[go: up one dir, main page]

GB1019061A - Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies - Google Patents

Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies

Info

Publication number
GB1019061A
GB1019061A GB11505/61A GB1150561A GB1019061A GB 1019061 A GB1019061 A GB 1019061A GB 11505/61 A GB11505/61 A GB 11505/61A GB 1150561 A GB1150561 A GB 1150561A GB 1019061 A GB1019061 A GB 1019061A
Authority
GB
United Kingdom
Prior art keywords
extensions
bodies
apertures
wing
drag
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
GB11505/61A
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.)
HERBERT HARRY PEARCEY
Original Assignee
HERBERT HARRY PEARCEY
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 HERBERT HARRY PEARCEY filed Critical HERBERT HARRY PEARCEY
Priority to GB11505/61A priority Critical patent/GB1019061A/en
Publication of GB1019061A publication Critical patent/GB1019061A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • 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
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,019,061. Aircraft wings; boundary layer control. H. H. PEARCEY. June 25, 1961 [March 29, 1961], No. 11505/61. Headings B7G and B7W. [Also in Division F2] An aircraft wing 11 has a squared-off trailing edge TE with extensions 12, 13 having apertures 14 which may be holes, or open or closed slots, Figs. 20a-20d, not shown; the extensions may be parallel, as shown, or divergent or convergent. The boundary layer bleeds through the apertures to raise the pressure aft of edge LE and produces a smoother mixing of fluid downstream of the wing. The area of the apertures can be varied by apertured slides operated by jacks, Fig. 8, not shown; the downstream length of the extensions can also be varied by providing an adjustable false edge within the extensions. A lift spoiler or augmenter on the wing can have a slotted extension, Fig. 9d, not shown, and apertured extensions are shown on missiles, " re-entry " bodies, motor vehicles, and jet engine nozzles.
GB11505/61A 1961-03-29 1961-03-29 Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies Expired GB1019061A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB11505/61A GB1019061A (en) 1961-03-29 1961-03-29 Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB11505/61A GB1019061A (en) 1961-03-29 1961-03-29 Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies

Publications (1)

Publication Number Publication Date
GB1019061A true GB1019061A (en) 1966-02-02

Family

ID=9987485

Family Applications (1)

Application Number Title Priority Date Filing Date
GB11505/61A Expired GB1019061A (en) 1961-03-29 1961-03-29 Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies

Country Status (1)

Country Link
GB (1) GB1019061A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4444367A (en) * 1980-03-25 1984-04-24 National Research Development Corporation Aerofoil bodies
US5265830A (en) * 1992-01-21 1993-11-30 Mcdonnell Douglas Corporation Trailing edge splitter
EP2168869A1 (en) * 2007-06-15 2010-03-31 EADS Construcciones Aeronauticas, S.A. Device for reducing the cross-stream force generated by the section of air refuelling booms
DE202009010904U1 (en) * 2009-08-17 2010-12-30 Becker Marine Systems Gmbh & Co. Kg Hydrofoils for watercraft
WO2015014877A1 (en) * 2013-07-31 2015-02-05 Alpha Velorum Ag Method for increasing the range of spin-stabilized projectiles, and projectile of said type
WO2017067968A1 (en) * 2015-10-22 2017-04-27 Universität Stuttgart Aerodynamic body and use thereof
US20240076033A1 (en) * 2022-09-02 2024-03-07 Raytheon Technologies Corporation Aerial vehicle fluid control system integrated with gas turbine engine

