def save_all_airfoil_spm_geometry_test():
"""
This test saves all airfoil images to
the given directory.
"""
# Write your own path with airfoil data here
airfoil_path = r'C:\Users\User\Documents\python\aero\airfoils_data'
# Write your own path to save images here (Path must already exists)
picture_path = r'C:\Users\User\Documents\python\aero\airfoils_picture'
files = listdir(airfoil_path)
for i, file in enumerate(files):
airfoil = figure.Airfoil(file, airfoil_path)
geometry = Geometry(airfoil)
# Create grid
x0, y0, dx, dy = airfoil.rect
grid = figure.Grid(x0, y0, dx + 0.2, dy + 0.5)
# Plot
plt = Plot(grid)
plt.plot_figure(airfoil)
plt.plot_source_panel_method(geometry)
plt.title(file)
plt.save_image('{}\\{}.png'.format(picture_path, file))
plt.close()
print(i, file)
def spm_geometry_and_inside_outside_test():
# # Write your own path here
# path = r'C:\Users\User\Documents\python\aero\airfoils_data'
# # Airfoil name
# name = 'ua79sff.txt'
# test_fig = figure.Airfoil(name, path)
test_fig = figure.Circle(10, num_points=20)
# test_fig = figure.Ellipse(10, 5, num_points=50)
# test_fig = figure.Square(10, num_points=50)
# test_fig = figure.Rectangle(10, 5, num_points=50)
# test_fig = figure.Triangle((0, 0), (6, 0), (3, 3))
# test_fig = figure.Triangle((0, 0), (0, 6), (3, 3))
# test_fig = figure.Triangle((0, 0), (6, 3), (3, 4))
# test_fig = figure.Polygon('Polygon',
# [(1, 1), (2, 2), (3, 3),
# (2, 3), (2, 4), (1, 4), (0, 3)])
# test_fig = figure.Ogive(2, 1, 5)
geometry = Geometry(test_fig, 1)
x0, y0, dx, dy = test_fig.rect
grid = figure.Grid(x0, y0,
1.5 * dx, 1.5 * dy, 20)
plt = Plot(grid)
plt.plot_figure(test_fig)
plt.plot_source_panel_method(geometry)
for x in grid.x:
for y in grid.y:
res = test_fig.is_inside(x, y)
if not res:
plt.plot_point(x, y, '.y')
plt.show()
def circle_pressure_coef_spm_test():
circle = figure.Circle(10, num_points=100)
spm = SPMCircle(circle, 1.0)
grid = figure.Grid(np.pi, -1.0, 2.0 * np.pi, 4.0)
plt = Plot(grid)
tetta = np.linspace(0.0, 2.*np.pi, 360)
cp = 1. - 4. * (np.sin(tetta) ** 2)
analytic_coef = figure.Figure('Pressure coef', tetta, cp)
plt.plot_figure(analytic_coef)
spm_coef = figure.Figure('Spm coef', spm.geometry.angle_cp, spm.surface_cp)
plt.plot_figure(spm_coef, '*b')
plt.show()
def circulation_flow_figure_test() -> None:
"""
This test shows example of how circulation
can be calculated for different shapes and
for given flow.
"""
# Make grid for plot
grid = figure.Grid(0, 0, 20, 20)
# Create flow
lift_flow = flow.LiftingCylinderFlow(vel=2, kappa=5, gamma=15)
# Calculate velocities in the given points of the grid
lift_flow.set_grid(grid)
# Init plot
plt = Plot(grid)
# Create figures
ellipse = figure.Ellipse(8.0, 1.0, 0.0, -7.0)
circle = figure.Circle(2.0)
square = figure.Square(4.0, 6.0, 5.0, num_points=360)
triangle = figure.Triangle((-3.0, 3.0), (-8.0, 3.0), (-5.5, 8.0))
# Draw the flow's streamlines and the figures
plt.plot_stream_line(lift_flow)
plt.plot_figure(ellipse)
plt.plot_figure(circle)
plt.plot_figure(square)
plt.plot_figure(triangle)
# Calculate circulations inside the given figures
el_gamma = Circulation.circulation(grid, lift_flow, ellipse)
ci_gamma = Circulation.circulation(grid, lift_flow, circle)
sq_gamma = Circulation.circulation(grid, lift_flow, square)
tr_gamma = Circulation.circulation(grid, lift_flow, triangle)
# Draw text
plt.plot_text(ellipse.center, '{:.02f}'.format(el_gamma))
plt.plot_text(circle.center, '{:.02f}'.format(ci_gamma))
plt.plot_text(square.center, '{:.02f}'.format(sq_gamma))
plt.plot_text(triangle.center, '{:.02f}'.format(tr_gamma))
# Show the plot
plt.show()
def grid_source_panel_method_test():
fgr = figure.Circle(10, num_points=180)
# fgr = figure.Ellipse(10, 5, num_points=100)
# fgr = figure.Square(10, num_points=100)
# fgr = figure.Rectangle(10, 5, num_points=100)
# fgr = figure.Triangle((0, 0), (6, 0), (3, 3))
# fgr = figure.Ogive(2, 1, 5)
spm = SourcePanelMethod(fgr, 1)
grid = figure.Grid(0.0, 0.0, 30.0, 30.0, 30)
plt = Plot(grid)
spm.set_grid(grid)
plt.plot_filled_figure(fgr)
plt.plot_stream_line(spm)
# plt.plot_flow(spm)
# plt.plot_contour(spm)
plt.show()
def plot_airfoil_data_test() -> None:
"""
This test plots airfoils by given name.
"""
# Write your own path here
path = r'C:\Users\User\Documents\python\aero\airfoils_data'
# Airfoil name, offline mode
name = 'naca0006.txt'
airfoil = figure.Airfoil(name, path)
# Airfoil name, online mode
# name = 'naca0006'
# airfoil = figure.Airfoil(name, online=True)
# Create grid
x0, y0, dx, dy = airfoil.rect
grid = figure.Grid(x0, y0, dx + 0.2, dy + 0.5)
# Plot
plt = Plot(grid)
plt.plot_figure(airfoil)
plt.title(name)
plt.show()
def airfoil_pressure_coef_spm_test():
# Write your own path here
path = r'C:\Users\User\Documents\python\aero\airfoils_data'
# Airfoil name
name = 'naca2412.txt'
test_fig = figure.Airfoil(name, path)
spm = SourcePanelMethod(test_fig, 1, 0.0 * np.pi / 180.0)
cp_upper = spm.surface_cp[spm.geometry.yc >= 0]
x_upper = spm.geometry.xc[spm.geometry.yc >= 0]
cp_lower = spm.surface_cp[spm.geometry.yc < 0]
x_lower = spm.geometry.xc[spm.geometry.yc < 0]
fgr_upper = figure.Figure('', x_upper, cp_upper)
fgr_lower = figure.Figure('', x_lower, cp_lower)
x01, y01, dx1, dy1 = fgr_upper.rect
x02, y02, dx2, dy2 = fgr_lower.rect
grid = figure.Grid(min(x01, x02), min(y01, y02),
max(dx1, dx2), max(dy1, dy2))
plt = Plot(grid)
plt.plot_figure(fgr_upper, '*b')
plt.plot_figure(fgr_lower, '-r')
plt.invert_y_axis()
plt.show()