DE2149956B2 - HIGH-FLOATING WINGS - Google Patents
HIGH-FLOATING WINGSInfo
- Publication number
- DE2149956B2 DE2149956B2 DE19712149956 DE2149956A DE2149956B2 DE 2149956 B2 DE2149956 B2 DE 2149956B2 DE 19712149956 DE19712149956 DE 19712149956 DE 2149956 A DE2149956 A DE 2149956A DE 2149956 B2 DE2149956 B2 DE 2149956B2
- Authority
- DE
- Germany
- Prior art keywords
- wing
- wings
- aircraft
- lift
- induced
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
- B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
- B64C23/076—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
- B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
- B64C23/072—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips the wing tip airfoil devices being moveable in their entirety
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
flügel 3 am weitesten nach obea und der hinterste Der mittlere Teil ιwing 3 furthest to obea and the rearmost the middle part ι
Teilflügel 6 am weitesten nach unten verschwenkt ist Der in F i g. 3 dargestellte Flügel besitzt zwei Teilflügel 3 und 4, die mit Klappen 8 und 10 versehenPartial wing 6 is pivoted the furthest downward in FIG. 3 wing shown has two wing parts 3 and 4, which are provided with flaps 8 and 10
sind. Diese Klappen sind am die Achsen9 und 11 TeüflügeU nach unten verschwenkt Hier-are. These flaps are pivoted downwards on the axes 9 and 11 TeüflugU.
"SSV »i*^ *d-— .. ind^er- ftSl,^«^,,^"SSV» i * ^ * d-— .. ind ^ er ftSl, ^ «^ ,, ^
Hierzu 1 Blatt Zeichnungen1 sheet of drawings
Claims (4)
weitesten nach oben und der hinterste (6) am Da die Erfindung sich insbesondere auf Hochaufweitesten nach unten eingestellt ist 15 triebsflugzeuge bezieht, kann sie bei Segelflugzeugen, 2. High lift wing according to claim 1, da- io is characterized in two or more smaller edge vortices on through that the sub-wings (3, 4, 5, divided, which overlay each other and here-6) in the pivoted state fan-like through each other influence so that the effective of the stand, the foremost wing part (3) is advantageously increased at the wing extension,
furthest to the top and the rearmost (6) at the Since the invention relates in particular to high-expansion downwards 15 propulsion aircraft, it can be used in gliders,
Flügelenden ausgehenden Wirbelbänder besonders Die durch die Erfindung erzielten Vorteile beste-The invention relates to a high-lift wing, according to a further feature of the invention its induced drag is improved in comparison with her- 30 in that the sub-wings are provided with adjustable wing constructions for a minimum of ren flaps. The flaps are supposed to be reduced in size. As is well known, the induced drag from the swiveled-out position of the wing elements is invented in a wing by being set in such a way that the flap diagonally downwards and upwards at the wing end due to the pressure equalization between the lower wing and the front wing element Flow 35 the flap of the rear wing part is caused obliquely to mung, which is directed to the formation of a we- above. This results in an optimal rebel area behind the wing, whereby the reduction of the induced drag is achieved.
