NACA airfoil: Unterschied zwischen den Versionen

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https://en.wikipedia.org/wiki/NACA_airfoil
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[[File:Airfoil geometry.svg|thumb|350px|Profile geometry – 1: Zero lift line; 2: Leading edge; 3: Nose circle; 4: Max. thickness; 5: Camber; 6: Upper surface; 7: Trailing edge; 8: Camber mean-line; 9: Lower surface]]
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'''Summary:''' The NACA airfoils are airfoil shapes for aircraft wings developed by the '''N'''ational '''A'''dvisory '''C'''ommittee for '''A'''eronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word “NACA”. The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties.
  
[[Category: -OSEG 400 - Bereich Technologie]]
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Continue reading at https://en.wikipedia.org/wiki/NACA_airfoil
[[Category: -OSEG 401 - Windenergie]]
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[[Category:OSEG - Bereich Technologie]]
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[[Category:OSEG - Windenergie]]
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[[Kategorie:English pages]]

Aktuelle Version vom 1. Juni 2018, 19:41 Uhr

Profile geometry – 1: Zero lift line; 2: Leading edge; 3: Nose circle; 4: Max. thickness; 5: Camber; 6: Upper surface; 7: Trailing edge; 8: Camber mean-line; 9: Lower surface

Summary: The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word “NACA”. The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties.

Continue reading at https://en.wikipedia.org/wiki/NACA_airfoil