand, such aerofoil profile can be avoided laminar flow separation bubble and postpone forwarding raw as much as possible.Therefore, the aerodynamic characteristic of aerofoil profile is also very important for the impact of the aeroperformance of wing.
Aristotle once said " if we want to find good answer to a problem, probably in the Nature, having had answer ".Bionic main task is the mechanism that the research excellent ability of biosystem or excellent properties produce, and it abstract be math modeling, then apply the technical equipment that these performances go Design and manufacture new.The process of Development of Human Civilization be unable to do without always and uses bionics thinking since ancient times, promotes the many utility models of human progress and create all to be unable to do without bionic thought.
At occurring in nature, birds directly contact with air with insect, and the wing of birds is also laterally arranged by a series of aerofoil profile to form, the most similar to fixed wing aircraft wing.The utility model take sea-gull as research object, is applied on aircraft by its wing aerofoil profile, intends at the fuel consumption rate reducing high-altitude fixed wing aircraft, during to extend boat.Sea-gull belongs to Lariformes, Laridae, and its chest muscle is flourishing, and being good at circling in the air, as long as up current a little just can glide across the sea for a long time, is the slowest birds that fly in the world.Be of value to like this and saving physical efficiency in-flight for a long time.
Utility model content:
The utility model relates to a kind of HAE fixed wing aircraft Airfoil, object commonly uses for fixed wing aircraft in the situation of high-altitude the situation that profile drag is comparatively large and 1ift-drag ratio is generally not high, make its resistance under compared with low reynolds number and the different angles of attack reduce 1ift-drag ratio to improve, imitative sea-gull aerofoil profile is applied on the fixed wing aircraft of high-altitude and greatly can reduces fuel consumption, when extending boat.
Above-mentioned purpose of the present utility model is achieved in that accompanying drawings is as follows:
A kind of HAE fixed wing aircraft Airfoil, be made up of chord length, thickness, leading-edge radius and camber, it is characterized in that, when described chord length c is 1, the value of maximum ga(u)ge t is 0.0670.0987, and the value of described leading-edge radius r is 0.028 ~ 0.063, and the span of described camber f is 0.051 ~ 0.083, and the position at maximum ga(u)ge t place accounts for 9.1% ~ 9.7% of the span of chord length c, the position at described maximum camber f place accounts for 45.5% ~ 48.1% of chord length c scope.
Leading-edge radius, the maximum ga(u)ge of imitative sea-gull aerofoil profile of the present utility model are less than standard aerofoil profile, and this can reduce the wind area of aerofoil profile thus reduce pressure drag; Preventing the air-flow in aerofoil profile from occurring premature disengagement when flowing through upper surface, causing loss of lift.
The utility model has the following advantages: aerofoil profile of the present utility model does not change shape own and surface texture just can obtain excellent aerodynamic characteristic; Range of angles of attack during experiment is-3 ° ~ 15 °, Reynolds number is 600000, and the drag coefficient recording imitative sea-gull aerofoil profile reduces 16.4% respectively than standard aerofoil profile, and 1ift-drag ratio improves 13.6% respectively than standard aerofoil profile.
The people such as the Li Guangning of Northwestern Polytechnical University use S-A turbulence model to carry out numerical modelling to the RAE2822 aerofoil profile of two dimension and three-dimensional ONERAM6 wing Viscous Flow, and result of calculation and external experimental result have been carried out contrasting and shown to select S-A turbulence model method for numerical simulation to have good precision and good comformability.The utility model selects S-A turbulence model when the flow field simulation to sea-gull wing.
Accompanying drawing illustrates:
The bionical aerofoil profile schematic diagram of Fig. 1.
Fig. 2 is that to carry out emulating the imitative sea-gull aerofoil profile and standard aerofoil profile fx63-137 that draw at the angle of attack with computing machine be-3 ° ~ 15 °, Mach 2 ship 0.2, the correlation curve figure of 1ift-drag ratio when Reynolds number is 600000.
Fig. 3 is that to carry out emulating the imitative sea-gull aerofoil profile and standard aerofoil profile fx63-137 that draw at the angle of attack with computing machine be-3 ° ~ 15 °, Mach 2 ship 0.2, the correlation curve figure of drag coefficient when Reynolds number is 600000.
Fig. 4 carries out emulating the imitative sea-gull aerofoil profile and standard aerofoil profile fx63-137 that draw at Mach 2 ship 0.2 with computing machine, and operating mode height is 20000m, the correlation curve figure of streamline when Reynolds number is 600000, pressure cloud atlas.
In figure: r-leading-edge radius, t-maximum ga(u)ge, f-camber, c-chord length, d-bending line, B-top airfoil, C-lower aerofoil
Detailed description of the invention:
When with reference to figure 1, to imitate sea-gull aerofoil profile chord length c be 1, the value of maximum ga(u)ge t is 0.067 ~ 0.0987, the value of described leading-edge radius r is 0.028 ~ 0.063, the span of described camber f is 0.051 ~ 0.083, and the position at maximum ga(u)ge t place account for chord length c span 9.1% ~ 9.7%, the position at described maximum camber f place accounts for 45.5% ~ 48.1% of chord length c scope.
