GB664288A - Improvements in or relating to stabilising devices for aircraft - Google Patents

Improvements in or relating to stabilising devices for aircraft

Info

Publication number
GB664288A
GB664288A GB10091/49A GB1009149A GB664288A GB 664288 A GB664288 A GB 664288A GB 10091/49 A GB10091/49 A GB 10091/49A GB 1009149 A GB1009149 A GB 1009149A GB 664288 A GB664288 A GB 664288A
Authority
GB
United Kingdom
Prior art keywords
members
airflow
fuselage
protuberance
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
Application number
GB10091/49A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to GB10091/49A priority Critical patent/GB664288A/en
Publication of GB664288A publication Critical patent/GB664288A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C17/00—Aircraft stabilisation not otherwise provided for

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mobile Radio Communication Systems (AREA)

Abstract

664,288. Controlling aircraft. YOUNGMAN, R. T. April 6, 1950 [April 14, 1949]. No. 10091/49. Class 4. An aircraft having a protuberance which under certain flight conditions tends to disturb the airflow over at least part of the main wing, is provided with a flow diverting member mounted at least partly in front of the leading edge of the wing in the neighbourhood of said protuberance to reduce the airflow disturbance caused by said protuberance and to divert the airflow back towards its normal path. the length of said flow diverting member being such that it does not extend appreciably outside the area in which airflow, disturbance tends to occur. A flow diverting member 12 is pivotally mounted on the fuselage 10 ahead of and preferably slightly above the main wing 11 and is arranged to be pivotally adjusted to the alternative positions 12a, 12b by a power drive 16. The members are mounted on a worm shaft 15 which, when rotated with the members 12 restrained in the horizontal position, will cause the members to be retracted within the fuselage. In alternative arrangements the members may be fixed to the fuselage or engine nacelles at a height corresponding to the maximum width thereof and may be planar, curved or of aerofoil cross section.
GB10091/49A 1949-04-14 1949-04-14 Improvements in or relating to stabilising devices for aircraft Expired GB664288A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB10091/49A GB664288A (en) 1949-04-14 1949-04-14 Improvements in or relating to stabilising devices for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB10091/49A GB664288A (en) 1949-04-14 1949-04-14 Improvements in or relating to stabilising devices for aircraft

Publications (1)

Publication Number Publication Date
GB664288A true GB664288A (en) 1952-01-02

Family

ID=9961308

Family Applications (1)

Application Number Title Priority Date Filing Date
GB10091/49A Expired GB664288A (en) 1949-04-14 1949-04-14 Improvements in or relating to stabilising devices for aircraft

Country Status (1)

Country Link
GB (1) GB664288A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3960345A (en) * 1975-05-16 1976-06-01 Grumman Aerospace Corporation Means to reduce and/or eliminate vortices, caused by wing body combinations
DE3029548A1 (en) * 1979-08-08 1981-02-26 British Aerospace PLANE
WO1984001347A1 (en) * 1982-09-30 1984-04-12 Boeing Co Shock inducing pod for causing flow separation
US4569494A (en) * 1982-12-23 1986-02-11 The Boeing Company Pitch control of swept wing aircraft
US4643376A (en) * 1982-09-30 1987-02-17 The Boeing Company Shock inducing pod for causing flow separation
US5496001A (en) * 1994-01-28 1996-03-05 Skow; Andrew T-38 aircraft modified with an F-5 wing
WO1999044887A1 (en) * 1998-03-06 1999-09-10 Batcho Paul F Method and apparatus for mitigating junction flows

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3960345A (en) * 1975-05-16 1976-06-01 Grumman Aerospace Corporation Means to reduce and/or eliminate vortices, caused by wing body combinations
DE3029548A1 (en) * 1979-08-08 1981-02-26 British Aerospace PLANE
US4381091A (en) * 1979-08-08 1983-04-26 British Aerospace Public Limited Company Control-effect enhancement of tiltable aircraft stabilizing member
WO1984001347A1 (en) * 1982-09-30 1984-04-12 Boeing Co Shock inducing pod for causing flow separation
US4643376A (en) * 1982-09-30 1987-02-17 The Boeing Company Shock inducing pod for causing flow separation
US4569494A (en) * 1982-12-23 1986-02-11 The Boeing Company Pitch control of swept wing aircraft
US5496001A (en) * 1994-01-28 1996-03-05 Skow; Andrew T-38 aircraft modified with an F-5 wing
WO1999044887A1 (en) * 1998-03-06 1999-09-10 Batcho Paul F Method and apparatus for mitigating junction flows

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