GB615318A - Improvements in or relating to low drag airfoils - Google Patents

Improvements in or relating to low drag airfoils

Info

Publication number
GB615318A
GB615318A GB25801/45A GB2580145A GB615318A GB 615318 A GB615318 A GB 615318A GB 25801/45 A GB25801/45 A GB 25801/45A GB 2580145 A GB2580145 A GB 2580145A GB 615318 A GB615318 A GB 615318A
Authority
GB
United Kingdom
Prior art keywords
cos
aerofoil
equations
sin
profile
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
GB25801/45A
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.)
Glenn L Martin Co
Original Assignee
Glenn L Martin Co
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 Glenn L Martin Co filed Critical Glenn L Martin Co
Publication of GB615318A publication Critical patent/GB615318A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/467—Aerodynamic features

Abstract

615,318. Aerofoils. MARTIN CO., G. L. Oct. 4, 1945, No. 25801. Convention date, June 7, 1944. Drawings to Specification. [Class 4] The Specification gives the mathematical analysis necessary to determine the aerofoil profile required for an aircraft of specified performance characteristics, The required pressure distribution is determined and from this is obtained the required velocity distribution over the aerofoil and the angle of attack for optimum lift coefficient. The values of certain parameters necessary for solving the following equations for the rectangular coordinates of the profile are then calculated. X=2 cosh # cos # Y=2 sinh # cos # In these equations # varies from #/16-1.94 # and # is expressed as a series in cos #-cos 12 0 and sin #-sin 12 #. Various equations for # are given in the description and claims. The nose portion of the aerofoil is completed by a smooth, faired curve having a radius of curvature equal to 2.298 per cent chord.
GB25801/45A 1944-06-07 1945-10-04 Improvements in or relating to low drag airfoils Expired GB615318A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US615318XA 1944-06-07 1944-06-07

Publications (1)

Publication Number Publication Date
GB615318A true GB615318A (en) 1949-01-05

Family

ID=22036365

Family Applications (1)

Application Number Title Priority Date Filing Date
GB25801/45A Expired GB615318A (en) 1944-06-07 1945-10-04 Improvements in or relating to low drag airfoils

Country Status (1)

Country Link
GB (1) GB615318A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2408518A1 (en) * 1977-11-11 1979-06-08 United Technologies Corp ADVANCED HELICOPTER BLADE
FR2463054A1 (en) * 1979-08-10 1981-02-20 Aerospatiale BLADE PROFILE FOR AN AIRCRAFT TURNING SAIL
EP0024229A2 (en) * 1979-08-10 1981-02-25 AEROSPATIALE Société Nationale Industrielle Blade profile for rotary-wing aircraft
EP0048649A1 (en) * 1980-09-24 1982-03-31 Aerospatiale Societe Nationale Industrielle Rotor blade airfoil for a helicopter
EP1371550A1 (en) * 2002-06-12 2003-12-17 Honda Giken Kogyo Kabushiki Kaisha Trailing edge shape of laminar-flow airfoil
CN109878721A (en) * 2019-04-04 2019-06-14 中南大学 A kind of design method and product of microminiature rotor unmanned aircraft rotor-blade airfoil
CN112948966A (en) * 2021-02-03 2021-06-11 西北工业大学 Automatic detection method for wing section resistance integral area
CN113479060A (en) * 2021-07-28 2021-10-08 深圳市人工智能与机器人研究院 Control method for automatic driving of light unmanned wing sail vehicle

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2408518A1 (en) * 1977-11-11 1979-06-08 United Technologies Corp ADVANCED HELICOPTER BLADE
FR2463054A1 (en) * 1979-08-10 1981-02-20 Aerospatiale BLADE PROFILE FOR AN AIRCRAFT TURNING SAIL
EP0024229A2 (en) * 1979-08-10 1981-02-25 AEROSPATIALE Société Nationale Industrielle Blade profile for rotary-wing aircraft
EP0024229A3 (en) * 1979-08-10 1981-04-29 Societe Nationale Industrielle Aerospatiale Societe Anonyme Dite: Blade profile for rotary-wing aircraft
EP0048649A1 (en) * 1980-09-24 1982-03-31 Aerospatiale Societe Nationale Industrielle Rotor blade airfoil for a helicopter
EP1371550A1 (en) * 2002-06-12 2003-12-17 Honda Giken Kogyo Kabushiki Kaisha Trailing edge shape of laminar-flow airfoil
US7093792B2 (en) 2002-06-12 2006-08-22 Honda Giken Kogyo Kabushiki Kaisha Laminar-flow airfoil
CN109878721A (en) * 2019-04-04 2019-06-14 中南大学 A kind of design method and product of microminiature rotor unmanned aircraft rotor-blade airfoil
CN109878721B (en) * 2019-04-04 2023-11-21 中南大学 Design method and product of rotor wing profile of micro rotor unmanned aerial vehicle
CN112948966A (en) * 2021-02-03 2021-06-11 西北工业大学 Automatic detection method for wing section resistance integral area
CN112948966B (en) * 2021-02-03 2023-02-14 西北工业大学 Automatic detection method for wing section resistance integral area
CN113479060A (en) * 2021-07-28 2021-10-08 深圳市人工智能与机器人研究院 Control method for automatic driving of light unmanned wing sail vehicle

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