GB338998A - Improvements in or relating to aeroplanes - Google Patents

Improvements in or relating to aeroplanes

Info

Publication number
GB338998A
GB338998A GB26868/29A GB2686829A GB338998A GB 338998 A GB338998 A GB 338998A GB 26868/29 A GB26868/29 A GB 26868/29A GB 2686829 A GB2686829 A GB 2686829A GB 338998 A GB338998 A GB 338998A
Authority
GB
United Kingdom
Prior art keywords
valve
leading edge
passage
pivoted
wing
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
GB26868/29A
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.)
HUBER WILLIAM BEEDLE
Original Assignee
HUBER WILLIAM BEEDLE
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 HUBER WILLIAM BEEDLE filed Critical HUBER WILLIAM BEEDLE
Priority to GB26868/29A priority Critical patent/GB338998A/en
Publication of GB338998A publication Critical patent/GB338998A/en
Expired legal-status Critical Current

Links

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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Air-Flow Control Members (AREA)
  • Toys (AREA)

Abstract

338,998. Beedle, H. W. Sept. 4, 1929. Planes, construction of; controlling.-For controlling the airflow about a wing, one or more openings are formed near the leading edge extending in the direction of the front spar and provided with pivoted valves on the upper or lower surface controlled automatically by a wind vane which acts to close the valves when a predetermined speed is reached. Fig. 1 shows an upwardly and rearwardly inclined passage closed at its lower end by a flap 4 pivoted at an intermediate point 5 near its leading edge. When the machine is at rest or flying at a low speed this valve is held open by a light spring, but as the speed increases it is closed by a, vane 6 connected thereto by an arm 7 and link 8. A light closing spring 9 may also be provided. The device may be formed as a unit to replace part of the main wing which is cut away to accommodate it. Alternatively, the passage may extend downwardly and rearwardly and be controlled by a valve which normally closes the upper surface of the wing and is pivoted at a point nearer to the trailing edge than the leading edge of the valve. This valve may be combined with another valve on the lower surface so that when the leading edge of the upper valve is raised that of the lower valve is depressed to admit air to the passage, both streams escaping through a comparatively restricted opening on the under surface at the rear edge of the passage.
GB26868/29A 1929-09-04 1929-09-04 Improvements in or relating to aeroplanes Expired GB338998A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB26868/29A GB338998A (en) 1929-09-04 1929-09-04 Improvements in or relating to aeroplanes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB26868/29A GB338998A (en) 1929-09-04 1929-09-04 Improvements in or relating to aeroplanes

Publications (1)

Publication Number Publication Date
GB338998A true GB338998A (en) 1930-12-04

Family

ID=10250476

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26868/29A Expired GB338998A (en) 1929-09-04 1929-09-04 Improvements in or relating to aeroplanes

Country Status (1)

Country Link
GB (1) GB338998A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109592001A (en) * 2017-09-30 2019-04-09 莫文彩 It is a kind of to prevent the aircraft that strong ascending air causes its wing stall to drop
CN109592006A (en) * 2017-09-30 2019-04-09 莫文彩 A kind of method and wing prevented aircraft and encounter the wing stall tenesmus of strong ascending air

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109592001A (en) * 2017-09-30 2019-04-09 莫文彩 It is a kind of to prevent the aircraft that strong ascending air causes its wing stall to drop
CN109592006A (en) * 2017-09-30 2019-04-09 莫文彩 A kind of method and wing prevented aircraft and encounter the wing stall tenesmus of strong ascending air

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