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4444367A (en) * 1980-03-25 1984-04-24 National Research Development Corporation Aerofoil bodies
US5265830A (en) * 1992-01-21 1993-11-30 Mcdonnell Douglas Corporation Trailing edge splitter
EP2168869A4 (en) * 2007-06-15 2013-10-09 Eads Constr Aeronauticas Sa Device for reducing the cross-stream force generated by the section of air refuelling booms
EP2168869A1 (en) * 2007-06-15 2010-03-31 EADS Construcciones Aeronauticas, S.A. Device for reducing the cross-stream force generated by the section of air refuelling booms
DE202009010904U1 (en) * 2009-08-17 2010-12-30 Becker Marine Systems Gmbh & Co. Kg Hydrofoils for watercraft
EP2287071A3 (en) * 2009-08-17 2011-04-06 Becker Marine Systems GmbH & Co. KG Wing for water vehicles
CN101992852A (en) * 2009-08-17 2011-03-30 贝克船舶系统有限公司 Hydrofoil for water-borne vessels
CN101992852B (en) * 2009-08-17 2014-06-04 贝克船舶系统有限公司 Hydrofoil for water-borne vessels
WO2015014877A1 (en) * 2013-07-31 2015-02-05 Alpha Velorum Ag Method for increasing the range of spin-stabilized projectiles, and projectile of said type
US10094644B2 (en) 2013-07-31 2018-10-09 Alpha Velorum Ag Method for increasing the range of spin-stabilized projectiles, and projectile of said type
WO2017067968A1 (en) * 2015-10-22 2017-04-27 Universität Stuttgart Aerodynamic body and use thereof
US20240076033A1 (en) * 2022-09-02 2024-03-07 Raytheon Technologies Corporation Aerial vehicle fluid control system integrated with gas turbine engine
US12208884B2 (en) * 2022-09-02 2025-01-28 Rtx Corporation Aerial vehicle fluid control system integrated with gas turbine engine

Similar Documents

Publication Publication Date Title
GB1014238A (en) Improvements in ducted fan powerplants
GB1529885A (en) Aerofoil tip vortex control
GB1512719A (en) Vertical takeoff and landing aircraft
GB1019061A (en) Improvements relating to control of fluid flow past bodies and to reduction of drag of such bodies
GB2070139A (en) Inlet Cowl for Supersonic Aircraft Engine
GB1448245A (en) Combination jet engine clam-shell thrust reverser and variable nozzle area ramp
US3370810A (en) Stall control device for swept wings
US4235400A (en) Hi-lo two speed wing
DE2149590C3 (en) Aircraft with short take-off and landing capabilities
GB1187474A (en) Improvements in or relating to Aircraft
GB1014250A (en) Improvements in ducted fan powerplants
GB1151413A (en) Improvements in Jet-Propelled Aeroplanes
GB1463810A (en) Aircraft
GB1117266A (en) Supersonic intake for a jet propulsion engine
GB1029106A (en) Aircraft
Corlett et al. Aerodynamic characteristics at Mach 0. 60 to 4. 63 of two cruciform missile models, one having trapezoidal wings with canard controls and the other having delta wings with tail controls(Wind tunnel tests to determine aerodynamic characteristics of two missile configurations with common body at transonic and supersonic speeds)
Brebner The control of guided weapons
GB1365305A (en) Aircraft
MATEESCU Aerodynamic characteristics in supersonic regime of rectangular and trapezoidal wings with spanwise variable profile(Aerodynamic lift, drag and momentum coefficients in supersonic regime for rectangular and trapezoidal wings with spanwise variable profile)
Holla et al. Evaluation of lift and drag of a family of conically cambered wings at off design Mach numbers(Lift and drag at off-design Mach numbers of conically cambered wings with subsonic leading edges and supersonic trailing edge)
Hicks et al. Effects of spanwise variation of leading-edge sweep on the lift, drag, and pitching moment of a wing-body combination at mach numbers 0. 7 to 2. 94(Effects of spanwise variation of leading edge sweep on lift, drag, & pitching moment of wing- body combination at transonic speeds)
GB1395150A (en) Aircraft
GB1035898A (en) Aircraft with lift jet engines
SPENCER Canard aircraft with split flaps ahead of the wing trailing edge and flaps on the leading and trailing edges of the canard control at low speed
TANNER Influence of the trailing edge shape on the drag of a rectangular wing in the Mach number range from MA= 0. 5 to 2. 2(Influence of trailing edge thickness on aerodynamic drag of rectangular wings in transonic and supersonic flow)