GB620409A - Thrust-increasing device for aircraft operated by the engine exhaust - Google Patents

Thrust-increasing device for aircraft operated by the engine exhaust

Info

Publication number
GB620409A
GB620409A GB20184/46A GB2018446A GB620409A GB 620409 A GB620409 A GB 620409A GB 20184/46 A GB20184/46 A GB 20184/46A GB 2018446 A GB2018446 A GB 2018446A GB 620409 A GB620409 A GB 620409A
Authority
GB
United Kingdom
Prior art keywords
aircraft
nacelle
engine exhaust
flaps
boundary layer
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
GB20184/46A
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.)
Societe Nationale des Constructions Aeronautiques du Sud Est SNCASE
Original Assignee
Societe Nationale des Constructions Aeronautiques du Sud Est SNCASE
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 Societe Nationale des Constructions Aeronautiques du Sud Est SNCASE filed Critical Societe Nationale des Constructions Aeronautiques du Sud Est SNCASE
Publication of GB620409A publication Critical patent/GB620409A/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
    • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
    • 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)
  • Testing Of Engines (AREA)

Abstract

620,409. Propelling aircraft. SOC. NATIONALE DE CONSTRUCTION AERONAUTIQUES DU SUD-EST. July 5, 1946, No.20184. Convention date, April 4. [Class 4] [Also in Group XXVI] A thrust-augmenter for aircraft comprises an adjustable guide nozzle into which the engine exhaust gases are fed, the nozzle sucking in a mixture of air from the external atmosphere and the boundary layers on the surfaces of the aircraft. As shown, the jet nozzle is formed by two flaps V<SP>1</SP>, V<SP>2</SP> placed at the trailing edge of the engine nacelle F and which may be rotated about the axes of transverse passages A<SP>1</SP>, A<SP>2</SP> through which the engine exhaust gases are discharged over the walls of the flaps. In the construction shown in Fig. 1, air is sucked into the centre of the jet stream from the atmosphere and the nacelle boundary layer L, while in the arrangement according to Fig. 4 additional air is drawn from the wing boundary layer through slots F <SP>3</SP>, F<SP>4</SP>, and from the engine radiator R placed beneath the nacelle. The ratio between the boundary layer airflow and the flow through the radiator is controlled by a flap K, or by separate flaps placed in the respective flow passages.
GB20184/46A 1946-04-04 1946-07-05 Thrust-increasing device for aircraft operated by the engine exhaust Expired GB620409A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR620409X 1946-04-04

Publications (1)

Publication Number Publication Date
GB620409A true GB620409A (en) 1949-03-24

Family

ID=8984388

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20184/46A Expired GB620409A (en) 1946-04-04 1946-07-05 Thrust-increasing device for aircraft operated by the engine exhaust

Country Status (1)

Country Link
GB (1) GB620409A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1219332B (en) * 1960-11-08 1966-06-16 Tomijiro Moriya Wing with a control flap hinged on the underside
DE1285894B (en) * 1963-08-29 1968-12-19 Dehavilland Aircraft Canada Airplane wing with trailing edge flaps
US9587585B1 (en) * 2013-04-30 2017-03-07 The United States Of America As Represented By The Secretary Of The Air Force Augmented propulsion system with boundary layer suction and wake blowing

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1219332B (en) * 1960-11-08 1966-06-16 Tomijiro Moriya Wing with a control flap hinged on the underside
DE1285894B (en) * 1963-08-29 1968-12-19 Dehavilland Aircraft Canada Airplane wing with trailing edge flaps
US9587585B1 (en) * 2013-04-30 2017-03-07 The United States Of America As Represented By The Secretary Of The Air Force Augmented propulsion system with boundary layer suction and wake blowing

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