Leading-edge radius, the maximum ga(u)ge of imitative sea-gull aerofoil profile of the present utility model are less than standard aerofoil profile, and this can reduce the wind area of aerofoil profile thus reduce pressure drag; Preventing the air-flow in aerofoil profile from occurring premature disengagement when flowing through upper surface, causing loss of lift.
Imitative coordinate figure corresponding to its upper and lower surface of sea-gull aerofoil profile meets following table:
Table 1
Fig. 2 be imitative sea-gull aerofoil profile and standard aerofoil profile 1ift-drag ratio with the change curve of the angle of attack, obtain through actual blowing experiment at wind tunnel laboratory.Can find out when Reynolds number is 600000, when the angle of attack is 5 °, the maximum lift-drag ratio of imitative sea-gull aerofoil profile is 22.2 add 10.1% than the maximum lift-drag ratio of standard aerofoil profile.Imitate sea-gull aerofoil profile when the angle of attack is respectively 8 °, 11 ° and improve 25.2%, 13.6% respectively than the 1ift-drag ratio of standard aerofoil profile.
Fig. 3 be imitative sea-gull aerofoil profile and standard profile drag coefficient with the change curve of the angle of attack, can find out, under positive incidence, the drag coefficient of imitative sea-gull aerofoil profile is all less than standard aerofoil profile, and all increases with the increase drag coefficient of the angle of attack.When Reynolds number is 600000, the resistance coefficient ratio standard aerofoil profile of imitating sea-gull aerofoil profile when the angle of attack is respectively 5 °, 8 °, 11 ° reduces 15.9%, 17.9%, 20.8% respectively.
Fig. 4 is sea-gull aerofoil profile and standard aerofoil profile streamline, equipressure line comparison diagram, can find out, at the same conditions, separation has just appearred in standard aerofoil profile air-flow when the angle of attack is 7 °, and sea-gull aerofoil profile is separated more late.
In summary it can be seen when the angle of attack is-3 ° ~ 15 °, the 1ift-drag ratio of the sea-gull aerofoil profile resistance lower than standard aerofoil profile fx63-137 and Geng Gao is imitated when Reynolds number is 600000, be applied on HAE fixed wing aircraft and can reduce fuel consumption rate, improve In-Flight Performance.
Claims (2)
1. a HAE fixed wing aircraft Airfoil, by chord length, thickness, leading-edge radius and camber composition, it is characterized in that, when described chord length (c) is 1, the value of maximum ga(u)ge (t) is 0.067 ~ 0.0987, the value of described leading-edge radius (r) is 0.028 ~ 0.063, the span of described camber (f) is 0.051 ~ 0.083, and the position at maximum ga(u)ge (t) place accounts for 9.1% ~ 9.7% of the span of chord length (c), the position at described maximum camber (f) place accounts for 45.5% ~ 48.1% of chord length (c) scope.
2. a kind of HAE fixed wing aircraft Airfoil according to claim 1, it is characterized in that, the coordinate figure corresponding to described Airfoil upper and lower surface is:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420652423.7U CN204197270U (en) | 2014-10-30 | 2014-10-30 | A kind of HAE fixed wing aircraft Airfoil |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420652423.7U CN204197270U (en) | 2014-10-30 | 2014-10-30 | A kind of HAE fixed wing aircraft Airfoil |
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| CN204197270U true CN204197270U (en) | 2015-03-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420652423.7U Withdrawn - After Issue CN204197270U (en) | 2014-10-30 | 2014-10-30 | A kind of HAE fixed wing aircraft Airfoil |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104354850A (en) * | 2014-10-30 | 2015-02-18 | 中国人民解放军空军航空大学 | Airfoil profile of airfoil of high-altitude long-endurance fixed-wing aircraft |
| CN105752314A (en) * | 2016-03-22 | 2016-07-13 | 西北工业大学 | High-altitude, low-speed and high-lift natural laminar flow airfoil |
-
2014
- 2014-10-30 CN CN201420652423.7U patent/CN204197270U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104354850A (en) * | 2014-10-30 | 2015-02-18 | 中国人民解放军空军航空大学 | Airfoil profile of airfoil of high-altitude long-endurance fixed-wing aircraft |
| CN105752314A (en) * | 2016-03-22 | 2016-07-13 | 西北工业大学 | High-altitude, low-speed and high-lift natural laminar flow airfoil |
| CN105752314B (en) * | 2016-03-22 | 2017-03-29 | 西北工业大学 | A kind of high-altitude low speed Natural Laminar Flow high-lift airfoil |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150311 Effective date of abandoning: 20160309 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |