GB620409A - Thrust-increasing device for aircraft operated by the engine exhaust - Google Patents
Thrust-increasing device for aircraft operated by the engine exhaustInfo
- Publication number
- GB620409A GB620409A GB20184/46A GB2018446A GB620409A GB 620409 A GB620409 A GB 620409A GB 20184/46 A GB20184/46 A GB 20184/46A GB 2018446 A GB2018446 A GB 2018446A GB 620409 A GB620409 A GB 620409A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- nacelle
- engine exhaust
- flaps
- boundary layer
- 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
- 238000010276 construction Methods 0.000 abstract 2
- 239000007789 gas Substances 0.000 abstract 2
- 239000000203 mixture Substances 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
- B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
-
- 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)
- Testing Of Engines (AREA)
Abstract
620,409. Propelling aircraft. SOC. NATIONALE DE CONSTRUCTION AERONAUTIQUES DU SUD-EST. July 5, 1946, No.20184. Convention date, April 4. [Class 4] [Also in Group XXVI] A thrust-augmenter for aircraft comprises an adjustable guide nozzle into which the engine exhaust gases are fed, the nozzle sucking in a mixture of air from the external atmosphere and the boundary layers on the surfaces of the aircraft. As shown, the jet nozzle is formed by two flaps V<SP>1</SP>, V<SP>2</SP> placed at the trailing edge of the engine nacelle F and which may be rotated about the axes of transverse passages A<SP>1</SP>, A<SP>2</SP> through which the engine exhaust gases are discharged over the walls of the flaps. In the construction shown in Fig. 1, air is sucked into the centre of the jet stream from the atmosphere and the nacelle boundary layer L, while in the arrangement according to Fig. 4 additional air is drawn from the wing boundary layer through slots F <SP>3</SP>, F<SP>4</SP>, and from the engine radiator R placed beneath the nacelle. The ratio between the boundary layer airflow and the flow through the radiator is controlled by a flap K, or by separate flaps placed in the respective flow passages.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR620409X | 1946-04-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB620409A true GB620409A (en) | 1949-03-24 |
Family
ID=8984388
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB20184/46A Expired GB620409A (en) | 1946-04-04 | 1946-07-05 | Thrust-increasing device for aircraft operated by the engine exhaust |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB620409A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1219332B (en) * | 1960-11-08 | 1966-06-16 | Tomijiro Moriya | Wing with a control flap hinged on the underside |
| DE1285894B (en) * | 1963-08-29 | 1968-12-19 | Dehavilland Aircraft Canada | Airplane wing with trailing edge flaps |
| US9587585B1 (en) * | 2013-04-30 | 2017-03-07 | The United States Of America As Represented By The Secretary Of The Air Force | Augmented propulsion system with boundary layer suction and wake blowing |
-
1946
- 1946-07-05 GB GB20184/46A patent/GB620409A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1219332B (en) * | 1960-11-08 | 1966-06-16 | Tomijiro Moriya | Wing with a control flap hinged on the underside |
| DE1285894B (en) * | 1963-08-29 | 1968-12-19 | Dehavilland Aircraft Canada | Airplane wing with trailing edge flaps |
| US9587585B1 (en) * | 2013-04-30 | 2017-03-07 | The United States Of America As Represented By The Secretary Of The Air Force | Augmented propulsion system with boundary layer suction and wake blowing |
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