GB675994A - Improvements in or relating to aircraft wings - Google Patents
Improvements in or relating to aircraft wingsInfo
- Publication number
- GB675994A GB675994A GB20370/48A GB2037048A GB675994A GB 675994 A GB675994 A GB 675994A GB 20370/48 A GB20370/48 A GB 20370/48A GB 2037048 A GB2037048 A GB 2037048A GB 675994 A GB675994 A GB 675994A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- flap
- duct
- slots
- slot
- 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.)
- Expired
Links
- 230000000694 effects Effects 0.000 abstract 2
- 239000012530 fluid Substances 0.000 abstract 2
- 239000007789 gas Substances 0.000 abstract 2
- 230000000994 depressogenic effect Effects 0.000 abstract 1
- 238000007689 inspection Methods 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/04—Boundary layer controls by actively generating fluid flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
-
- 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)
- Jet Pumps And Other Pumps (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
675,994. Controlling aircraft. OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES and SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU SUD-OUEST. July 30, 1948 [July 31, 1947; Dec. 22, 1947; July 17, 1948], Nos. 20370/48, 20371/48 and 20372/48. Class 4. An aircraft wing comprises a main section and two pivotal sections whereby the camber of the wing can be varied, the upper surface of said main section defining with the upper surface of one of said pivotal sections an air inlet slot which is variable as said pivotal section is moved to vary the camber of the wing, an airflow discharge slot formed at the upper rear portion of that wing section which lies between the two other sections, a spanwise directed pipe disposed between said air inlet and discharge slots, fluid ejecting means operated through said pipe, a mixing chamber establishing communication between said inlet and discharge slots, and means for supplying fluid under pressure to said ejecting means through said pipe to produce an aspirating effect by the latter for cansing a sheet of air to be drawn in through said inlet slot and discharged through said discharge slot. The device comprises a spanwise duct 10 which may be formed with a rearwardly directed coutinuous slot or may be provided with longitudinally spaced nozzles. The duct is supplied with compressed air or exhaust gases which it ejects into chordwise ducts 9 arranged to eject at 2 through the aperture formed between the trailing edge flaps 6 and the wing. The leading edge of the wing is provided with a nose flap 4 hinged about its lower edge so that when depressed it forms a gap 1 with the wing. The ejector effect of the nozzle 10 creates an airflow through the gap 1 and the duct 9 to control the airflow over the leading edge of the wing and the upper surface of the flap 6. In an alternative arrangement, Fig. 3 (not shown), the duct 10 may comprise two concentric ducts, one supplied with compressed air and the other with exhaust gases. In a further arrangement, Fig. 5 (not shown), the trailing edge of the wing may be provided with a first flap to which is pivoted a second flap. The nozzle 10 and the duct 9 may be installed inside the first flap to draw air from the gap formed between the flap and the wing and eject it through the gap formed between the first and second flaps. The nozzle 10 may be located on the hinge axis of the first flap and arranged to rotate therewith. The Specification as open to inspection under Sect. 91, comprises also a number of embodiments in which a is provided with a single trailing edge flap only and air inlet slots are provided in the fixed upper surface of the wing. A further embodiment is described applied to fuselages and nacelles in which continuous circumferential air inlet and outlet slots are formed in the outer panelling, ejector devices being mounted within the body between the slots. This subject-matter does not appear in the Specification as accepted.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR675994X | 1947-07-31 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB675994A true GB675994A (en) | 1952-07-23 |
Family
ID=9019647
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB20370/48A Expired GB675994A (en) | 1947-07-31 | 1948-07-30 | Improvements in or relating to aircraft wings |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB675994A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1013174B (en) * | 1953-08-12 | 1957-08-01 | Power Jets Res & Dev Ltd | Aircraft with lift control devices, e.g. Flaps, on the wing trailing edges |
GB2324351A (en) * | 1997-04-18 | 1998-10-21 | British Aerospace | Reducing drag in aircraft wing assembly |
WO2008057065A3 (en) * | 2005-08-09 | 2008-09-25 | Boeing Co | Lift augmentation system and associated method |
EP2955105A1 (en) | 2014-06-10 | 2015-12-16 | Instytut Lotnictwa | Autonomous active flow control system |
CN113071667A (en) * | 2021-03-12 | 2021-07-06 | 南京航空航天大学 | Method for improving wave resistance of amphibious aircraft based on active flow control technology |
WO2022128035A1 (en) * | 2020-12-15 | 2022-06-23 | Amonyx Aps | Airfoil with augmented lift |
-
1948
- 1948-07-30 GB GB20370/48A patent/GB675994A/en not_active Expired
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1013174B (en) * | 1953-08-12 | 1957-08-01 | Power Jets Res & Dev Ltd | Aircraft with lift control devices, e.g. Flaps, on the wing trailing edges |
GB2324351A (en) * | 1997-04-18 | 1998-10-21 | British Aerospace | Reducing drag in aircraft wing assembly |
US6135395A (en) * | 1997-04-18 | 2000-10-24 | British Aerospace Public Limited Company | Aircraft wing leading edge high lift device with suction |
WO2008057065A3 (en) * | 2005-08-09 | 2008-09-25 | Boeing Co | Lift augmentation system and associated method |
US8033510B2 (en) | 2005-08-09 | 2011-10-11 | The Boeing Company | Lift augmentation system and associated method |
EP2955105A1 (en) | 2014-06-10 | 2015-12-16 | Instytut Lotnictwa | Autonomous active flow control system |
WO2022128035A1 (en) * | 2020-12-15 | 2022-06-23 | Amonyx Aps | Airfoil with augmented lift |
CN113071667A (en) * | 2021-03-12 | 2021-07-06 | 南京航空航天大学 | Method for improving wave resistance of amphibious aircraft based on active flow control technology |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3161377A (en) | Apparatus for controlling aircraft | |
EP1720765B1 (en) | Apparatus and method for the control of trailing wake flows | |
US2841344A (en) | Boundary layer control | |
US3090584A (en) | Aircraft | |
US2568813A (en) | Jet-propelled aircraft with boundary layer control | |
US3051413A (en) | Vtol aircraft | |
US2478793A (en) | Variable camber airfoil | |
GB1436097A (en) | Method and apparatus for elimination of airfoil trailing vortices | |
US2577919A (en) | Association on flying machine of compressor-jet units with ramjet units | |
JPH01301495A (en) | Lift generator, flying body using same and lift generating method | |
US2912189A (en) | Jet propelled aircraft with jet flaps | |
GB750601A (en) | Improvements in jet nozzles and jet propulsion units | |
GB675994A (en) | Improvements in or relating to aircraft wings | |
US2961192A (en) | Jet propelled aircraft | |
US2848867A (en) | Ejector-silencer exhaust nozzle | |
GB634332A (en) | Improvements in and relating to rotary wing aircraft | |
GB484405A (en) | Improvements in aircraft | |
GB510546A (en) | Improvements relating to high-lift aerofoils | |
GB636045A (en) | Improvements in aircraft equipped with reaction jet propulsion means | |
GB596367A (en) | Improvements in airfoils | |
USRE24917E (en) | Aircraft high lift supercirculation system | |
GB871470A (en) | Improvements relating to aircraft incorporating vertical thrust generators | |
US3100094A (en) | Sweptwing jet flow control means | |
US3031156A (en) | Exhaust systems for jet propulsion engines | |
GB889540A (en) | Improvements in or relating to jet propelled aircraft |