RCAIDE.Library.Components.Airfoils.Airfoil

Airfoil

class Airfoil(*args, **kwarg)

Bases: Component

Base class for defining airfoil geometries and their aerodynamic characteristics

tag

Identifier for the airfoil (default: ‘Airfoil’)

Type:

str

coordinate_file

Path to file containing airfoil coordinates (default: None)

Type:

str, optional

geometry

Array containing x,y coordinates defining the airfoil shape (default: None)

Type:

array_like, optional

polar_files

Paths to files containing aerodynamic polar data (default: None)

Type:

list of str, optional

polars

Dictionary containing aerodynamic coefficient data (default: None)

Type:

dict, optional

prev

Reference to previous airfoil in a wing (default: None)

Type:

Airfoil, optional

next

Reference to next airfoil in a wing (default: None)

Type:

Airfoil, optional

number_of_points

Number of points used to discretize the airfoil geometry (default: 201)

Type:

int

Notes

The Airfoil class serves as a base class for more specific airfoil implementations. It provides basic structure for storing geometry and aerodynamic data, which can be loaded from files or generated programmatically.

Definitions

‘Polar Data’

Aerodynamic coefficient data (typically cl, cd, cm) as a function of angle of attack

See also

RCAIDE.Library.Components.Airfoils.NACA_4_Series_Airfoil

Implementation for NACA 4-series airfoils

append_operating_conditions(segment, energy_conditions)

Placeholder for adding operating conditions to the airfoil.

Parameters:

• segment (Data) – Flight segment data

• propulsor (Data) – Propulsion system data