GB1290924A - - Google Patents

Info

Publication number
GB1290924A
GB1290924A GB1290924DA GB1290924A GB 1290924 A GB1290924 A GB 1290924A GB 1290924D A GB1290924D A GB 1290924DA GB 1290924 A GB1290924 A GB 1290924A
Authority
GB
United Kingdom
Prior art keywords
blade
lift
providing
attack
sections
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
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 filed Critical
Publication of GB1290924A publication Critical patent/GB1290924A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Toys (AREA)

Abstract

1290924 Helicopter rotors VEREINIGTE FLUGTECHNISCHE WERKE - FOKKER GmbH 13 May 1970 [13 May 1969] 23241/70 Heading B7W In a helicopter for flying at high speeds, each blade of the rotor has an inner portion 15 providing positive lift and an outer ponton 16 providing negative lift when the blade is advancing, but both sections providing no lift when the blade is retreating, due to cyclic control of the effective angle of attack of each section of the blade, an exemplary lift profile being shown in Fig. 2. The effective angle of attack is changed by control or jet flaps 17, 18 provided respectively on the inner and outer blade sections 15, 16 of each blade.
GB1290924D 1969-05-13 1970-05-13 Expired GB1290924A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19691924299 DE1924299A1 (en) 1969-05-13 1969-05-13 Helicopter for high flight speeds

Publications (1)

Publication Number Publication Date
GB1290924A true GB1290924A (en) 1972-09-27

Family

ID=5734037

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1290924D Expired GB1290924A (en) 1969-05-13 1970-05-13

Country Status (3)

Country Link
DE (1) DE1924299A1 (en)
FR (1) FR2042601B3 (en)
GB (1) GB1290924A (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5328330A (en) * 1993-08-02 1994-07-12 Hudson Products Corporation Extruded aluminum fan blade

Also Published As

Publication number Publication date
FR2042601A7 (en) 1971-02-12
DE1924299A1 (en) 1971-02-04
FR2042601B3 (en) 1973-03-16

Similar Documents

Publication Publication Date Title
CA961826A (en) Composite aerodynamic blade with twin-beam spar
GB1331025A (en) Helicopter rotor blades
ES8102955A1 (en) Rotor blade pitch control for helicopter with coaxial rotors.
GB1202216A (en) Improvements in or relating to propeller assemblies
GB1485683A (en) Helicopter rotor blade
GB1290924A (en)
GB1526433A (en) Helicopter rotor blades
GB1174955A (en) Rotatable Aerofoil Assembly
GB1346563A (en) Rotary wing overload protection
GB1514347A (en) Helicopter rotors
GB1297723A (en)
GB987792A (en) Improvements in and relating to aircraft wings
GB964360A (en) Helicopter
GB1124929A (en) A folding multi-blade airscrew
GB1261024A (en) Method and means for minimizing the actuating forces of a controllable pitch propeller
GB755629A (en) Improvements relating to single-rotor helicopters
DELEST Presentation of a method for calculating lift distribution at fixed points along a helicopter rotor blade
GB614621A (en) Improvements in and relating to rotative aerofoils with propulsive ducts
JONES Unsteady aerodynamics of helicopter rotors(Developments in unsteady aerodynamics of helicopter rotary wings to analyze stall flutter, transient effects of interactions, and wake induced instabilities)
GB1041116A (en) Helicopter
BERMAN A new approach to the solution of rotor blade dynamic problems(Matrix solution of simultaneous linear differential equations describing dynamics of two degree-of-freedom helicopter rotor blades)
TIRUMALESA Pressure distribution over circular arc airfoils at transonic speed examined through application of the shock boundary layer interaction theory
FETTERMAN et al. Control-surface interaction effects on delta- wing windward pressures at a mach number of 6. 83 at high angles of attack(Control surface interaction effects on delta wing windward pressures at hypersonic speeds and high angles of attack)
WILLIAMS Recent developments in circulation control rotor technology(Development of concept of circulation control applied to rotary wings to show effects on hover, transition, and high speed cruise performance)
BUTLER et al. Analysis of boundary layer controls for high lift at low speeds along trailing-edge flaps, and the design features required for optimum performance

Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees