GB460636A - Aeroplane stabilising means - Google Patents
Aeroplane stabilising meansInfo
- Publication number
- GB460636A GB460636A GB21810/35A GB2181035A GB460636A GB 460636 A GB460636 A GB 460636A GB 21810/35 A GB21810/35 A GB 21810/35A GB 2181035 A GB2181035 A GB 2181035A GB 460636 A GB460636 A GB 460636A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fins
- wing
- chord
- inboard
- situated
- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fertilizers (AREA)
Abstract
460,636. Stabilizing aircraft. GRAY, W. E. Aug. 1, 1935, No. 21810. Drawings to Specification. [Class 4] A fixed lifting-wing for aeroplanes having a span several times as great as its mean chord, of aerofoil section and parallel or moderately tapered in plan is provided on its upper surface with a fin or fins near each wing-tip ; the fins lie approximately in or are skewed out from fore and aft vertical planes, extend over the whole or the major forward portion of the wing chord and are increased in height from the front towards the rear. The fins may have a mean height of about 15 to 25 per cent of the wing chord and may be situated in the region of <1>/6 or <1>/7 of the wing span from the wing-tips. The ailerons may be situated entirely or mainly outboard of the fins. In the latter case the rear ends of the fins may be telescopic. The fins may be applied to the inboard ends of automatically or manually operable or fixed wing-tip slot-forming slots. The fins may be folded into the wing surface and may have adjustable rear ends and the wing inboard of the fins, may be designed to have an early stall. The fins may be formed as cantilever structures fused into the wings.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB21810/35A GB460636A (en) | 1935-08-01 | 1935-08-01 | Aeroplane stabilising means |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB21810/35A GB460636A (en) | 1935-08-01 | 1935-08-01 | Aeroplane stabilising means |
Publications (1)
Publication Number | Publication Date |
---|---|
GB460636A true GB460636A (en) | 1937-02-01 |
Family
ID=10169192
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB21810/35A Expired GB460636A (en) | 1935-08-01 | 1935-08-01 | Aeroplane stabilising means |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB460636A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2649265A (en) * | 1948-07-30 | 1953-08-18 | Charles H Grant | Airplane with stabilizing fins |
US3960345A (en) * | 1975-05-16 | 1976-06-01 | Grumman Aerospace Corporation | Means to reduce and/or eliminate vortices, caused by wing body combinations |
US5806807A (en) * | 1995-10-04 | 1998-09-15 | Haney; William R. | Airfoil vortex attenuation apparatus and method |
DE102007054873B4 (en) * | 2006-11-16 | 2011-04-28 | Johann Valentin Krier | Deflection device for preventing the contamination of the boundary layer on wings of a missile in subsonic and trans-sonic flow through the fuselage or similar bodies |
-
1935
- 1935-08-01 GB GB21810/35A patent/GB460636A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2649265A (en) * | 1948-07-30 | 1953-08-18 | Charles H Grant | Airplane with stabilizing fins |
US3960345A (en) * | 1975-05-16 | 1976-06-01 | Grumman Aerospace Corporation | Means to reduce and/or eliminate vortices, caused by wing body combinations |
US5806807A (en) * | 1995-10-04 | 1998-09-15 | Haney; William R. | Airfoil vortex attenuation apparatus and method |
DE102007054873B4 (en) * | 2006-11-16 | 2011-04-28 | Johann Valentin Krier | Deflection device for preventing the contamination of the boundary layer on wings of a missile in subsonic and trans-sonic flow through the fuselage or similar bodies |
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