# RCAIDE/Library/Plots/Performance/Aerodynamics/plot_airfoil_polars.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
from RCAIDE.Framework.Core import Units
from RCAIDE.Library.Plots.Common import set_axes, plot_style
import matplotlib.pyplot as plt
# ----------------------------------------------------------------------------------------------------------------------
# PLOTS
# ----------------------------------------------------------------------------------------------------------------------
## @ingroup Library-Plots-Performance-Aerodynamics
[docs]
def plot_airfoil_polars(polar_data,
save_figure = False,
save_filename = "Airfoil_Polars",
file_type = ".png",
width = 11, height = 7):
"""
Generate plots of airfoil aerodynamic characteristics from analysis results.
Parameters
----------
polar_data : Data
Airfoil analysis results containing:
- cl_invisc[0] : array
Inviscid lift coefficients
- cd_invisc[0] : array
Inviscid drag coefficients
- cm_invisc[0] : array
Inviscid moment coefficients
- AoA[0] : array
Angles of attack [rad]
- Re[0] : array
Reynolds numbers
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 inviscid airfoil characteristics:
- Top left: Lift coefficient vs angle of attack
- Top right: Drag coefficient vs angle of attack
- Bottom left: Moment coefficient vs angle of attack
- Bottom right: Lift-to-drag ratio vs angle of attack
Results are plotted for a single Reynolds number case, with the
Reynolds number shown in the legend (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.compute_airfoil_inviscid : Analysis module
RCAIDE.Library.Plots.Aerodynamics.plot_airfoil_polar_files : Viscous polar plotting function
"""
# Get raw data polars
CL = polar_data.cl_invisc[0]
CD = polar_data.cd_invisc[0]
CM = polar_data.cm_invisc[0]
alpha = polar_data.AoA[0]/Units.degrees
Re_raw = polar_data.Re[0]
Re_val = str(round(Re_raw[0])/1e6)+'e6'
# 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)
fig = plt.figure(save_filename)
fig.set_size_inches(width,height)
axis_1 = plt.subplot(2,2,1)
axis_1.plot(alpha, CL, color = ps.color, marker = ps.markers[0], linewidth = ps.line_width, label = 'Re = '+Re_val)
axis_1.set_ylabel(r'$C_l$')
set_axes(axis_1)
axis_2 = plt.subplot(2,2,2)
axis_2.plot(alpha, CD, color = ps.color, marker = ps.markers[0], linewidth = ps.line_width)
axis_2.set_ylabel(r'$C_d$')
set_axes(axis_2)
axis_3 = plt.subplot(2,2,3)
axis_3.plot(alpha, CM, color = ps.color, marker = ps.markers[0], linewidth = ps.line_width)
axis_3.set_xlabel('AoA [deg]')
axis_3.set_ylabel(r'$C_m$')
set_axes(axis_3)
axis_4 = plt.subplot(2,2,4)
axis_4.plot(alpha, CL/CD, color = ps.color, marker = ps.markers[0], linewidth = ps.line_width)
axis_4.set_xlabel('AoA [deg]')
axis_4.set_ylabel(r'Cl/Cd')
axis_4.set_ylim([-20,20])
set_axes(axis_4)
if save_figure:
plt.savefig(save_filename + file_type)
return fig
