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 ESDU
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 A.00.02
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ESDU FAT A.00.02 58th Edition, April 1, 1973
The effect of mean stress on fatigue strength (test piece with stress concentration).
Includes all amendments and changes through AA, April 1, 1973

ESDU FAT A.00.02

58th Edition, April 1, 1973

Complete Document
 
The effect of mean stress on fatigue strength (test piece with stress concentration).
Includes all amendments and changes through AA, April 1, 1973
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ESDU FAT A.00.01 58th Edition, February 1, 1975
The effect of mean stress on fatigue strength (plain test piece).
Includes all amendments and changes through AA, February 1, 1975

ESDU FAT A.00.01

58th Edition, February 1, 1975

Complete Document
 
The effect of mean stress on fatigue strength (plain test piece).
Includes all amendments and changes through AA, February 1, 1975
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ESDU FAT A.05.02 65th Edition, April 1, 1973
Estimation of endurance of pin joints.
Includes all amendments and changes through AB, April 1, 1973

ESDU FAT A.05.02

65th Edition, April 1, 1973

Complete Document
 
Estimation of endurance of pin joints.
Includes all amendments and changes through AB, April 1, 1973
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ESDU AERO 00.02.05 62nd Edition, February 1, 1981
Heat transfer under conditions of forced convection for the subsonic turbulent flow of gases in smooth straight ducts of constant cross section.
Includes all amendments and changes through AA, February 1, 1981

ESDU AERO 00.02.05

62nd Edition, February 1, 1981

Complete Document
 
Heat transfer under conditions of forced convection for the subsonic turbulent flow of gases in smooth straight ducts of constant cross section.
Includes all amendments and changes through AA, February 1, 1981
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ESDU FAT E.07.02 1965 Edition, April 1, 1965
Notes supplementary to E.07.01 on the fatigue strength of aluminium alloys.

ESDU FAT E.07.02

1965 Edition, April 1, 1965

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Notes supplementary to E.07.01 on the fatigue strength of aluminium alloys.
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ESDU AERO A.02.03.02 59th Edition, December 1, 1982
Optimum area distribution and associated theoretical transonic drag-rise for aircraft at zero lift.
Includes all amendments and changes through AA, December 1, 1982

ESDU AERO A.02.03.02

59th Edition, December 1, 1982

Complete Document
 
Optimum area distribution and associated theoretical transonic drag-rise for aircraft at zero lift.
Includes all amendments and changes through AA, December 1, 1982
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ESDU STRUCT 02.00.00 62nd Edition, April 1, 1969
Criteria of yielding and failure.
Includes all amendments and changes through AA, April 1, 1969

ESDU STRUCT 02.00.00

62nd Edition, April 1, 1969

Complete Document
 
Criteria of yielding and failure.
Includes all amendments and changes through AA, April 1, 1969
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ESDU STRUCT 02.05.00 48th Edition, February 1, 1983
Diffusion of loads into flat uniform panels.
Includes all amendments and changes through AA, February 1, 1983

ESDU STRUCT 02.05.00

48th Edition, February 1, 1983

Complete Document
 
Diffusion of loads into flat uniform panels.
Includes all amendments and changes through AA, February 1, 1983
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ESDU AERO W.02.04.00 52nd Edition, January 1, 1994
Information on the use of Data Items in the series Wings 02.04.
Includes all amendments and changes through AB, January 1, 1994

ESDU AERO W.02.04.00

52nd Edition, January 1, 1994

Complete Document
 
Information on the use of Data Items in the series Wings 02.04.
Includes all amendments and changes through AB, January 1, 1994
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ESDU AERO A.07.01.00 46th Edition, January 1, 2015
Information on the use of Data Items on yawing moment and sideforce derivatives of an aircraft
Includes all amendments and changes through AI, January 1, 2015

ESDU AERO A.07.01.00

46th Edition, January 1, 2015

Complete Document
 
Information on the use of Data Items on yawing moment and sideforce derivatives of an aircraft
Includes all amendments and changes through AI, January 1, 2015
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ESDU AERO A.06.01.00 58th Edition, January 1, 2015
Information on the use of Data Items on rolling moment derivatives of an aircraft
Includes all amendments and changes through AK, January 1, 2015

