# RCAIDE/Library/Plots/Aerodynamics/plot_drag_components.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
import matplotlib.cm as cm
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# PLOTS
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def plot_drag_components(results,
save_figure=False,
show_legend= True,
save_filename="Drag_Components",
file_type=".png",
width = 11, height = 7):
"""
Generate plots showing the breakdown of aircraft drag components over time.
Parameters
----------
results : Data
Mission results data structure containing:
results.segments[i].conditions.aerodynamics.coefficients.drag with fields:
- parasite.total : array
Total parasite drag coefficient
- induced.total : array
Total induced drag coefficient
- compressible.total : array
Total compressibility drag coefficient
- miscellaneous.total : array
Other drag components coefficient
- total : array
Total aircraft drag coefficient
save_figure : bool, optional
Save figure to file if True, default False
show_legend : bool, optional
Display component legend if True, default True
save_filename : str, optional
Name for saved figure file, default "Drag_Components"
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 single plot showing:
- Parasite drag coefficient (CDp)
- Induced drag coefficient (CDi)
- Compressibility drag coefficient (CDc)
- Miscellaneous drag coefficient (CDm)
- Total drag coefficient (CD)
Each mission segment uses a different color from the inferno colormap.
Components are distinguished by different markers.
**Definitions**
'Parasite Drag'
Zero-lift drag due to viscous effects
'Induced Drag'
Drag due to lift production
'Compressibility Drag'
Additional drag due to shock waves
'Miscellaneous Drag'
Other sources including interference
See Also
--------
RCAIDE.Library.Plots.Common.set_axes : Standardized axis formatting
RCAIDE.Library.Plots.Common.plot_style : RCAIDE plot styling
"""
# 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 line colors for plots
line_colors = cm.inferno(np.linspace(0,0.9,len(results.segments)))
fig = plt.figure(save_filename)
axis_1 = plt.subplot(1,1,1)
fig.set_size_inches(12,height)
for i in range(len(results.segments)):
time = results.segments[i].conditions.frames.inertial.time[:,0] / Units.min
drag = results.segments[i].conditions.aerodynamics.coefficients.drag
cdp = drag.parasite.total[:,0]
cdi = drag.induced.total[:,0]
cdc = drag.compressible.total[:,0]
cdm = drag.miscellaneous.total[:,0]
cd = drag.total[:,0]
if i == 0:
axis_1.plot(time, cdp, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width, label = r'$C_{Dp}$')
axis_1.plot(time,cdi, color = line_colors[i], marker = ps.markers[1], linewidth = ps.line_width, label = r'$C_{Di}$')
axis_1.plot(time, cdc, color = line_colors[i], marker = ps.markers[2], linewidth = ps.line_width, label =r'$C_{Dc}$')
axis_1.plot(time, cdm, color = line_colors[i], marker = ps.markers[3], linewidth = ps.line_width, label =r'$C_{Dm}$')
axis_1.plot(time, cd, color = line_colors[i], marker = ps.markers[5], linewidth = ps.line_width, label =r'$C_D$')
else:
axis_1.plot(time, cdp, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width)
axis_1.plot(time,cdi, color = line_colors[i], marker = ps.markers[1], linewidth = ps.line_width)
axis_1.plot(time, cdc, color = line_colors[i], marker = ps.markers[2], linewidth = ps.line_width)
axis_1.plot(time, cdm, color = line_colors[i], marker = ps.markers[3], linewidth = ps.line_width)
axis_1.plot(time, cd, color = line_colors[i], marker = ps.markers[5], linewidth = ps.line_width)
set_axes(axis_1)
axis_1.set_xlabel('Time (mins)')
axis_1.set_ylabel('Drag Compoments')
if show_legend:
leg = fig.legend(bbox_to_anchor=(0.5, 0.95), loc='upper center', ncol = 4)
leg.set_title('Flight Segment', prop={'size': ps.legend_font_size, 'weight': 'heavy'})
# Adjusting the sub-plots for legend
fig.tight_layout()
fig.subplots_adjust(top=0.8)
# set title of plot
title_text = 'Drag Components'
fig.suptitle(title_text)
if save_figure:
plt.savefig(save_filename + file_type)
return fig
