Source code for RCAIDE.Library.Components.Airfoils.NACA_4_Series_Airfoil
# RCAIDE/Library/Compoments/Airfoils/NACA_4_Series_Airfoil.py
#
#
# Created: Mar 2024, M. Clarke
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# IMPORT
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# RCAIDE imports
from .Airfoil import Airfoil
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# Airfoil
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[docs]
class NACA_4_Series_Airfoil(Airfoil):
"""
Class for generating NACA 4-series airfoil geometries.
Attributes
----------
tag : str
Identifier for the airfoil (default: 'NACA_4_Series')
NACA_4_Series_code : str
Four-digit NACA designation (default: '0012')
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
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
None
"""
self.tag = 'NACA_4_Series'
self.NACA_4_Series_code = '0012'
return