ESDU AERO A.06.01.00

58th Edition, January 1, 2015

Complete Document
 
Information on the use of Data Items on rolling moment derivatives of an aircraft
Includes all amendments and changes through AK, January 1, 2015
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ESDU STRUCT 00.06.00 46th Edition, December 1, 1980
Information on the use of Data Items in the Struct 00.06. series.
Includes all amendments and changes through AA, December 1, 1980

ESDU STRUCT 00.06.00

46th Edition, December 1, 1980

Complete Document
 
Information on the use of Data Items in the Struct 00.06. series.
Includes all amendments and changes through AA, December 1, 1980
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ESDU STRUCT 00.07.00 47th Edition, January 1, 1983
Information on the use of Data Sheets in the 00.07 series.
Includes all amendments and changes through AA, January 1, 1983

ESDU STRUCT 00.07.00

47th Edition, January 1, 1983

Complete Document
 
Information on the use of Data Sheets in the 00.07 series.
Includes all amendments and changes through AA, January 1, 1983
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ESDU AERO 00.01.12 62nd Edition, May 1, 1982
Mollier chart of the thermodynamic properties of argon-free air in dissociation equilibrium: T = 100 K to T = 6 000 K.
Includes all amendments and changes through AA, May 1, 1982

ESDU AERO 00.01.12

62nd Edition, May 1, 1982

Complete Document
 
Mollier chart of the thermodynamic properties of argon-free air in dissociation equilibrium: T = 100 K to T = 6 000 K.
Includes all amendments and changes through AA, May 1, 1982
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ESDU STRUCT 01.00.01 43rd Edition, April 1, 1980
Flexural properties of stringer sections (lipped and unlipped angles, channels and Z-sections).
Includes all amendments and changes through AA, April 1, 1980

ESDU STRUCT 01.00.01

43rd Edition, April 1, 1980

Complete Document
 
Flexural properties of stringer sections (lipped and unlipped angles, channels and Z-sections).
Includes all amendments and changes through AA, April 1, 1980
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ESDU AERO 00.01.11 62nd Edition, May 1, 1982
Mollier chart of the thermodynamic properties of argon-free air in dissociation equilibrium: T = 2 000 K to T = 13 000 K.
Includes all amendments and changes through AA, May 1, 1982

ESDU AERO 00.01.11

62nd Edition, May 1, 1982

Complete Document
 
Mollier chart of the thermodynamic properties of argon-free air in dissociation equilibrium: T = 2 000 K to T = 13 000 K.
Includes all amendments and changes through AA, May 1, 1982
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ESDU AERO 00.03.28 63rd Edition, February 1, 1978
Conditions behind normal shock waves in a perfect gas for various values of gamma.
Includes all amendments and changes through AA, February 1, 1978

ESDU AERO 00.03.28

63rd Edition, February 1, 1978

Complete Document
 
Conditions behind normal shock waves in a perfect gas for various values of gamma.
Includes all amendments and changes through AA, February 1, 1978
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ESDU AERO 00.03.26 62nd Edition, April 1, 1973
Wall and average gas temperatures for subsonic turbulent flow with heat transfer in ducts of constant circular cross section.
Includes all amendments and changes through AA, April 1, 1973

ESDU AERO 00.03.26

62nd Edition, April 1, 1973

Complete Document
 
Wall and average gas temperatures for subsonic turbulent flow with heat transfer in ducts of constant circular cross section.
Includes all amendments and changes through AA, April 1, 1973
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ESDU AERO 00.03.30 65th Edition, January 1, 1999
Solutions to the oblique shock wave relations for a range of specific heat ratios: pressure coefficient and detachment angle.
Includes all amendments and changes through AA, January 1, 1999

ESDU AERO 00.03.30

65th Edition, January 1, 1999

Complete Document
 
Solutions to the oblique shock wave relations for a range of specific heat ratios: pressure coefficient and detachment angle.
Includes all amendments and changes through AA, January 1, 1999
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ESDU AERO 00.03.31 1965 Edition, August 1, 1965
Solutions to the Prandtl-Meyer expansion relations for a range of specific heat ratios: pressure coefficient and maximum flow deflection angle.

ESDU AERO 00.03.31

1965 Edition, August 1, 1965

Complete Document
 
Solutions to the Prandtl-Meyer expansion relations for a range of specific heat ratios: pressure coefficient and maximum flow deflection angle.
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