GB488942A - Improvements in or connected with aerofoil surfaces for aircraft - Google Patents
Improvements in or connected with aerofoil surfaces for aircraftInfo
- Publication number
- GB488942A GB488942A GB1397/37A GB139737A GB488942A GB 488942 A GB488942 A GB 488942A GB 1397/37 A GB1397/37 A GB 1397/37A GB 139737 A GB139737 A GB 139737A GB 488942 A GB488942 A GB 488942A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aerofoil
- passage
- wing
- chord
- aircraft
- 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
- 230000004048 modification Effects 0.000 abstract 2
- 238000012986 modification Methods 0.000 abstract 2
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/146—Adjustable control surfaces or members, e.g. rudders forming slots at an other wing location than the rear or the front
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/20—Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
-
- 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
-
- 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
- Y02T50/30—Wing lift efficiency
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
488,942. Controlling aircraft. VICKERS (AVIATION), Ltd., and ELLIS, D. L. Jan. 16, 1937, No. 1397. [Class 4] An aerofoil surface for aircraft has openings in its upper and lower surfaces communicating with each other by a passage or passages combined with a separately formed member spaced beneath the aerofoil and shaped to form a convergent-divergent passage between it and the aerofoil, the member extending for a part only of the chord of the aerofoil and being so located that the point of minimum depth of the passage is situated directly beneath the opening in the lower surface. As shown, an auxiliary aerofoil a extends for 25 per cent only of the chord of the aerofoil b and is disposed beneath a passage d. The aerofoil a may be retracted into the recess e. In a modification, the passage f, g, Fig. 2, connects the wing surfaces and the aerofoil a is disposed nearer the leading edge of the wing. In a further modification, the passage g terminates in the rear edge of an aerofoil provided with a flap which in its normal position closes the passage. The auxiliary aerofoil may be disposed at any point on the chord of the main wing and may be adjustable to vary the size of the passage. The size of the passage through the wing may be adjustable.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1397/37A GB488942A (en) | 1937-01-16 | 1937-01-16 | Improvements in or connected with aerofoil surfaces for aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1397/37A GB488942A (en) | 1937-01-16 | 1937-01-16 | Improvements in or connected with aerofoil surfaces for aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB488942A true GB488942A (en) | 1938-07-18 |
Family
ID=9721284
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1397/37A Expired GB488942A (en) | 1937-01-16 | 1937-01-16 | Improvements in or connected with aerofoil surfaces for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB488942A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2631794A (en) * | 1947-07-22 | 1953-03-17 | Douglas K Warner | Airfoil nose flap arrangement |
US2809793A (en) * | 1947-07-22 | 1957-10-15 | Douglas K Warner | High lift airfoil system |
DE1078875B (en) * | 1957-07-03 | 1960-03-31 | Flugzeugwerke Dresden Veb | Body flowed over with slits that lead from one side of the flow to the other |
FR2555676A1 (en) * | 1983-11-24 | 1985-05-31 | Messerschmitt Boelkow Blohm | METHOD FOR SUBJECTING THE DETACHED LAMINARY BOUNDARY LAYER TO A STABILIZING INFLUENCE |
GB2285669A (en) * | 1994-01-13 | 1995-07-19 | Short Brothers Plc | Boundary layer control in aerodynamic structures |
FR2850353A1 (en) * | 2003-01-29 | 2004-07-30 | Const Aeronautiques Du Nord Es | Air flow turbulence modulator comprises duct through rear part of wing and suction unit beneath it to draw air flow from upper surface |
CN117446152A (en) * | 2023-12-22 | 2024-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Cracking type control surface structure and aircraft |
-
1937
- 1937-01-16 GB GB1397/37A patent/GB488942A/en not_active Expired
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2631794A (en) * | 1947-07-22 | 1953-03-17 | Douglas K Warner | Airfoil nose flap arrangement |
US2809793A (en) * | 1947-07-22 | 1957-10-15 | Douglas K Warner | High lift airfoil system |
DE1078875B (en) * | 1957-07-03 | 1960-03-31 | Flugzeugwerke Dresden Veb | Body flowed over with slits that lead from one side of the flow to the other |
FR2555676A1 (en) * | 1983-11-24 | 1985-05-31 | Messerschmitt Boelkow Blohm | METHOD FOR SUBJECTING THE DETACHED LAMINARY BOUNDARY LAYER TO A STABILIZING INFLUENCE |
GB2285669A (en) * | 1994-01-13 | 1995-07-19 | Short Brothers Plc | Boundary layer control in aerodynamic structures |
US5743493A (en) * | 1994-01-13 | 1998-04-28 | Short Brothers Plc | Boundary layer control in aerodynamic low drag structures |
GB2285669B (en) * | 1994-01-13 | 1998-06-10 | Short Brothers Plc | Boundary layer control in aerodynamic low drag structures |
FR2850353A1 (en) * | 2003-01-29 | 2004-07-30 | Const Aeronautiques Du Nord Es | Air flow turbulence modulator comprises duct through rear part of wing and suction unit beneath it to draw air flow from upper surface |
CN117446152A (en) * | 2023-12-22 | 2024-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Cracking type control surface structure and aircraft |
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