Source code for RCAIDE.Library.Plots.Aerodynamics.plot_aircraft_aerodynamics
# RCAIDE/Library/Plots/Aerodynamics/plot_aircraft_aerodynamic_analysis.py
#
#
# Created: Dec 2024, 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_aircraft_aerodynamics(results,
save_figure = False,
line_color = 'bo-',
line_color2 = 'rs--',
save_filename = "Aircraft_Aerodynamic_Analysis",
file_type = ".png",
width = 11, height = 7):
"""
Creates 3D surface plots of aircraft lift and drag coefficients as functions of
Mach number and angle of attack.
Parameters
----------
results : Results
RCAIDE results data structure containing:
- Mach : array
Array of Mach numbers
- alpha : array
Array of angles of attack in radians
- lift_coefficient : array
2D array of lift coefficients [Mach, alpha]
- drag_coefficient : array
2D array of drag coefficients [Mach, alpha]
save_figure : bool, optional
Flag for saving the figure (default: False)
line_color : str, optional
Color and style specification for lift plot (default: 'bo-')
line_color2 : str, optional
Color and style specification for drag plot (default: 'rs--')
save_filename : str, optional
Name of file for saved figure (default: "Aircraft_Aerodynamic_Analysis")
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
-------
None
Notes
-----
Creates visualization showing:
- Aerodynamic coefficient variations
- Mach number effects
- Angle of attack sensitivity
- Nonlinear aerodynamic behavior
Function displays and optionally saves two 3D surface plots:
Left Panel:
- Lift coefficient surface
- Shows CL variation with Mach and alpha
- X-axis: Mach number
- Y-axis: Angle of attack [degrees]
- Z-axis: Lift coefficient
Right Panel:
- Drag coefficient surface
- Shows CD variation with Mach and alpha
- X-axis: Mach number
- Y-axis: Angle of attack [degrees]
- Z-axis: Drag coefficient
**Definitions**
'Mach Number'
Ratio of airspeed to speed of sound
'Angle of Attack'
Angle between airflow and reference line
'Lift Coefficient'
Non-dimensional lift force
'Drag Coefficient'
Non-dimensional drag force
See Also
--------
plot_aerodynamic_coefficients : Time history of coefficients
plot_drag_components : Drag breakdown analysis
"""
# 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)
#------------------------------------------------------------------------
# setup figures
#------------------------------------------------------------------------
fig = plt.figure(save_filename + " Lift Coefficients")
fig.set_size_inches(12,6)
axis_1 = fig.add_subplot(1, 2, 1, projection='3d')
axis_2 = fig.add_subplot(1, 2, 2, projection='3d')
X, Y = np.meshgrid(results.Mach, results.alpha)
surf = axis_1.plot_surface(X, Y/Units.degree, results.lift_coefficient , cmap=cm.jet,linewidth=0, antialiased=False)
surf = axis_2.plot_surface(X, Y/Units.degree, results.drag_coefficient , cmap=cm.jet,linewidth=0, antialiased=False)
axis_1.set_title('$C_L$')
axis_2.set_title('$C_D$')
axis_1.set_ylabel('AoA')
axis_2.set_ylabel('AoA')
axis_1.set_xlabel('Mach')
axis_2.set_xlabel('Mach')
# set title of plot
title_text = 'Aircraft Aerodynamic Analysis '
fig.suptitle(title_text)
plt.tight_layout()
if save_figure:
fig.savefig(save_filename + file_type)
plt.tight_layout()
return
