GB484405A - Improvements in aircraft - Google Patents

Improvements in aircraft

Info

Publication number
GB484405A
GB484405A GB29804/36A GB2980436A GB484405A GB 484405 A GB484405 A GB 484405A GB 29804/36 A GB29804/36 A GB 29804/36A GB 2980436 A GB2980436 A GB 2980436A GB 484405 A GB484405 A GB 484405A
Authority
GB
United Kingdom
Prior art keywords
chamber
wing
aircraft
leading
conduit
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
GB29804/36A
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.)
Bristol Aeroplane Co Ltd
Original Assignee
Bristol Aeroplane Co Ltd
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 Bristol Aeroplane Co Ltd filed Critical Bristol Aeroplane Co Ltd
Priority to GB29804/36A priority Critical patent/GB484405A/en
Publication of GB484405A publication Critical patent/GB484405A/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
    • B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and 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
    • B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
    • 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)
  • Toys (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

484,405. Reducing drag on aircraft surfaces. BRISTOL AEROPLANE CO., Ltd., FEDDEN, A. H. R., and OWNER, F. M. Nov. 2, 1936, No. 29804. [Class 4] Means for reducing drag on aircraft surfaces comprise a chamber within the aircraft body, an inlet conduit leading to the chamber from perforations in the surface of the body, an ejector-nozzle within the chamber, an exhaustpipe leading from an aero-engine to the nozzle and an outlet conduit leading from said chamber to discharge air drawn from the boundary layer in a rearward direction. As shown, the exhaust gases from an aero engine 13 pass from a manifold forming the leading edge of a cowling 16 through a tail-pipe 21 to ejector-nozzles 22 disposed in a chamber 19 in an aircraft wing 10. Air is drawn through orifices 17 in the upper surface of the wing and is discharged together with the exhaust gases through a conduit 20. The outlet of the conduit 20 may be disposed in the under surface of the wing towards the trailing edge. The orifices may be formed of holes one sixty-fourth inch diameter and one quarter-inch pitch and be situated at about the middle of the wing chord. The nozzles 22 and chamber 19 may be designed to facilitate flow and may be designed to give a propulsive effect.
GB29804/36A 1936-11-02 1936-11-02 Improvements in aircraft Expired GB484405A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB29804/36A GB484405A (en) 1936-11-02 1936-11-02 Improvements in aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29804/36A GB484405A (en) 1936-11-02 1936-11-02 Improvements in aircraft

Publications (1)

Publication Number Publication Date
GB484405A true GB484405A (en) 1938-05-02

Family

ID=10297422

Family Applications (1)

Application Number Title Priority Date Filing Date
GB29804/36A Expired GB484405A (en) 1936-11-02 1936-11-02 Improvements in aircraft

Country Status (1)

Country Link
GB (1) GB484405A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2508288A (en) * 1944-12-08 1950-05-16 Bristol Aeroplane Co Ltd Gas turbine power plant for aircraft
US2517524A (en) * 1945-02-10 1950-08-01 Goodyear Aircraft Corp Boundary layer control
US2523378A (en) * 1945-11-28 1950-09-26 Kollsman Paul Wing-mounted jet reaction engine for aircraft
US2547936A (en) * 1944-11-17 1951-04-10 Harlow B Grow Ducted rocket propulsion means for aircraft
US2585676A (en) * 1947-07-31 1952-02-12 Poisson-Quinton Philippe Aircraft wing and flap with boundary layer control
US2742247A (en) * 1950-10-31 1956-04-17 Handley Page Ltd Outer surfaces for craft moving in one fluid
GB2344092A (en) * 1998-11-27 2000-05-31 David Albert Smyth Wing with airflow passage therethrough
FR2857650A1 (en) * 2003-07-19 2005-01-21 Rolls Royce Plc NACELLE OR LAMINAR FLOW SURFACE FOR AN AIRCRAFT ENGINE
CN106364666A (en) * 2016-09-30 2017-02-01 朱晓义 Wing generating larger lift force and aircraft
CN113955088A (en) * 2021-12-21 2022-01-21 中国空气动力研究与发展中心设备设计与测试技术研究所 Fluid thrust vector exciter

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2547936A (en) * 1944-11-17 1951-04-10 Harlow B Grow Ducted rocket propulsion means for aircraft
US2508288A (en) * 1944-12-08 1950-05-16 Bristol Aeroplane Co Ltd Gas turbine power plant for aircraft
US2517524A (en) * 1945-02-10 1950-08-01 Goodyear Aircraft Corp Boundary layer control
US2523378A (en) * 1945-11-28 1950-09-26 Kollsman Paul Wing-mounted jet reaction engine for aircraft
US2585676A (en) * 1947-07-31 1952-02-12 Poisson-Quinton Philippe Aircraft wing and flap with boundary layer control
US2742247A (en) * 1950-10-31 1956-04-17 Handley Page Ltd Outer surfaces for craft moving in one fluid
GB2344092A (en) * 1998-11-27 2000-05-31 David Albert Smyth Wing with airflow passage therethrough
FR2857650A1 (en) * 2003-07-19 2005-01-21 Rolls Royce Plc NACELLE OR LAMINAR FLOW SURFACE FOR AN AIRCRAFT ENGINE
CN106364666A (en) * 2016-09-30 2017-02-01 朱晓义 Wing generating larger lift force and aircraft
CN113955088A (en) * 2021-12-21 2022-01-21 中国空气动力研究与发展中心设备设计与测试技术研究所 Fluid thrust vector exciter

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