GB1470718A - Vehicle provided with a drag reducing low nose wing - Google Patents

Vehicle provided with a drag reducing low nose wing

Info

Publication number
GB1470718A
GB1470718A GB1896974A GB1896974A GB1470718A GB 1470718 A GB1470718 A GB 1470718A GB 1896974 A GB1896974 A GB 1896974A GB 1896974 A GB1896974 A GB 1896974A GB 1470718 A GB1470718 A GB 1470718A
Authority
GB
United Kingdom
Prior art keywords
wing
larson
canard
main wing
flow
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
GB1896974A
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
Publication of GB1470718A publication Critical patent/GB1470718A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C17/00—Aircraft stabilisation not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/12—Canard-type aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • 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
    • Y02T50/30—Wing lift efficiency

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)

Abstract

1470718 Canard wing aircraft; reducing drag S E LARSON I H LARSON C I K LARSON B E H LARSON J E G LARSON L O A LARSON and G P G LARSON 30 April 1974 [4 May 1973] 18969/74 Headings B7W and B7M A vehicle for operation in air or water has a main wing 3 and a canard wing 4 located upstream of and below the level of the main wing, the canard wing having such camber and location relative to the main wing that during a main wing angle of attack increase in a vehicle pitching manoeuvre the canard wing flow effects, by interference with the flow round the main wing, a stabilization and linearization of the flow over at least the leading edge of the main wing, whereby flow separation at the main wing leading edge is suppressed and retarded and a flow of essentially potential flow character is maintained at the main wing up to high angles of attack whereby a flow drag reduction and smoothing of the vehicle pitching moment curve is achieved. Test results are described supported by CL/CD curves (Fig. 6, not shown), for a diagrammatically represented model provided with leading and trailing edge flaps (Figs. 7a, 7b, not shown), and an optimum region for positioning the canard wing forward and below the main wing is illustrated in Figs. 8 and 9, wherein the leading point 31 and trailing point 41 of the aerodynamic mean chord 30 and 40 of the main and canard wings respectively are projected on to the centre axis 32 at points 33 and 42, the point 33 being selected as origin for an orthogonal co-ordinate system (X, Z). The shaded area within which the canard or nose wing should be positioned to achieve optimum drag reduction is bounded by line a defined by the points 33 and 51 having the X-Z co-ordinates (0; 0) and (0; 0À25 # NW ) where # NW is the length of the symmetry chord of the nose wing; line b defined by the points 33 and 52 having the X-Z co-ordinates (0; 0) and (2 # NW ; 0À1 C NW ) respectively, and line c defined by points 51 and 53 having the X-Z co-ordinates (0; 0À25 C NW and 2 # NW ; # NW ) respectively. A wing placed in this area is stated to obviate the need for leading edge slats on the main wing.
GB1896974A 1973-05-04 1974-04-30 Vehicle provided with a drag reducing low nose wing Expired GB1470718A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE7306302A SE381016B (en) 1973-05-04 1973-05-04 INCLUDES GEOMETRIC LOCATION OF NOS WING AND MAIN WING AT AIRCRAFT OR OTHER VEHICLE

Publications (1)

Publication Number Publication Date
GB1470718A true GB1470718A (en) 1977-04-21

Family

ID=20317371

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1896974A Expired GB1470718A (en) 1973-05-04 1974-04-30 Vehicle provided with a drag reducing low nose wing

Country Status (7)

Country Link
JP (1) JPS5030299A (en)
CA (1) CA1005041A (en)
DE (1) DE2421524A1 (en)
FR (1) FR2227991B1 (en)
GB (1) GB1470718A (en)
NL (1) NL7405987A (en)
SE (1) SE381016B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1323900C (en) * 2003-08-22 2007-07-04 中国计量学院 Hydrofoil diving military miniature speedboat and using method thereof
CN101595027A (en) * 2007-02-20 2009-12-02 李希成 Series connection/canard ground effect vehicle with suspension system
CN113562160A (en) * 2021-08-07 2021-10-29 中国航空工业集团公司沈阳飞机设计研究所 Front wing application method for improving pitching moment characteristic of airplane

