GB661960A - Improvements in and relating to aircraft and aircraft wings - Google Patents

Improvements in and relating to aircraft and aircraft wings

Info

Publication number
GB661960A
GB661960A GB1109/49A GB110949A GB661960A GB 661960 A GB661960 A GB 661960A GB 1109/49 A GB1109/49 A GB 1109/49A GB 110949 A GB110949 A GB 110949A GB 661960 A GB661960 A GB 661960A
Authority
GB
United Kingdom
Prior art keywords
aircraft
auxiliary
turbine
jet
propeller
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
GB1109/49A
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 GB1109/49A priority Critical patent/GB661960A/en
Publication of GB661960A publication Critical patent/GB661960A/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
    • B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

661,960. Jet propulsion plant. STALKER, E. A. Jan. 14, 1949. No. 1109/49. Class 110(iii). [Also in Group XXXIII] An aircraft with means for boundary layer control comprises a jet propulsive device auxiliary to the main propulsion means for the aircraft and arranged to receive air from the boundary layer control means, the total amount of air supplied to the auxiliary jet device being controlled in accordance with flight conditions. As shown, the air drawn throughwing slots 44, 45 is fed to an annular duct 20 surrounding a turbine-propeller' unit 1, 14, passing through an auxiliary compressor 22 coupled to the turbine shaft by an over-running clutch 32, and then to a combustion chamber fitted with fuel burners 50, from which it is discharged with the exhaust from the main turbine 6 through a variable-area nozzle 54. The provision of the clutch 32 enables the compressor 22 to be driven by the propeller 14 when the latter is windmilling, for example, during landing. The airflow through the duct 20 is augmented during take-off by withdrawing a valve ring 46 to open an annular inlet 47 at the leading edge of the nacelle.
GB1109/49A 1949-01-14 1949-01-14 Improvements in and relating to aircraft and aircraft wings Expired GB661960A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1109/49A GB661960A (en) 1949-01-14 1949-01-14 Improvements in and relating to aircraft and aircraft wings

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1109/49A GB661960A (en) 1949-01-14 1949-01-14 Improvements in and relating to aircraft and aircraft wings

Publications (1)

Publication Number Publication Date
GB661960A true GB661960A (en) 1951-11-28

Family

ID=9716327

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1109/49A Expired GB661960A (en) 1949-01-14 1949-01-14 Improvements in and relating to aircraft and aircraft wings

Country Status (1)

Country Link
GB (1) GB661960A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1041803B (en) * 1952-11-28 1958-10-23 Rudolf Wurzbach Dr Ing Propulsion surface, especially for aircraft

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1041803B (en) * 1952-11-28 1958-10-23 Rudolf Wurzbach Dr Ing Propulsion surface, especially for aircraft

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