RCAIDE.Library.Components.Airfoils.NACA_4_Series_Airfoil

NACA_4_Series_Airfoil#

class NACA_4_Series_Airfoil(*args, **kwarg)[source]#

Bases: Airfoil

Class for generating NACA 4-series airfoil geometries.

tag#

Identifier for the airfoil (default: ‘NACA_4_Series’)

Type:

str

NACA_4_Series_code#

Four-digit NACA designation (default: ‘0012’)

Type:

str

Notes

Inherits all attributes from the base Airfoil class. The geometry is generated based on the NACA 4-series equations using the specified four-digit code.

The NACA 4-series airfoils are defined by four digits that specify the camber, position of maximum camber, and thickness. For example, in a NACA 2412: - First digit (2) specifies maximum camber in percentage of chord - Second digit (4) specifies position of maximum camber in tenths of chord - Last two digits (12) specify maximum thickness in percentage of chord

‘NACA Code Format’

MPXX where: - M is the maximum camber in percentage of chord - P is the position of maximum camber in tenths of chord - XX is the maximum thickness in percentage of chord

See also

RCAIDE.Library.Components.Airfoils.Airfoil

Base airfoil class