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