NACA airfoil: Unterschied zwischen den Versionen
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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]] | |
| + | '''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: | + | Continue reading at https://en.wikipedia.org/wiki/NACA_airfoil |
| − | [[Category: | + | |
| + | [[Category:OSEG - Bereich Technologie]] | ||
| + | [[Category:OSEG - Windenergie]] | ||
| + | [[Kategorie:English pages]] | ||
Aktuelle Version vom 1. Juni 2018, 19:41 Uhr
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