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS49134732U (en) * 1973-03-20 1974-11-20
IT1235222B (en) * 1982-11-26 1992-06-26 Secratary Of State For Defence IMPROVEMENT IN MISSILE AND SIMILAR FUSELETS
BR8601586A (en) * 1985-04-09 1986-12-30 Dei Tech Inc SUPER AGIL TACTICAL CACA AVIATION AND PILOT PROCESS
USRE35387E (en) * 1985-04-09 1996-12-03 Dynamic Engineering, Inc. Superfragile tactical fighter aircraft and method of flying it in supernormal flight
DE4337850A1 (en) * 1993-11-05 1995-05-18 Fritz Hausser Rudder, aileron and elevator for front of aircraft
US5901925A (en) * 1996-08-28 1999-05-11 Administrator, National Aeronautics And Space Administration Serrated-planform lifting-surfaces

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1323900C (en) * 2003-08-22 2007-07-04 中国计量学院 Hydrofoil diving military miniature speedboat and using method thereof
CN101595027A (en) * 2007-02-20 2009-12-02 李希成 Series connection/canard ground effect vehicle with suspension system
CN113562160A (en) * 2021-08-07 2021-10-29 中国航空工业集团公司沈阳飞机设计研究所 Front wing application method for improving pitching moment characteristic of airplane
CN113562160B (en) * 2021-08-07 2024-01-02 中国航空工业集团公司沈阳飞机设计研究所 Front wing application method for improving pitching moment characteristics of airplane

Also Published As

Publication number Publication date
FR2227991A1 (en) 1974-11-29
NL7405987A (en) 1974-11-06
SE381016B (en) 1975-11-24
CA1005041A (en) 1977-02-08
JPS5030299A (en) 1975-03-26
DE2421524A1 (en) 1974-11-21
FR2227991B1 (en) 1980-04-11

Similar Documents

Publication Publication Date Title
US3411738A (en) Airfoil tip
CN108639339B (en) Pneumatic layout of unmanned aerial vehicle
US3188022A (en) Delta wing canard aircraft
US4050397A (en) Foil fence for hydrofoil craft
US4176813A (en) Shark nose for aircraft
GB1470718A (en) Vehicle provided with a drag reducing low nose wing
Kalman et al. Spanwise distribution of induced drag in subsonic flow by the vortexlattice method
Rinoie et al. Experimental studies of vortex flaps and vortex plates
Newsom Jr et al. Effects of wing-leading-edge modifications on a full-scale, low-wing general aviation airplane: Wind-tunnel investigation of high-angle-of-attack aerodynamic characteristics
US2496565A (en) Tailless aircraft with stabilizing wing
Wimpress Upper surface blowing technology as applied to the YC-14 airplane
US2920842A (en) Aircraft configuration
US3871602A (en) Circular wing aircraft
Spearman Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations
US2608365A (en) Aircraft control surface
JPH0478793A (en) Aircraft
GB1508389A (en) Aerodynamic lift enhancing apparatus
EP0120009B1 (en) Shock inducing pod for causing flow separation
Sleeman Jr Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations
JPH06312697A (en) Resistance reducing vertical rudder
Runckel et al. The Aerodynamic Characteristics at Transonic Speeds of a Model with a 45 Degree Sweptback Wing, Including the Effect of Leading Edge Slats and a Low Horizontal Tail
Lopez et al. A theoretical method for calculating the aerodynamic characteristics of arbitary jet-flapped wings. Volume 1: The elementary vortex distribution jet-wing lifting surface theory[Final Technical Report]
US2385499A (en) Fuselage bulge
Scallion Low Speed Static Longitudinal and Lateral Aerodynamic Characteristics of a Model with a Low-aspect-ratio Variable-incidence Wing and with a Free-floating and a Programed High-lift Canard Control
ROTHBLUM et al. Methods for controlling the sideforce on surface-piercing hydrofoil struts[Final Report]

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee