"""Demonstrates running Ptera Software's UnsteadyRingVortexLatticeMethodSolver on three
airplanes flying in formation, each with custom flapping wings."""
import pterasoftware as ps
x_spacing = 13
y_spacing = 13
# Create the lead Airplane.
lead_airplane = ps.geometry.airplane.Airplane(
wings=[
ps.geometry.wing.Wing(
wing_cross_sections=[
ps.geometry.wing_cross_section.WingCrossSection(
airfoil=ps.geometry.airfoil.Airfoil(
name="naca0012",
),
num_spanwise_panels=10,
chord=1.75,
control_surface_symmetry_type="symmetric",
spanwise_spacing="cosine",
),
ps.geometry.wing_cross_section.WingCrossSection(
airfoil=ps.geometry.airfoil.Airfoil(
name="naca0012",
),
num_spanwise_panels=None,
chord=1.5,
Lp_Wcsp_Lpp=(0.75, 6.0, 0.0),
control_surface_symmetry_type="symmetric",
spanwise_spacing=None,
),
],
name="Main Wing",
Ler_Gs_Cgs=(0.0, 0.25, 0.0),
angles_Gs_to_Wn_ixyz=(0.0, 5.0, 0.0),
symmetric=True,
symmetryNormal_G=(0.0, 1.0, 0.0),
symmetryPoint_G_Cg=(0.0, 0.0, 0.0),
num_chordwise_panels=4,
chordwise_spacing="uniform",
),
],
name="Lead Airplane",
Cg_GP1_CgP1=(0.0, 0.0, 0.0),
)
# Now define the lead Airplane's AirplaneMovement.
lead_airplane_movement = ps.movements.airplane_movement.AirplaneMovement(
base_airplane=lead_airplane,
wing_movements=[
# Define the main Wing's WingMovement.
ps.movements.wing_movement.WingMovement(
base_wing=lead_airplane.wings[0],
wing_cross_section_movements=[
# Define the root WingCrossSection's WingCrossSectionMovement.
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=lead_airplane.wings[0].wing_cross_sections[
0
]
),
# Define the tip WingCrossSection's WingCrossSectionMovement.
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=lead_airplane.wings[0].wing_cross_sections[
1
]
),
],
ampAngles_Gs_to_Wn_ixyz=(25.0, 0.0, 0.0),
periodAngles_Gs_to_Wn_ixyz=(1.0, 0.0, 0.0),
spacingAngles_Gs_to_Wn_ixyz=("sine", "sine", "sine"),
phaseAngles_Gs_to_Wn_ixyz=(0.0, 0.0, 0.0),
),
# Define the reflected main Wing's WingMovement.
ps.movements.wing_movement.WingMovement(
base_wing=lead_airplane.wings[1],
wing_cross_section_movements=[
# Define the root WingCrossSection's WingCrossSectionMovement.
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=lead_airplane.wings[1].wing_cross_sections[
0
]
),
# Define the tip WingCrossSection's WingCrossSectionMovement.
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=lead_airplane.wings[1].wing_cross_sections[
1
]
),
],
ampAngles_Gs_to_Wn_ixyz=(25.0, 0.0, 0.0),
periodAngles_Gs_to_Wn_ixyz=(1.0, 0.0, 0.0),
spacingAngles_Gs_to_Wn_ixyz=("sine", "sine", "sine"),
phaseAngles_Gs_to_Wn_ixyz=(0.0, 0.0, 0.0),
),
],
)
