GB761077A - Improvements in or relating to aeroplanes - Google Patents
Improvements in or relating to aeroplanesInfo
- Publication number
- GB761077A GB761077A GB32071/53A GB3207153A GB761077A GB 761077 A GB761077 A GB 761077A GB 32071/53 A GB32071/53 A GB 32071/53A GB 3207153 A GB3207153 A GB 3207153A GB 761077 A GB761077 A GB 761077A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aerofoil
- air
- slot
- duct
- leading edge
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
761,077. Aircraft. GALLAWAY, I. U. M. Nov. 19, 1954 [Nov. 19, 1953], No. 32071/53. Class 4. An aeroplane comprises at least one main aerofoil having a rounded leading edge 7, and, in line with and in advance of each such aerofoil, an auxiliary aerofoil 1 with a sharp leading edge and a slot 3 in its trailing edge into which air at a desired pressure may be introduced, the aerofoil being designed to have its centre of pressure downstream of its neutral axis 4 i.e. the axis passing through the centres of gravity of chordioise sections, about which it is rotatable. In Fig. 3, the spanwise slot 3 is fed with air from a spanwise duct 2. The slot may be of varying cross section at different chordioise stations, and bleed holes may be provided from the interior of the slot to the exterior upper or lower surface of the aerofoil 1. A duct 5 for deicing fluid is provided. The aerofoil 1 may be in chord 10 per cent of the chord of the main aerofoil, and be symmetrical about a horizontal plane. Stops are fitted to limit the maximum free swing of the aerofoil 1 which may be mounted on a leading edge flop. Air for the duct 2 may be bled from a jet engine compressor, and this air may be heated for deicing and reducing the viscosity of the boundary layer on the main aerofoil 7. The device is stated to be useful in the transonic region, and may also be used to give an indication of the angle of attack, or as an emergency air speed indicator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB32071/53A GB761077A (en) | 1953-11-19 | 1953-11-19 | Improvements in or relating to aeroplanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB32071/53A GB761077A (en) | 1953-11-19 | 1953-11-19 | Improvements in or relating to aeroplanes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB761077A true GB761077A (en) | 1956-11-07 |
Family
ID=10332739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB32071/53A Expired GB761077A (en) | 1953-11-19 | 1953-11-19 | Improvements in or relating to aeroplanes |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB761077A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1147850B (en) * | 1956-05-31 | 1963-04-25 | United Aircraft Corp | Aircraft wing with low aspect ratio |
| US4483497A (en) * | 1973-03-16 | 1984-11-20 | Rethorst Scott C | Wide-body supersonic aircraft |
| US6113036A (en) * | 1997-02-04 | 2000-09-05 | Degraffenried; Albert L. | Boundary layer control system |
| US7861966B2 (en) | 2005-04-18 | 2011-01-04 | Vehicle Research Corporation | Supersonic aircraft footprint spreading control system and method |
| CN114906316A (en) * | 2022-04-15 | 2022-08-16 | 西华大学 | Supersonic blowing circular quantity trailing edge device and aircraft |
-
1953
- 1953-11-19 GB GB32071/53A patent/GB761077A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1147850B (en) * | 1956-05-31 | 1963-04-25 | United Aircraft Corp | Aircraft wing with low aspect ratio |
| US4483497A (en) * | 1973-03-16 | 1984-11-20 | Rethorst Scott C | Wide-body supersonic aircraft |
| US6113036A (en) * | 1997-02-04 | 2000-09-05 | Degraffenried; Albert L. | Boundary layer control system |
| US7861966B2 (en) | 2005-04-18 | 2011-01-04 | Vehicle Research Corporation | Supersonic aircraft footprint spreading control system and method |
| CN114906316A (en) * | 2022-04-15 | 2022-08-16 | 西华大学 | Supersonic blowing circular quantity trailing edge device and aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Jacobs | Preliminary report on laminar-flow airfoils and new methods adopted for airfoil and boundary-layer investigations | |
| Schwenk et al. | A preliminary analysis of the magnitude of shock losses in transonic compressors | |
| GB761077A (en) | Improvements in or relating to aeroplanes | |
| GB518663A (en) | Improvements in or relating to aircraft, hydroplanes and the like | |
| GB605765A (en) | Improvements in or relating to aerofoil sections for low reynolds numbers | |
| GB474065A (en) | Improvements in or relating to surfaces adapted to be displaced in a fluid medium | |
| GB408457A (en) | Improvements in or relating to sustaining or propelling surfaces particularly aeroplane wing structures | |
| FR928469A (en) | Improvements to aerodynes equipped with jet thrusters | |
| Harvell et al. | Aerodynamic characteristics of a circulation control elliptical airfoil with two blown jets | |
| Hilbig et al. | Aerodynamic design trends for commercial aircraft | |
| Welsh et al. | Flight Investigation at Mach Numbers From 0.8 to 1.5 of the Drag of a Canopy Located at Two Positions on a Parabolic Body of Revolution | |
| SU69339A1 (en) | Aircraft | |
| Sandahl | Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing | |
| Hall et al. | Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-percent-thick Triangular Wing and 6-and 9-percent-thick Triangular Wings in Combination with a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections | |
| Stueper | Flight Experiences and tests on two airplanes with suction slots | |
| Blenkush et al. | Effect of Dive Brakes on Airfoil and Airplane Characteristics | |
| RELF et al. | THE 42ND JAMES FORREST LECTURE 1936. MODERN DEVELOPMENTS IN THE DESIGN OF AEROPLANES. | |
| GB536904A (en) | Aeroplanes | |
| Thompson | Hinge-moment, Lift, and Pitching-moment Characteristics of a Flap-type Control Surface Having Various Hinge-line Locations on a 4-percent-thick 60 Degree Delta Wing: Transonic Bump Method | |
| Neely et al. | Effects of Wing and Nacelle Modifications on Drag and Wake Characteristics of a Bomber-type Airplane Model | |
| Hills | Use of Wind Tunnel Model Data in Aerodynamic Design | |
| ARC | 314 VOL. 59 JOURNAL OF THE ROYAL AERONAUTICAL SOCIETY APRIL 1955 | |
| Hoerner | Skin Drag of High Speed Aircraft: The Laws for the Drag of Smooth and Rough Flat Surfaces Applied to Aircraft | |
| Fowler | Determination of the Influence of Propeller Thrust on C L and C D of an Airplane Using a Triple-Slotted Flap at Various Deflections | |
| Hoffman et al. | Transonic Flight Tests To Compare the Zero-Lift Drags of 450 Sweptback Wings of Aspect Ratio 3.55 and 6.0 With and Without Nacelles at the Wing Tips |