CN102442422A - Winglet for increasing pneumatic efficiency of horizontal tail of time-domain airplane - Google Patents
Winglet for increasing pneumatic efficiency of horizontal tail of time-domain airplane Download PDFInfo
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- CN102442422A CN102442422A CN2011103461468A CN201110346146A CN102442422A CN 102442422 A CN102442422 A CN 102442422A CN 2011103461468 A CN2011103461468 A CN 2011103461468A CN 201110346146 A CN201110346146 A CN 201110346146A CN 102442422 A CN102442422 A CN 102442422A
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- winglet
- horizontal tail
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Abstract
The invention provides a winglet for increasing pneumatic efficiency of a horizontal tail of a time-domain airplane. The winglet has a pneumatic profile as below: a wing root employs a NACA0012 aerofoil profile and has a chord length of 500 mm; a wingtip employs a NACA0009 aerofoil profile and has a chord length of 300 mm; a ratio of wing root to wingtip of the winglet is 0.6; a stretched length of the winglet is 800 mm; a profile from the wing root to the wingtip of the winglet is in linear transition; the winglets are uprightly arranged on stabilizers of horizontal tails on two sides of the airplane and on a position 75% of a horizontal tail stretched length; an upper surface and a lower surface of each horizontal tail are respectively provided with a winglet, and totally four winglets are in symmetry in the left-right direction. The invention has advantages that without changing a basic dimension of the horizontal tail, winglets are added to realize goals of increasing pneumatic efficiency of the horizontal tail and improving airplane course stability. As the basic profile dimension of the horizontal tail remains unchanged, the arrangement positions of the winglets are optimized and have little influence on an elevator; and tests also show that addition of the winglets causes no unfavorable influence on elevator control rule.
Description
Technical field
The present invention is a kind of winglet that improves time domain aircraft horizontal tail pneumatic efficiency, belongs to the pneumatics field of aircraft.
Background technology
Y12IV type aircraft time domain aircaft configuration characteristics are for carrying machine with Y12IV type aircraft; Through the be diversion specific electromagnetic signal of cable emission of machine of suspension installation ring; Utilize towing to collect background return then, survey subsurface mineral according to reflected signal at the detection gondola of afterbody.In order to satisfy above-mentioned requirements; Need carry out the profile repacking to Y12IV type aircraft, plant the repacking design and still belong to the first time at home, because the repacking coverage is very wide; The profile of repacking back Y12IV type aircraft has had great changes, and the original aerodynamic characteristic of aircraft has been produced bigger negative effect.
Summary of the invention
The present invention designs to the requirement of above-mentioned prior art equipment just a kind of winglet that improves time domain aircraft horizontal tail pneumatic efficiency is provided; This kind winglet is to be used for Y12IV type aircraft for carrying the time domain aircraft of machine; Its objective is that the pneumatic efficiency that improves horizontal tail improves the aerodynamic characteristic of time domain aircraft, increases vector stability and longitudinal controllability.
Horizontal tail is one of main Pneumatic component of aircraft; Consider the complexity of Y12IV type time domain aircraft; Technical scheme of the present invention is under the situation that does not change original horizontal tail leading dimensions; The method of the winglet through installing particular design additional realizes goal of the invention, and technical scheme of the present invention comprises following content:
This kind improves the winglet of time domain aircraft horizontal tail pneumatic efficiency, and it is characterized in that: the aerodynamic configuration of this winglet is: wing root adopts NACA0012 aerofoil profile, root chord length 500mm; The wing adopts the NACA0009 aerofoil profile slightly, and the wing is chord length 300mm slightly, and the root of winglet is slightly than being 0.6; The exhibition of winglet is long to be 800mm; 1/4 string of a musical instrument sweepback angle of winglet (4) is 0 °, and winglet is erect and is installed on the stabilator of aircraft both sides horizontal tail, and the position is at 75% long place of horizontal tail exhibition; Respectively adorn a slice, left-right symmetric distribution up and down, install four altogether.
The NACA aerofoil profile is the NACA series aerofoil profile of National Advisory Committee for Aeronautics (being called for short NACA) research and development, is maturation and the classical aerofoil profile that on a large amount of experimental basis, obtains, and NACA series airfoil is disclosed to countries in the world.The aircraft of countries in the world development generally adopts NACA series aerofoil profile.
When aircraft flight, winglet can produce favourable aerodynamic interference with horizontal tail, has improved the local flow field quality of horizontal tail, and the exhibition that reduces horizontal tail prevents the expansion in horizontal tail surface isolation district to flowing, and has increased the lift of horizontal tail, improves the horizontal tail pneumatic efficiency.Owing to erect the bigger area of winglet tool, when breakking away, can produce certain yawing moment simultaneously, because the installation site of winglet is comparatively reasonable, less to the influence degree of vertical fin, course stability total behind both mutual actions still increases again.Bright through Y12IV type time domain aircraft wind-tunnel test card, the efficient that horizontal tail installation winglet can increase horizontal tail also makes the course stability of aircraft that certain increase is arranged simultaneously.
The advantage of technical scheme of the present invention is: under the prerequisite that does not change basic specifications such as horizontal tail type, exhibition length, chord length,, increase vector stability through on horizontal tail, installing the pneumatic efficiency that winglet improves horizontal tail additional, and less to the influence of elevator control rule.