Vertebral ligaments emanating from the wing tips in particular The advantages achieved by the invention
trächtlichen Bestandteil des Gesamtwiderstandes dar, 45 Ausführungsbeispiele der Erfindung sind in der für dessen Überwindung ein entsprechender Anteil Zeichnung dargestellt. Es zeigt
der Triebwerksleistung verbraucht wird. F i g. 1 die Gesamtansicht eines Flugzeuges, dasTo overcome the induced resistance 40 of those in short-take-off aircraft, in a smaller minimum during the flight, work constantly works, a better glide and become, which is the greater, the greater the rate of climb and the more stable flight behavior at high- Wing generated lift is. The induced lift and better maneuvering performance of hunting resistance in high-lift aircraft provide an aircraft with a greater range,
A significant component of the total resistance, 45 exemplary embodiments of the invention are shown in the drawing for overcoming it. It shows
the engine power is consumed. F i g. 1 the general view of an aircraft that
Verringerung des induzierten Widerstandes besteht F i g. 4 die Seitenansicht eines Tragflügels mit zweiAnother well-known means of being fitted with flaps,
There is a reduction in the induced drag. 4 is a side view of a wing with two
gern. Eine ähnlich wirkende Lösung ergibt sich bei der Das in F i g. 1 dargestellte Hochauftriebsflugzeug 1in the attachment of end disks to the wing parts, which are provided with flaps, in resting ends, which reduce the intensity of the tip vortices in the swiveled-out position,
gladly. A solution that has a similar effect results from the example in FIG. 1 depicted high-lift aircraft 1
Vermeidung der aufgeführten Nachteile den indu- Die F i g. 2 zeigt einen mit vier Teilflügeln 3, 4,The invention is based on the object, under 65 wings 4 or 4 'pivoted downwards.
Avoidance of the listed disadvantages the indu- The F i g. 2 shows one with four partial wings 3, 4,
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2149956A DE2149956C3 (en) | 1971-10-07 | 1971-10-07 | High lift wing |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2149956A DE2149956C3 (en) | 1971-10-07 | 1971-10-07 | High lift wing |
Publications (3)
Publication Number | Publication Date |
---|---|
DE2149956A1 DE2149956A1 (en) | 1973-04-12 |
DE2149956B2 true DE2149956B2 (en) | 1973-08-16 |
DE2149956C3 DE2149956C3 (en) | 1974-03-28 |
Family
ID=5821655
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE2149956A Expired DE2149956C3 (en) | 1971-10-07 | 1971-10-07 | High lift wing |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE2149956C3 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3643070A1 (en) * | 1986-12-17 | 1988-06-30 | Messerschmitt Boelkow Blohm | ROLL-UP WING-EDGE FLAP |
Families Citing this family (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4172574A (en) * | 1976-06-16 | 1979-10-30 | National Research Development Corporation | Fluid stream deflecting members for aircraft bodies or the like |
US4598885A (en) * | 1979-03-05 | 1986-07-08 | Waitzman Simon V | Airplane airframe |
DE3242584A1 (en) * | 1982-11-18 | 1984-05-24 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | ARRANGEMENT OF ADDITIONAL SURFACES AT THE TIPS OF AN WING |
DE3621800A1 (en) * | 1986-06-28 | 1988-01-07 | Riedelsheimer Hans Joachim | PLANE |
DE19626333A1 (en) * | 1996-07-01 | 1998-01-08 | Zf Luftfahrttechnik Gmbh | Device for auxiliary power supply to aeroplane |
FR2783885B1 (en) * | 1998-09-25 | 2001-07-27 | Geco As | SUPPORTING STRUCTURE WITH REDUCED MARGINAL TOURBILLON |
DE19926832B4 (en) | 1999-06-12 | 2005-09-15 | Airbus Deutschland Gmbh | Subsonic aircraft preferably with swept-up wings |
JP4535550B2 (en) | 2000-02-23 | 2010-09-01 | 富士重工業株式会社 | Rotor blade of rotorcraft |
