## @ingroup Library-Plots-Performance-Aerodynamics
# RCAIDE/Library/Plots/Performance/Aerodynamics/plot_airfoil_polar_files.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
from RCAIDE.Framework.Core import Units
from RCAIDE.Library.Plots.Common import set_axes, plot_style,segment_colors
import matplotlib.pyplot as plt
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# PLOTS
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def plot_airfoil_polar_files(polar_data,
save_figure = False,
show_legend = True,
save_filename = "Airfoil_Polars",
file_type = ".png",
width = 11, height = 7):
"""
Generate plots of airfoil performance data from polar files.
Parameters
----------
polar_data : Data
Airfoil polar data structure containing:
- lift_coefficients : array
CL values for each Reynolds number and angle of attack
- drag_coefficients : array
CD values for each Reynolds number and angle of attack
- angle_of_attacks : array
Angles of attack [rad]
- reynolds_numbers : array
Reynolds numbers
- re_from_polar : array
List of Reynolds numbers from polar files
save_figure : bool, optional
Save figure to file if True, default False
save_filename : str, optional
Name for saved figure file, default "Airfoil_Polars"
file_type : str, optional
File extension for saved figure, default ".png"
width : float, optional
Figure width in inches, default 11
height : float, optional
Figure height in inches, default 7
Returns
-------
fig : matplotlib.figure.Figure
Notes
-----
Creates a 2x2 subplot figure showing airfoil performance:
- Top left: Lift coefficient vs angle of attack
- Top right: Drag coefficient vs angle of attack
- Bottom left: Drag polar (CL vs CD)
- Bottom right: Lift-to-drag ratio vs angle of attack
Each Reynolds number case is plotted in a different color using
the inferno colormap. Legend entries show Reynolds numbers in
scientific notation (e.g., "Re=1.0e6").
See Also
--------
RCAIDE.Library.Plots.Common.set_axes : Standardized axis formatting
RCAIDE.Library.Plots.Common.plot_style : RCAIDE plot styling
RCAIDE.Library.Analysis.Aerodynamics.process_airfoil_polars : Analysis module
"""
# get plotting style
ps = plot_style()
parameters = {'axes.labelsize': ps.axis_font_size,
'xtick.labelsize': ps.axis_font_size,
'ytick.labelsize': ps.axis_font_size,
'axes.titlesize': ps.title_font_size}
plt.rcParams.update(parameters)
# Get raw data polars
CL = polar_data.lift_coefficients
CD = polar_data.drag_coefficients
alpha = polar_data.angle_of_attacks/Units.degrees
Re_raw = polar_data.reynolds_numbers
n_Re = len(polar_data.re_from_polar)
# get line colors for plots
line_colors = segment_colors(n_Re)
fig = plt.figure(save_filename)
fig.set_size_inches(width,height)
for j in range(n_Re):
Re_val = str(round(Re_raw[j])/1e6)+' x $10^6$'
axis_1 = plt.subplot(2,2,1)
axis_1.plot(alpha, CL[j,:], color = line_colors[j], marker = ps.markers[0], linewidth = ps.line_width, label ='Re = '+Re_val)
axis_1.set_ylabel(r'$C_l$')
axis_1.set_xlabel(r'$\alpha$')
set_axes(axis_1)
axis_2 = plt.subplot(2,2,2)
axis_2.plot(alpha,CD[j,:], color = line_colors[j], marker = ps.markers[0], linewidth = ps.line_width)
axis_2.set_ylabel(r'$C_d$')
axis_2.set_xlabel(r'$\alpha$')
set_axes(axis_2)
axis_3 = plt.subplot(2,2,3)
axis_3.plot(CD[j,:],CL[j,:], color = line_colors[j], marker = ps.markers[0], linewidth = ps.line_width)
axis_3.set_xlabel('$C_d$')
axis_3.set_ylabel(r'$C_l$')
set_axes(axis_3)
axis_4 = plt.subplot(2,2,4)
axis_4.plot(alpha, CL[j,:]/CD[j,:], color = line_colors[j], marker = ps.markers[0], linewidth = ps.line_width)
axis_4.set_ylabel(r'$Cl/Cd$')
axis_4.set_xlabel(r'$\alpha$')
set_axes(axis_4)
if show_legend:
leg = fig.legend(bbox_to_anchor=(0.5, 0.95), loc='upper center', ncol = 4)
leg.set_title('Airfoil Polars', prop={'size': ps.legend_font_size, 'weight': 'heavy'})
# Adjusting the sub-plots for legend
fig.tight_layout()
fig.subplots_adjust(top=0.8)
if save_figure:
plt.savefig(save_filename + file_type)
return fig
