def test_airfoil_multielement():
a = asb.AirfoilInviscid(airfoil=[
asb.Airfoil("e423").repanel(n_points_per_side=50),
asb.Airfoil("naca6408").repanel(n_points_per_side=25).scale(
0.4, 0.4).rotate(np.radians(-20)).translate(0.9, -0.05),
],
op_point=asb.OperatingPoint(velocity=1, alpha=5))
def test_airfoil_symmetric_NACA():
a = asb.AirfoilInviscid(airfoil=[asb.Airfoil("naca0012").repanel(50)],
op_point=asb.OperatingPoint(
velocity=1,
alpha=0,
))
assert a.Cl == pytest.approx(0, abs=1e-8)
def display_graph(n_clicks, alpha, height, streamline_density,
operating_checklist, *kulfan_inputs):
### Figure out if a button was pressed
global n_clicks_last
if n_clicks is None:
n_clicks = 0
analyze_button_pressed = n_clicks > n_clicks_last
n_clicks_last = n_clicks
### Parse the checklist
ground_effect = "ground_effect" in operating_checklist
### Start constructing the figure
airfoil = asb.Airfoil(coordinates=asb.get_kulfan_coordinates(
lower_weights=np.array(kulfan_inputs[n_kulfan_inputs_per_side:]),
upper_weights=np.array(kulfan_inputs[:n_kulfan_inputs_per_side]),
TE_thickness=0,
enforce_continuous_LE_radius=False,
n_points_per_side=200,
))
### Do coordinates output
coordinates_output = "\n".join(
["```"] + ["AeroSandbox Airfoil"] +
["\t%f\t%f" % tuple(coordinate)
for coordinate in airfoil.coordinates] + ["```"])
### Continue doing the airfoil things
airfoil = airfoil.rotate(angle=-np.radians(alpha))
airfoil = airfoil.translate(0, height + 0.5 * np.sind(alpha))
fig = go.Figure()
fig.add_trace(
go.Scatter(
x=airfoil.x(),
y=airfoil.y(),
mode="lines",
name="Airfoil",
fill="toself",
line=dict(color="blue"),
))
### Default text output
text_output = 'Click "Analyze" to compute aerodynamics!'
xrng = (-0.5, 1.5)
yrng = (-0.6, 0.6) if not ground_effect else (0, 1.2)
if analyze_button_pressed:
analysis = asb.AirfoilInviscid(
airfoil=airfoil.repanel(50),
op_point=asb.OperatingPoint(
velocity=1,
alpha=0,
),
ground_effect=ground_effect,
)
x = np.linspace(*xrng, 100)
y = np.linspace(*yrng, 100)
X, Y = np.meshgrid(x, y)
u, v = analysis.calculate_velocity(x_field=X.flatten(),
y_field=Y.flatten())
U = u.reshape(X.shape)
V = v.reshape(Y.shape)
streamline_fig = ff.create_streamline(
x,
y,
U,
V,
arrow_scale=1e-16,
density=streamline_density,
line=dict(color="#ff82a3"),
name="Streamlines",
)
fig = go.Figure(data=streamline_fig.data + fig.data)
text_output = make_table(
pd.DataFrame({
"Engineering Quantity": ["C_L"],
"Value": [f"{analysis.Cl:.3f}"]
}))
fig.update_layout(
xaxis_title="x/c",
yaxis_title="y/c",
showlegend=False,
yaxis=dict(scaleanchor="x", scaleratio=1),
margin={"t": 0},
title=None,
)
fig.update_xaxes(range=xrng)
fig.update_yaxes(range=yrng)
return fig, text_output, [coordinates_output]
def test_airfoil_with_TE_gap():
a = asb.AirfoilInviscid(airfoil=asb.Airfoil("naca4408").repanel(100),
op_point=asb.OperatingPoint(velocity=1, alpha=5))
assert a.Cl == pytest.approx(1.0754, abs=0.01) # From XFoil
def test_airfoil_ground_effect():
a = asb.AirfoilInviscid(
airfoil=asb.Airfoil("naca4408").repanel(100).translate(0, 0.2),
op_point=asb.OperatingPoint(velocity=1, alpha=0),
ground_effect=True)
assert a.calculate_velocity(0, 0)[1] == pytest.approx(0)