DE10160315A1 (en) | 2001-12-07 | 2003-11-13 | Airbus Gmbh | Device for the approach control of an aircraft |
FR2841532B1 (en) | 2002-06-27 | 2004-12-17 | Airbus France | AIRCRAFT WITH ACTIVE WINGER TURN CONTROL |
DE10302514B4 (en) * | 2003-01-23 | 2008-12-18 | Eads Deutschland Gmbh | Fluid-mechanically effective surface of a moving in a fluid device, in particular an aircraft, in particular wing of an aircraft |
DE602006007118D1 (en) * | 2005-04-18 | 2009-07-16 | Airbus Gmbh | SYSTEM AND METHOD FOR REDUCING SURFACE SWIVELS |
DE102005017825A1 (en) | 2005-04-18 | 2006-10-26 | Airbus Deutschland Gmbh | Aircraft`s wake reducing system, has component provided fixed unit and two aerofoil units, which are periodically swivelable between end positions for interference of rolling procedure of air in area of outer aerofoil in flight direction |
RU2009113854A (en) | 2006-09-15 | 2010-10-20 | Эрбус Дойчланд Гмбх (De) | AERODYNAMIC BODY, AND ALSO A WING WITH AERODYNAMIC BODY, COMBINATION OF A COMPUTER AND WING OR AERODYNAMIC BODY, METHOD OF INFLUENCE ON THE CONTROL SIGNALS FOR A COMPUTER SERVICE SYSTEM AND A COMPUTER SERVICE DRIVER |
US7900876B2 (en) * | 2007-08-09 | 2011-03-08 | The Boeing Company | Wingtip feathers, including forward swept feathers, and associated aircraft systems and methods |
US20090084904A1 (en) * | 2007-10-02 | 2009-04-02 | The Boeing Company | Wingtip Feathers, Including Paired, Fixed Feathers, and Associated Systems and Methods |
US8128035B2 (en) | 2008-04-15 | 2012-03-06 | The Boeing Company | Winglets with recessed surfaces, and associated systems and methods |
WO2009155584A1 (en) | 2008-06-20 | 2009-12-23 | Aviation Partners, Inc. | Curved wing tip |
US9302766B2 (en) | 2008-06-20 | 2016-04-05 | Aviation Partners, Inc. | Split blended winglet |
US9162755B2 (en) | 2009-12-01 | 2015-10-20 | Tamarack Aerospace Group, Inc. | Multiple controllable airflow modification devices |
US20110127383A1 (en) | 2009-12-01 | 2011-06-02 | Guida Associates Consulting, Inc. | Active winglet |
GB201011843D0 (en) * | 2010-07-14 | 2010-09-01 | Airbus Operations Ltd | Wing tip device |
CN106081070A (en) | 2011-06-09 | 2016-11-09 | 航空伙伴股份有限公司 | Spiral type wing tip and aircraft |
US8936219B2 (en) | 2012-03-30 | 2015-01-20 | The Boeing Company | Performance-enhancing winglet system and method |
EP2834146B1 (en) * | 2012-04-03 | 2023-10-11 | Tamarack Aerospace Group, Inc. | Multiple controllable airflow modification devices |
US9511850B2 (en) | 2014-04-12 | 2016-12-06 | The Boeing Company | Wing tip device for an aircraft wing |
GB2533413A (en) | 2014-12-19 | 2016-06-22 | Airbus Operations Ltd | Lifting Surfaces |
JP6621585B2 (en) * | 2015-02-27 | 2019-12-18 | 三菱重工業株式会社 | Flutter control device |
EP3269635A1 (en) | 2016-07-12 | 2018-01-17 | The Aircraft Performance Company UG | Airplane wing |
KR20200028930A (en) | 2017-07-12 | 2020-03-17 | 더 에어크래프트 퍼포먼스 컴퍼니 게엠베하 | Aircraft wing with at least 2 winglets |
ES2819559T3 (en) | 2017-12-15 | 2021-04-16 | The Aircraft Performance Company Gmbh | Airplane wing |
EP3511243B1 (en) | 2018-01-15 | 2021-12-29 | The Aircraft Performance Company GmbH | Airplane wing |
US11254412B2 (en) | 2019-03-29 | 2022-02-22 | The Boeing Company | Foldable raked wing tips having aerodynamic devices |
-
1971
- 1971-10-07 DE DE2149956A patent/DE2149956C3/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3643070A1 (en) * | 1986-12-17 | 1988-06-30 | Messerschmitt Boelkow Blohm | ROLL-UP WING-EDGE FLAP |
Also Published As
Publication number | Publication date |
---|---|
DE2149956A1 (en) | 1973-04-12 |
DE2149956C3 (en) | 1974-03-28 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
C3 | Grant after two publication steps (3rd publication) |