## @ingroup Library-Plots-Performance-Aerodynamics
# RCAIDE/Library/Plots/Performance/Aerodynamics/plot_airfoil_surface_forces.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
from RCAIDE.Framework.Core import Units
import matplotlib.pyplot as plt
# ----------------------------------------------------------------------------------------------------------------------
# PLOTS
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def plot_airfoil_surface_forces(ap,
save_figure = False,
arrow_color = 'red',
save_filename = 'Airfoil_Cp_Distribution',
show_figure = True,
file_type = ".png"):
"""
Generate plots showing pressure forces on airfoil surface using arrows.
Parameters
----------
ap : Data
Airfoil properties data structure containing:
- x : array
Airfoil surface x-coordinates
- y : array
Airfoil surface y-coordinates
- cp : array
Pressure coefficients at surface points
- normals : array
Surface normal vectors [nx, ny]
- AoA : array
Angles of attack [rad]
- Re : array
Reynolds numbers
save_figure : bool, optional
Save figure to file if True, default False
arrow_color : str, optional
Color specification for force arrows, default 'red'
save_filename : str, optional
Name for saved figure file, default 'Airfoil_Cp_Distribution'
show_figure : bool, optional
Display figure if True, default True
file_type : str, optional
File extension for saved figure, default ".png"
Returns
-------
fig : matplotlib.figure.Figure
Notes
-----
Creates a figure showing:
- Airfoil profile
- Pressure force vectors as arrows normal to surface
- Arrow length proportional to local pressure coefficient
- Arrows point inward for negative Cp (suction)
- Arrows point outward for positive Cp (pressure)
A separate figure is created for each combination of angle of
attack and Reynolds number.
**Definitions**
'Surface Normal'
Unit vector perpendicular to airfoil surface
See Also
--------
RCAIDE.Library.Plots.Common.set_axes : Standardized axis formatting
RCAIDE.Library.Analysis.Aerodynamics.compute_pressure_forces : Analysis module
"""
# determine dimension of angle of attack and reynolds number
n_cpts = len(ap.AoA)
nAoA = len(ap.AoA[0])
n_pts = len(ap.x[0,0,:])- 1
for i in range(n_cpts):
for j in range(nAoA):
label = '_AoA_' + str(round(ap.AoA[i][j]/Units.degrees,2)) + '_deg_Re_' + str(round(ap.Re[i][j]/1000000,2)) + 'E6'
fig = plt.figure('Airfoil_Pressure_Normals' + label )
axis = fig.add_subplot(1,1,1)
axis.plot(ap.x[0,0,:], ap.y[0,0,:],'k-')
for k in range(n_pts):
dx_val = ap.normals[i,j,k,0]*abs(ap.cp[i,j,k])*0.1
dy_val = ap.normals[i,j,k,1]*abs(ap.cp[i,j,k])*0.1
if ap.cp[i,j,k] < 0:
plt.arrow(x= ap.x[i,j,k], y=ap.y[i,j,k] , dx= dx_val , dy = dy_val ,
fc=arrow_color, ec=arrow_color,head_width=0.005, head_length=0.01 )
else:
plt.arrow(x= ap.x[i,j,k]+dx_val , y= ap.y[i,j,k]+dy_val , dx= -dx_val , dy = -dy_val ,
fc=arrow_color, ec=arrow_color,head_width=0.005, head_length=0.01 )
return fig
