## @ingroup Library-Plots-Performance-Aerodynamics
# RCAIDE/Library/Plots/Performance/Aerodynamics/plot_airfoil_boundary_layer_properties.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
from RCAIDE.Framework.Core import Units
from RCAIDE.Library.Plots.Common import set_axes, plot_style
# python imports
import matplotlib.pyplot as plt
import matplotlib.cm as cm
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# PLOTS
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def plot_airfoil_boundary_layer_properties(ap,
save_figure = False,
show_legend = False,
file_type = ".png",
save_filename = 'Airfoil_with_Boundary_Layers',
width = 11, height = 7):
"""
Generate plots of airfoil boundary layer properties and distributions.
Parameters
----------
ap : Data
Airfoil properties data structure containing:
- x, y : arrays
Airfoil surface coordinates
- y_bl : array
Boundary layer displacement thickness coordinates
- Ue_Vinf : array
Edge velocity ratio (Ue/U∞)
- H : array
Shape factor
- delta_star : array
Displacement thickness
- delta : array
Boundary layer thickness
- theta : array
Momentum thickness
- cf : array
Skin friction coefficient
- Re_theta : array
Momentum thickness Reynolds number
- AoA : array
Angles of attack [rad]
- Re : array
Reynolds numbers
save_figure : bool, optional
Save figures to files if True, default False
show_legend : bool, optional
Display case legend if True, default False
file_type : str, optional
File extension for saved figures, default ".png"
save_filename : str, optional
Base name for saved figure files, default 'Airfoil_with_Boundary_Layers'
width : float, optional
Figure width in inches, default 11
height : float, optional
Figure height in inches, default 7
Returns
-------
fig : matplotlib.figure.Figure
Figure showing airfoil with boundary layers
Notes
-----
Creates multiple figures showing:
- Airfoil profile with boundary layer thickness
- Edge velocity distribution
- Shape factor distribution
- Displacement thickness distribution
- Boundary layer thickness distribution
- Momentum thickness distribution
- Skin friction distribution
- Momentum thickness Reynolds number distribution
Each case (combination of AoA and Re) is plotted in a different color.
Upper and lower surfaces are distinguished by line style.
**Definitions**
'Shape Factor'
Ratio of displacement to momentum thickness
'Displacement Thickness'
Distance flow is displaced from surface
'Momentum Thickness'
Loss of momentum flux in boundary layer
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_boundary_layer : Analysis module
"""
# get plotting style
ps = plot_style()
plot_quantity(ap, ap.Ue_Vinf, r'U_e/U_inf$' ,'Inviscid Edge Velocity',0,3,file_type,show_legend,save_figure,width,height)
plot_quantity(ap, ap.H, r'H' ,'Kinematic Shape Parameter',-1,10,file_type,show_legend,save_figure,width,height)
plot_quantity(ap, ap.delta_star, r'delta*' ,'Displacement Thickness',-0.01,0.1 ,file_type,show_legend,save_figure,width,height)
plot_quantity(ap, ap.delta , r'delta' ,'Boundary Layer Thickness',-0.01,0.1 ,file_type,show_legend,save_figure,width,height)
plot_quantity(ap, ap.theta, r'theta' ,'Momentum Thickness',-0.001, 0.015,file_type,show_legend,save_figure,width,height)
plot_quantity(ap, ap.cf, r'c_f' , 'Skin Friction Coefficient',-0.1,1,file_type,show_legend,save_figure,width,height)
plot_quantity(ap, ap.Re_theta, r'Re_theta' ,'Theta Reynolds Number',-2E2,1E3,file_type,show_legend,save_figure,width,height)
n_cpts = len(ap.AoA[:,0])
n_cases = len(ap.AoA[0,:])
# create array of colors for difference reynolds numbers
blues = cm.winter(np.linspace(0,0.9,n_cases))
reds = cm.autumn(np.linspace(0,0.9,n_cases))
fig = plt.figure(save_filename)
fig.set_size_inches(width,height)
for i in range(n_cpts):
for j in range(n_cases):
axis_0 = plt.subplot(1,1,1)
axis_0.plot(ap.x[i,j], ap.y[i,j], color = blues[j], marker = ps.markers[0], linewidth = ps.line_width )
axis_0.plot(ap.x[i,j][:-1], ap.y_bl[i,j], color = reds[j], marker = ps.markers[0], linewidth = ps.line_width )
set_axes(axis_0)
# set title of plot
title_text = 'Airfoil with Boundary Layers'
fig.suptitle(title_text)
if save_figure:
plt.savefig(save_filename + file_type)
return fig
# ----------------------------------------------------------------------
# Plot Quantity
# ----------------------------------------------------------------------
[docs]
def plot_quantity(ap, q, qaxis, qname, ylim_low, ylim_high, file_type, show_legend, save_figure, width, height):
"""
Generate standardized plots of boundary layer quantities along airfoil surfaces.
Parameters
----------
ap : Data
Airfoil properties data structure containing:
- x : array
Airfoil surface coordinates
- AoA : array
Angles of attack [rad]
- Re : array
Reynolds numbers
q : array
Values of quantity to plot along airfoil surface
qaxis : str
LaTeX-formatted axis label for quantity
qname : str
Descriptive name for quantity (used in title)
ylim_low : float
Lower limit for y-axis
ylim_high : float
Upper limit for y-axis
file_type : str
File extension for saved figure
show_legend : bool
Display case legend if True
save_figure : bool
Save figure to file if True
width : float
Figure width in inches
height : float
Figure height in inches
Returns
-------
None
Notes
-----
Creates a single figure showing the specified quantity distribution
along the airfoil surface for all cases (combinations of AoA and Re).
Cases are plotted in different colors using the inferno colormap.
Legend entries show AoA in degrees and Re number for each case.
The plot uses standardized RCAIDE styling and axis formatting.
See Also
--------
RCAIDE.Library.Plots.Common.set_axes : Standardized axis formatting
RCAIDE.Library.Plots.Common.plot_style : RCAIDE plot styling
RCAIDE.Library.Plots.Aerodynamics.plot_airfoil_boundary_layer_properties : Main plotting function
"""
# 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)
n_cpts = len(ap.AoA[:,0])
n_cases = len(ap.AoA[0,:])
fig = plt.figure(qname.replace(" ", "_"))
fig.set_size_inches(width,height)
axis = fig.add_subplot(1,1,1)
# get line colors for plots
line_colors = cm.inferno(np.linspace(0,0.9,n_cases))
for i in range(n_cpts):
for j in range(n_cases):
case_label = 'AoA: ' + str(round(ap.AoA[i,j]/Units.degrees, 2)) + ', Re: ' + str(ap.Re[i,j])
axis.plot( ap.x[i,j], q[i,j], color = line_colors[j], marker = ps.markers[0], linewidth = ps.line_width, label =case_label)
axis.set_ylim([ylim_low,ylim_high])
if show_legend:
leg = fig.legend(bbox_to_anchor=(0.5, 0.95), loc='upper center', ncol = 4)
# Adjusting the sub-plots for legend
fig.subplots_adjust(top=0.8)
# set title of plot
title_text = qname
fig.suptitle(title_text)
if save_figure:
plt.savefig(qname.replace(" ", "_") + file_type)
return