# Create the trailing right Airplane.
trailing_right_airplane = ps.geometry.airplane.Airplane(
wings=[
ps.geometry.wing.Wing(
wing_cross_sections=[
ps.geometry.wing_cross_section.WingCrossSection(
airfoil=ps.geometry.airfoil.Airfoil(
name="naca0012",
),
num_spanwise_panels=10,
chord=1.75,
control_surface_symmetry_type="symmetric",
spanwise_spacing="cosine",
),
ps.geometry.wing_cross_section.WingCrossSection(
airfoil=ps.geometry.airfoil.Airfoil(
name="naca0012",
),
num_spanwise_panels=None,
chord=1.5,
Lp_Wcsp_Lpp=(0.75, 6.0, 0.0),
control_surface_symmetry_type="symmetric",
spanwise_spacing=None,
),
],
name="Main Wing",
Ler_Gs_Cgs=(0.0, 0.25, 0.0),
angles_Gs_to_Wn_ixyz=(0.0, 5.0, 0.0),
symmetric=True,
symmetryNormal_G=(0.0, 1.0, 0.0),
symmetryPoint_G_Cg=(0.0, 0.0, 0.0),
num_chordwise_panels=4,
chordwise_spacing="uniform",
),
],
name="Trailing Right Airplane",
Cg_GP1_CgP1=(x_spacing, y_spacing, 0.0),
)
# Create the trailing right Airplane's AirplaneMovement.
trailing_right_airplane_movement = ps.movements.airplane_movement.AirplaneMovement(
base_airplane=trailing_right_airplane,
wing_movements=[
ps.movements.wing_movement.WingMovement(
base_wing=trailing_right_airplane.wings[0],
wing_cross_section_movements=[
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_right_airplane.wings[
0
].wing_cross_sections[0]
),
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_right_airplane.wings[
0
].wing_cross_sections[1]
),
],
ampAngles_Gs_to_Wn_ixyz=(25.0, 0.0, 0.0),
periodAngles_Gs_to_Wn_ixyz=(1.0, 0.0, 0.0),
spacingAngles_Gs_to_Wn_ixyz=("sine", "sine", "sine"),
phaseAngles_Gs_to_Wn_ixyz=(0.0, 0.0, 0.0),
),
ps.movements.wing_movement.WingMovement(
base_wing=trailing_right_airplane.wings[1],
wing_cross_section_movements=[
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_right_airplane.wings[
1
].wing_cross_sections[0]
),
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_right_airplane.wings[
1
].wing_cross_sections[1]
),
],
ampAngles_Gs_to_Wn_ixyz=(25.0, 0.0, 0.0),
periodAngles_Gs_to_Wn_ixyz=(1.0, 0.0, 0.0),
spacingAngles_Gs_to_Wn_ixyz=("sine", "sine", "sine"),
phaseAngles_Gs_to_Wn_ixyz=(0.0, 0.0, 0.0),
),
],
)
# Create the trailing left Airplane.
trailing_left_airplane = ps.geometry.airplane.Airplane(
wings=[
ps.geometry.wing.Wing(
wing_cross_sections=[
ps.geometry.wing_cross_section.WingCrossSection(
airfoil=ps.geometry.airfoil.Airfoil(
name="naca0012",
),
num_spanwise_panels=10,
chord=1.75,
control_surface_symmetry_type="symmetric",
spanwise_spacing="cosine",
),
ps.geometry.wing_cross_section.WingCrossSection(
airfoil=ps.geometry.airfoil.Airfoil(
name="naca0012",
),
num_spanwise_panels=None,
chord=1.5,
Lp_Wcsp_Lpp=(0.75, 6.0, 0.0),
control_surface_symmetry_type="symmetric",
spanwise_spacing=None,
),
],
name="Main Wing",
Ler_Gs_Cgs=(0.0, 0.25, 0.0),
angles_Gs_to_Wn_ixyz=(0.0, 5.0, 0.0),
symmetric=True,
symmetryNormal_G=(0.0, 1.0, 0.0),
symmetryPoint_G_Cg=(0.0, 0.0, 0.0),
num_chordwise_panels=4,
chordwise_spacing="uniform",
),
],
name="Trailing Left Airplane",
Cg_GP1_CgP1=(x_spacing, -y_spacing, 0.0),
)
