Source code for RCAIDE.Library.Plots.Aerodynamics.plot_surface_pressures
# RCAIDE/Library/Plots/Performance/Aerodynamics/plot_surface_pressures.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
from RCAIDE.Library.Plots.Common import set_axes, plot_style
import matplotlib.pyplot as plt
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# PLOTS
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def plot_surface_pressures(results,
save_figure = False,
save_filename = "Surface_Pressure",
file_type = ".png"):
"""
Creates contour plots of surface pressure distributions on aircraft lifting surfaces.
Parameters
----------
results : Results
RCAIDE results data structure containing:
- segments[i].conditions.aerodynamics
Aerodynamic data containing:
- coefficients.surface_pressure[ti]
Pressure coefficient at each control point
- segments[i].analyses.aerodynamics.vehicle
Vehicle data containing:
- vortex_distribution
Distribution data with:
- n_cw : array
Number of chordwise panels per wing
- n_sw : array
Number of spanwise panels per wing
- n_w : int
Number of wings
- XC, YC : arrays
Control point coordinates
- X : array
Surface point x-coordinates
- wings : list
Wing components with:
- vertical : bool
Flag for vertical surfaces
- symmetric : bool
Flag for symmetric surfaces
save_figure : bool, optional
Flag for saving the figure (default: False)
save_filename : str, optional
Name of file for saved figure (default: "Surface_Pressure")
file_type : str, optional
File extension for saved figure (default: ".png")
Returns
-------
None
Notes
-----
Creates visualization showing:
- Surface pressure distributions
- Spanwise pressure variations
- Chordwise pressure variations
- Wing geometry outlines
**Definitions**
'Pressure Coefficient'
Non-dimensional pressure difference
'Control Point'
Location where pressure is evaluated
'Lifting Surface'
Wing, tail, or other aerodynamic surface
'Planform'
Top-view shape of lifting surface
See Also
--------
RCAIDE.Library.Plots.Aerodynamics.plot_lift_distribution : Spanwise lift analysis
RCAIDE.Library.Plots.Aerodynamics.plot_aerodynamic_coefficients : Overall coefficient plots
"""
vehicle = results.segments[0].analyses.aerodynamics.vehicle
VD = vehicle.vortex_distribution
n_cw = VD.n_cw
n_cw = VD.n_cw
n_sw = VD.n_sw
n_w = VD.n_w
b_pts = np.concatenate(([0],np.cumsum(VD.n_sw*VD.n_cw)))
# Create a boolean for not plotting vertical wings
idx = 0
plot_flag = np.ones(n_w)
for wing in vehicle.wings:
if wing.vertical:
plot_flag[idx] = 0
idx += 1
else:
idx += 1
if wing.vertical and wing.symmetric:
plot_flag[idx] = 0
idx += 1
else:
idx += 1
img_idx = 1
seg_idx = 1
for segment in results.segments.values():
num_ctrl_pts = len(segment.conditions.frames.inertial.time)
for ti in range(num_ctrl_pts):
CP = segment.conditions.aerodynamics.coefficients.surface_pressure[ti]
fig = plt.figure()
axes = plt.subplot(1, 1, 1)
x_max = max(VD.XC) + 2
y_max = max(VD.YC) + 2
axes.set_ylim(x_max, 0)
axes.set_xlim(-y_max, y_max)
fig.set_size_inches(8,8)
for i in range(n_w):
n_pts = (n_sw[i] + 1) * (n_cw[i]+ 1)
xc_pts = VD.X[i*(n_pts):(i+1)*(n_pts)]
x_pts = np.reshape(np.atleast_2d(VD.XC[b_pts[i]:b_pts[i+1]]).T, (n_sw[i],-1))
y_pts = np.reshape(np.atleast_2d(VD.YC[b_pts[i]:b_pts[i+1]]).T, (n_sw[i],-1))
z_pts = np.reshape(np.atleast_2d(CP[b_pts[i]:b_pts[i+1]]).T, (n_sw[i],-1))
x_pts_p = x_pts*((n_cw[i]+1)/n_cw[i]) - x_pts[0,0]*((n_cw[i]+1)/n_cw[i]) + xc_pts[0]
points = np.linspace(0.001,1,50)
A = np.cumsum(np.sin(np.pi/2*points))
levels = -(np.concatenate([-A[::-1],A[1:]])/(2*A[-1]) + A[-1]/(2*A[-1]) )[::-1]*0.015
color_map = plt.cm.get_cmap('jet')
rev_cm = color_map.reversed()
CS = axes.contourf(y_pts,x_pts_p, z_pts, cmap = rev_cm,extend='both')
# Set Color bar
cbar = fig.colorbar(CS, ax=axes)
cbar.ax.set_ylabel('$C_{P}$', rotation = 0)
plt.axis('off')
plt.grid(None)
if save_figure:
plt.savefig( save_filename + '_' + str(img_idx) + file_type)
img_idx += 1
seg_idx +=1
return
