airfoils package¶
Submodules¶
airfoils.airfoils module¶
Provides tools to create and modify airfoil objects
Developed for Airinnova AB, Stockholm, Sweden.
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class
airfoils.airfoils.Airfoil(upper, lower)¶ Bases:
object-
classmethod
NACA4(naca_digits, n_points=200)¶ Create an airfoil object from a NACA 4-digit series definition
- Note:
This is an alternative constructor method
- Args:
- naca_digits
String like ‘4412’
- points
Total number of points used to create the airfoil
- Returns:
- airfoil
New airfoil instance
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property
all_points¶ Returns a single 2 x N array with x and y-coordinates in separate columns
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camber_line(x)¶ Compute the camber line
Method 1: y_camber = (y_upper + y_lower)/2
- Args:
- x
Relative chordwise coordinate ranging from 0 to 1
- Returns:
- camber_line
y-coordinates at given x positions
-
camber_line_angle(x)¶ Compute the camber line angle
- Args:
- x
Relative chordwise coordinate ranging from 0 to 1
- Returns:
- theta
Camber line angle at given x positions
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classmethod
morph_new_from_two_foils(airfoil1, airfoil2, eta, n_points)¶ Create an airfoil object from a linear interpolation between two airfoil objects
- Note:
This is an alternative constructor method
- Args:
- airfoil1
Airfoil object at eta = 0
- airfoil2
Airfoil object at eta = 1
- eta
Relative position where eta = [0, 1]
- n_points
Number of points for new airfoil object
- Returns:
- airfoil
New airfoil instance
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plot(*, show=True, save=False, settings={})¶ Plot the airfoil and camber line
- Note:
‘show’ and/or ‘save’ must be True
- Args:
- show
(bool) Create an interactive plot
- save
(bool) Save plot to file
- settings
(bool) Plot settings
- Plot settings:
Plot settings must be a dictionary
Allowed keys:
‘points’: (bool) ==> Plot coordinate points ‘camber’: (bool) ==> Plot camber ‘chord’: (bool) ==> Plot chord ‘path’: (str) ==> Output path (directory path, must exists) ‘file_name’: (str) ==> Full file name
- Returns:
None or ‘file_name’ (full path) if ‘save’ is True
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y_lower(x)¶
-
y_upper(x)¶
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classmethod
-
class
airfoils.airfoils.MorphAirfoil(airfoil1, airfoil2, n_points=200)¶ Bases:
object-
at_eta(eta)¶ Returns a new airfoil object at a given eta position
- Args:
- eta
(float) eta position where eta = [0, 1]
- Returns:
- morphed_airfoil
(obj) interpolated airfoil object at the given eta position
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exception
airfoils.airfoils.NACADefintionError¶ Bases:
ExceptionRaised when the NACA identifier number is not valid
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airfoils.airfoils.gen_NACA4_airfoil(p, m, xx, n_points)¶ Generate upper and lower points for a NACA 4 airfoil
- Args:
- p
- m
- xx
- n_points
- Returns:
- upper
2 x N array with x- and y-coordinates of the upper side
- lower
2 x N array with x- and y-coordinates of the lower side
airfoils.fileio module¶
Import airfoil data from a text file
Developed for Airinnova AB, Stockholm, Sweden.
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exception
airfoils.fileio.FileInputFormatError¶ Bases:
ExceptionRaised if file input data is not formatted correctly
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airfoils.fileio.import_airfoil_data(file_name)¶ Import airfoil data from a text file
- Args:
- file_name
File name (string)
- Returns:
- upper
Upper airfoil coordinates
- lower
Lower airfoil coordinates