# Create the trailing left Airplane's AirplaneMovement.
trailing_left_airplane_movement = ps.movements.airplane_movement.AirplaneMovement(
base_airplane=trailing_left_airplane,
wing_movements=[
ps.movements.wing_movement.WingMovement(
base_wing=trailing_left_airplane.wings[0],
wing_cross_section_movements=[
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_left_airplane.wings[
0
].wing_cross_sections[0]
),
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_left_airplane.wings[
0
].wing_cross_sections[1]
),
],
ampAngles_Gs_to_Wn_ixyz=(25.0, 0.0, 0.0),
periodAngles_Gs_to_Wn_ixyz=(1.0, 0.0, 0.0),
spacingAngles_Gs_to_Wn_ixyz=("sine", "sine", "sine"),
phaseAngles_Gs_to_Wn_ixyz=(0.0, 0.0, 0.0),
),
ps.movements.wing_movement.WingMovement(
base_wing=trailing_left_airplane.wings[1],
wing_cross_section_movements=[
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_left_airplane.wings[
1
].wing_cross_sections[0]
),
ps.movements.wing_cross_section_movement.WingCrossSectionMovement(
base_wing_cross_section=trailing_left_airplane.wings[
1
].wing_cross_sections[1]
),
],
ampAngles_Gs_to_Wn_ixyz=(25.0, 0.0, 0.0),
periodAngles_Gs_to_Wn_ixyz=(1.0, 0.0, 0.0),
spacingAngles_Gs_to_Wn_ixyz=("sine", "sine", "sine"),
phaseAngles_Gs_to_Wn_ixyz=(0.0, 0.0, 0.0),
),
],
)
# Define an OperatingPoint. This defines the state at which all the Airplanes are
# operating.
example_operating_point = ps.operating_point.OperatingPoint(vCg__E=15.0, alpha=0.0)
# Define the OperatingPoint's OperatingPointMovement.
example_operating_point_movement = (
ps.movements.operating_point_movement.OperatingPointMovement(
base_operating_point=example_operating_point
)
)
# Delete the extraneous pointers to the Airplanes and the OperatingPoint, as these are
# now accessible within their respective movement objects.
del lead_airplane
del trailing_right_airplane
del trailing_left_airplane
del example_operating_point
# Define the Movement. This contains each AirplaneMovement and the
# OperatingPointMovement.
example_movement = ps.movements.movement.Movement(
airplane_movements=[
lead_airplane_movement,
trailing_right_airplane_movement,
trailing_left_airplane_movement,
],
operating_point_movement=example_operating_point_movement,
num_cycles=3,
)
# Delete the extraneous pointers to the AirplaneMovements and the
# OperatingPointMovement, as these are now accessible within the Movement.
del lead_airplane_movement
del trailing_right_airplane_movement
del trailing_left_airplane_movement
del example_operating_point_movement
# Using the Movement, create an UnsteadyProblem.
example_problem = ps.problems.UnsteadyProblem(
movement=example_movement,
)
# Define a new UnsteadyRingVortexLatticeMethodSolver.
example_solver = (
ps.unsteady_ring_vortex_lattice_method.UnsteadyRingVortexLatticeMethodSolver(
unsteady_problem=example_problem,
)
)
# Delete the extraneous pointer to the UnsteadyProblem.
del example_problem
# Run the solver.
example_solver.run(
prescribed_wake=True,
show_progress=True,
)
print("The simulation has finished.")
# Save the solved solver to a compressed JSON file. This allows us to load the results
# later without re-running the simulation. Use ".json.gz" for gzip compression, which is
# recommended over plain JSONs for all but the smallest, unmeshed geometry objects.
print("Saving the solver...")
ps.save("example_solver.json.gz", example_solver)
print("Finished saving the solver.")
# Load the saved solver. The loaded object is identical to the original and can be
# passed to any output function.
print("Loading the saved solver...")
loaded_solver = ps.load("example_solver.json.gz")
print("Finished loading the saved solver.")
# Now that we have run the solver, we can create an animation of the results.
ps.output.animate(
unsteady_solver=loaded_solver,
scalar_type="lift",
show_wake_vortices=True,
save=True,
)