Description of drawings
Fig. 1 is the front elevation of the mounting structure of winglet of the present invention
Fig. 2 is the lateral plan of Fig. 1
Fig. 3 is the scheme drawing of the installation site of winglet of the present invention
Fig. 4 for the pitching moment coefficient of winglet of the present invention to angle of attack figure
Fig. 5 for the yawing moment coefficient of winglet of the present invention to angle of side slip figure
The specific embodiment
Below will combine accompanying drawing and embodiment that the invention technical scheme is done to detail further:
Shown in accompanying drawing 1～3, this kind improves the winglet of time domain aircraft horizontal tail pneumatic efficiency, and it is characterized in that: the aerodynamic configuration of this winglet 4 is: wing root adopts the NACA0012 aerofoil profile; Root chord length 500mm, the wing adopts the NACA0009 aerofoil profile slightly, and the wing is chord length 300mm slightly; Than being 0.6, the exhibition of winglet 4 is long to be 800mm to the root of winglet 4 slightly, and 1/4 string of a musical instrument sweepback angle of winglet (4) is 0 °; The wing root of winglet 4 is a straight transitions to wing profile slightly, and winglet 4 is erect and is installed on the stabilator 5 of aircraft 1 both sides horizontal tail 3, and makes the deicing cover of winglet 4 and horizontal tail 3 leading edges not produce constructive interference to reduce the interference to elevating rudder simultaneously as far as possible; Interfere vertical fin 2 not when breakking away simultaneously; The installation site of winglet 4 is respectively adorned a slice, left-right symmetric distribution up and down at 75% long place of horizontal tail 3 exhibitions, installs four altogether.
Shown in accompanying drawing 4; Installing the attack against each other basic law of angular curve of the full machine pitching moment coefficients in winglet 4 back additional does not change; Show that improving design does not change horizontal tail 3 original aerodynamic characteristics basically, and one about 0.04 step has appearred in two curves, the aircraft 1 that winglet 4 is installed when being illustrated in the identical angle of attack has increased by about 0.04 nose-up pitching moment than prototype pitching moment; The knowledge horizontal tail in many institute's weeks is main providers of nose-up pitching moment, this shows that the pneumatic efficiency of horizontal tail is improved.
Shown in accompanying drawing 5, the yawing moment coefficient that installs the full machine in winglet 4 backs additional is big to the slope change of angle of side slip, i.e. coursekeeping derivative m
y βBecome big, the course stability of aircraft has strengthened, and this just shows the effect that the winglet that installs additional on the horizontal tail can play increases yawing moment raising course stability.
Technical scheme of the present invention receives 863 Program 2006AA06A206 problem and subsidizes; Compared with prior art; Technical scheme of the present invention reaches the purpose that improves the horizontal tail pneumatic efficiency, increases vector stability through installing winglet additional under the prerequisite that does not change the horizontal tail leading dimensions.Because the basic oad of horizontal tail does not have variation, very little to the influence of elevating rudder through the installation site of preferred winglet again, test shows that also installing winglet additional does not have a negative impact to the elevator control rule.
Claims (1)
1. winglet that improves time domain aircraft horizontal tail pneumatic efficiency, it is characterized in that: the aerodynamic configuration of this winglet (4) is: wing root adopts NACA0012 aerofoil profile, root chord length 500mm; The wing adopts the NACA0009 aerofoil profile slightly, and the wing is chord length 300mm slightly, and the root of winglet (4) is slightly than being 0.6; The exhibition of winglet (4) is long to be 800mm; 1/4 string of a musical instrument sweepback angle of winglet (4) is 0 °, and winglet (4) is erect and is installed on the stabilator (5) of aircraft (1) both sides horizontal tails (3), and the position is at 75% long place of horizontal tail (3) exhibition;, install four altogether.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103461468A CN102442422A (en) | 2011-11-04 | 2011-11-04 | Winglet for increasing pneumatic efficiency of horizontal tail of time-domain airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103461468A CN102442422A (en) | 2011-11-04 | 2011-11-04 | Winglet for increasing pneumatic efficiency of horizontal tail of time-domain airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102442422A true CN102442422A (en) | 2012-05-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011103461468A Pending CN102442422A (en) | 2011-11-04 | 2011-11-04 | Winglet for increasing pneumatic efficiency of horizontal tail of time-domain airplane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108116662A (en) * | 2016-11-28 | 2018-06-05 | 成都飞机工业（集团）有限责任公司 | A kind of no empennage airplane yawing control method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201224495Y (en) * | 2008-06-24 | 2009-04-22 | 北京航空航天大学 | Wing tip winglet of 150-seat trunkliner |
| US20090256029A1 (en) * | 2008-04-15 | 2009-10-15 | The Boeing Company | Winglets with Recessed Surfaces, and Associated Systems and Methods |
| CN101596934A (en) * | 2009-07-02 | 2009-12-09 | 北京航空航天大学 | A kind of wing-tip vortex disperser |
-
2011
- 2011-11-04 CN CN2011103461468A patent/CN102442422A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090256029A1 (en) * | 2008-04-15 | 2009-10-15 | The Boeing Company | Winglets with Recessed Surfaces, and Associated Systems and Methods |
| CN201224495Y (en) * | 2008-06-24 | 2009-04-22 | 北京航空航天大学 | Wing tip winglet of 150-seat trunkliner |
| CN101596934A (en) * | 2009-07-02 | 2009-12-09 | 北京航空航天大学 | A kind of wing-tip vortex disperser |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108116662A (en) * | 2016-11-28 | 2018-06-05 | 成都飞机工业（集团）有限责任公司 | A kind of no empennage airplane yawing control method |
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Application publication date: 20120509 |