GB718421A - Improvements relating to boundary layer control means for aerofoils and other boundary walls - Google Patents
Improvements relating to boundary layer control means for aerofoils and other boundary wallsInfo
- Publication number
- GB718421A GB718421A GB3383/51A GB338351A GB718421A GB 718421 A GB718421 A GB 718421A GB 3383/51 A GB3383/51 A GB 3383/51A GB 338351 A GB338351 A GB 338351A GB 718421 A GB718421 A GB 718421A
- Authority
- GB
- United Kingdom
- Prior art keywords
- filler
- layer control
- boundary layer
- boundary
- ridges
- 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
- 239000000945 filler Substances 0.000 abstract 5
- 239000012530 fluid Substances 0.000 abstract 3
- 239000004020 conductor Substances 0.000 abstract 2
- 239000002184 metal Substances 0.000 abstract 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 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
- B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for 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
- B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
718,421. Boundary layer control. FAIREY AVIATION CO., Ltd., and HOOPER, M. S. Feb. 4, 1952 [Feb. 12 1951], No. 3383/51. Class 4 Boundary layer control means for fluid flowing relatively to a boundary wall is provided by the wall consisting of an inner and an outer perforated skin, 18 and 17, with a porous or granular filler 19 and means for drawing the fluid through all three layers. The stressed skin 11 of the aerofoil shown in Fig. 1 is formed with ridges 15 and 16 to correspond to ridges 20 in the boundary wall, and which may be fastened thereto by rivets, or by screwing down into spars 12. The spaces between skins 18 and 11, and consecutive ridges, form ducts through which the indrawn fluid may be guided. The ducts are joined to a manifold at the root of the wing, to which the suction means is also coupled. Control valves may be provided to restrict the flow through all or certain of the ducts. Deicing may be accomplished by passing an electric current through the filler 19 by electrodes 52 and 53 or electrode 51 and the perforated skins, which filler may be a conductor, e.g. carbon granules, or coated with a suitable conducting material. Provision may be made for similar boundary layer control of any part of the aircraft surface. The degree of perforation of the inner and outer skins, and the porosity of the filler may be varied from place to place. The filler may be confined by metal gauze or the like, to leave an air gap between it and the inner or outer skin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3383/51A GB718421A (en) | 1951-02-12 | 1951-02-12 | Improvements relating to boundary layer control means for aerofoils and other boundary walls |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3383/51A GB718421A (en) | 1951-02-12 | 1951-02-12 | Improvements relating to boundary layer control means for aerofoils and other boundary walls |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB718421A true GB718421A (en) | 1954-11-17 |
Family
ID=9757296
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3383/51A Expired GB718421A (en) | 1951-02-12 | 1951-02-12 | Improvements relating to boundary layer control means for aerofoils and other boundary walls |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB718421A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2833492A (en) * | 1955-02-07 | 1958-05-06 | Harlan D Fowler | Boundary layer control system with aerodynamic glove |
| US2867392A (en) * | 1955-08-19 | 1959-01-06 | Lear Inc | Boundary layer control for aircraft |
| US2925231A (en) * | 1956-02-29 | 1960-02-16 | Martin Co | Boundary layer removal structure |
| WO1992021560A1 (en) * | 1991-05-30 | 1992-12-10 | Short Brothers Plc | Boundary layer control |
| DE4414205A1 (en) * | 1994-04-23 | 1995-10-26 | Daimler Benz Aerospace Airbus | Arrangement for boundary layer suction of aircraft |
| US9511848B2 (en) | 2010-04-12 | 2016-12-06 | Airbus Operations Gmbh | Profile plate portion for use as an outer wall of a flow body, method for manufacturing a profile plate portion and flow body component comprising a suction-extraction device for fluid |
| US10967955B2 (en) | 2017-10-09 | 2021-04-06 | Airbus Operations Gmbh | Vertical tail unit for flow control |
| US10974817B2 (en) | 2017-10-09 | 2021-04-13 | Airbus Operations Gmbh | Vertical tail unit for flow control |
| US11040769B2 (en) | 2017-07-11 | 2021-06-22 | Airbus Operations Gmbh | Leading edge structure for a flow control system of an aircraft |
| US11142296B2 (en) | 2017-10-20 | 2021-10-12 | Airbus Operations Limited | Apparatus for laminar flow control |
-
1951
- 1951-02-12 GB GB3383/51A patent/GB718421A/en not_active Expired
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2833492A (en) * | 1955-02-07 | 1958-05-06 | Harlan D Fowler | Boundary layer control system with aerodynamic glove |
| US2867392A (en) * | 1955-08-19 | 1959-01-06 | Lear Inc | Boundary layer control for aircraft |
| US2925231A (en) * | 1956-02-29 | 1960-02-16 | Martin Co | Boundary layer removal structure |
| WO1992021560A1 (en) * | 1991-05-30 | 1992-12-10 | Short Brothers Plc | Boundary layer control |
| DE4414205A1 (en) * | 1994-04-23 | 1995-10-26 | Daimler Benz Aerospace Airbus | Arrangement for boundary layer suction of aircraft |
| DE4414205C2 (en) * | 1994-04-23 | 1999-09-02 | Daimler Chrysler Aerospace | Arrangement for boundary layer suction |
| US9511848B2 (en) | 2010-04-12 | 2016-12-06 | Airbus Operations Gmbh | Profile plate portion for use as an outer wall of a flow body, method for manufacturing a profile plate portion and flow body component comprising a suction-extraction device for fluid |
| EP2558362B1 (en) * | 2010-04-12 | 2018-07-25 | Airbus Operations GmbH | Profile-plate portion for use as an outer wall of a flow body, and flow-body component with a suction-extraction device for fluid |
| US11040769B2 (en) | 2017-07-11 | 2021-06-22 | Airbus Operations Gmbh | Leading edge structure for a flow control system of an aircraft |
| US10967955B2 (en) | 2017-10-09 | 2021-04-06 | Airbus Operations Gmbh | Vertical tail unit for flow control |
| US10974817B2 (en) | 2017-10-09 | 2021-04-13 | Airbus Operations Gmbh | Vertical tail unit for flow control |
| US11565795B2 (en) | 2017-10-09 | 2023-01-31 | Airbus Operations Gmbh | Vertical tail unit for flow control |
| US11142296B2 (en) | 2017-10-20 | 2021-10-12 | Airbus Operations Limited | Apparatus for laminar flow control |
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