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added isolated propeller and bet evtol examples #1174

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1c2755d
added isolated propeller and bet evtol examples
wiktor-flex Jun 18, 2025
53e7ef3
black
wiktor-flex Jun 18, 2025
e3461bb
fixed project upload
wiktor-flex Jun 18, 2025
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113 changes: 113 additions & 0 deletions examples/advanced_simulations/rotorcraft/BET_eVTOL.py
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Original file line number Diff line number Diff line change
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import flow360 as fl
from flow360.examples import BETEVTOL

BETEVTOL.get_files()

project = fl.Project.from_geometry(BETEVTOL.geometry, name="BET eVTOL")

geometry = project.geometry
geometry.group_edges_by_tag("edgeId")
geometry.group_faces_by_tag("faceId")


with fl.SI_unit_system:
box1 = fl.Box(name="Box 1", center=[2, 0, 0.5], size=[12, 16, 4])
box2 = fl.Box(name="Box 2", center=[8, 0, 0.5], size=[24, 32, 8])
cylinder1 = fl.Cylinder(
name="BET 1", center=[-1.95, -6, 0.57], axis=[-1, 0, 0], outer_radius=1.5, height=0.2
)
cylinder2 = fl.Cylinder(
name="BET 2", center=[-1.95, -2.65, 0.51], axis=[-1, 0, 0], outer_radius=1.5, height=0.2
)
cylinder3 = fl.Cylinder(
name="BET 3", center=[-1.95, 2.65, 0.51], axis=[-1, 0, 0], outer_radius=1.5, height=0.2
)
cylinder4 = fl.Cylinder(
name="BET 4", center=[-1.95, 6, 0.57], axis=[-1, 0, 0], outer_radius=1.5, height=0.2
)
cylinder5 = fl.Cylinder(
name="BET 5", center=[2.7, -6, 1.06], axis=[0, 0, 1], outer_radius=1.5, height=0.2
)
cylinder6 = fl.Cylinder(
name="BET 6", center=[2.7, -2.65, 1.06], axis=[0, 0, 1], outer_radius=1.5, height=0.2
)
cylinder7 = fl.Cylinder(
name="BET 7", center=[2.7, 2.65, 1.06], axis=[0, 0, 1], outer_radius=1.5, height=0.2
)
cylinder8 = fl.Cylinder(
name="BET 8", center=[2.7, 6, 1.06], axis=[0, 0, 1], outer_radius=1.5, height=0.2
)
slices = [
fl.Slice(name=f"Slice BET {i+1}", normal=[0, 1, 0], origin=[0, originY, 0])
for i, originY in enumerate([-6, -2.65, 2.65, 6])
]
farfield = fl.AutomatedFarfield(name="Farfield")
params = fl.SimulationParams(
meshing=fl.MeshingParams(
defaults=fl.MeshingDefaults(
surface_max_edge_length=0.05, boundary_layer_first_layer_thickness=0.01 * fl.u.mm
),
volume_zones=[farfield],
refinements=[
fl.AxisymmetricRefinement(
name="BET refinement",
spacing_axial=0.01,
spacing_radial=0.03,
spacing_circumferential=0.03,
entities=[
cylinder1,
cylinder2,
cylinder3,
cylinder4,
cylinder5,
cylinder6,
cylinder7,
cylinder8,
],
),
fl.UniformRefinement(name="Uniform refinement 0.05", spacing=0.05, entities=box1),
fl.UniformRefinement(name="Uniform refinement 0.1", spacing=0.1, entities=box2),
],
),
reference_geometry=fl.ReferenceGeometry(
area=16.8, moment_center=[0, 0, 0], moment_length=[1.4, 1.4, 1.4]
),
operating_condition=fl.AerospaceCondition(velocity_magnitude=70, alpha=15 * fl.u.deg),
models=[
fl.Wall(name="Wall", surfaces=[geometry["*"]]),
fl.Freestream(name="Freestream", surfaces=[farfield.farfield]),
fl.Fluid(
navier_stokes_solver=fl.NavierStokesSolver(relative_tolerance=0.01),
turbulence_model_solver=fl.SpalartAllmaras(
relative_tolerance=0.01,
rotation_correction=True,
hybrid_model=fl.DetachedEddySimulation(),
),
),
fl.BETDisk.from_file(BETEVTOL.extra["disk13"]),
fl.BETDisk.from_file(BETEVTOL.extra["disk24"]),
fl.BETDisk.from_file(BETEVTOL.extra["disk57"]),
fl.BETDisk.from_file(BETEVTOL.extra["disk68"]),
],
time_stepping=fl.Unsteady(
steps=1000,
step_size=0.0004,
max_pseudo_steps=30,
CFL=fl.AdaptiveCFL(
min=1, max=3000, max_relative_change=50, convergence_limiting_factor=0.1
),
),
outputs=[
fl.SurfaceOutput(
name="Surface output",
output_fields=["Cp", "yPlus", "Cf", "CfVec"],
surfaces=[geometry["*"]],
),
fl.SliceOutput(
name="Slice output", output_fields=["Cp", "Mach", "vorticity"], slices=[*slices]
),
],
)


project.run_case(params, name="BET eVTOL case")
84 changes: 84 additions & 0 deletions examples/advanced_simulations/rotorcraft/isolated_propeller.py
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import flow360 as fl
from flow360.examples import IsolatedPropeller

IsolatedPropeller.get_files()

project = fl.Project.from_geometry(IsolatedPropeller.geometry, name="Isolated Propeller")

geometry = project.geometry
geometry.group_edges_by_tag("edgeId")
geometry.group_faces_by_tag("faceName")


with fl.SI_unit_system:
rotating_cylinder = fl.Cylinder(
name="Rotating zone", center=[0, 0, 0], axis=[1, 0, 0], outer_radius=2, height=0.8
)
refinement_cylinder = fl.Cylinder(
name="Refinement zone", center=[1.9, 0, 0], axis=[1, 0, 0], outer_radius=2, height=4
)
slice = fl.Slice(name="Slice", normal=[1, 0, 0], origin=[0.6, 0, 0])
volume_zone_rotating_cylinder = fl.RotationCylinder(
name="Rotation cylinder",
spacing_axial=0.05,
spacing_radial=0.05,
spacing_circumferential=0.05,
entities=[rotating_cylinder],
enclosed_entities=[geometry["*"]],
)
farfield = fl.AutomatedFarfield(name="Farfield")
params = fl.SimulationParams(
meshing=fl.MeshingParams(
defaults=fl.MeshingDefaults(
surface_max_edge_length=1, boundary_layer_first_layer_thickness=0.1 * fl.u.mm
),
refinements=[
fl.UniformRefinement(
name="Uniform refinement", spacing=0.025, entities=[refinement_cylinder]
)
],
volume_zones=[farfield, volume_zone_rotating_cylinder],
),
reference_geometry=fl.ReferenceGeometry(
area=1, moment_center=[0, 0, 0], moment_length=[1, 1, 1]
),
operating_condition=fl.AerospaceCondition(velocity_magnitude=20),
models=[
fl.Wall(name="Wall", surfaces=[geometry["*"]]),
fl.Freestream(name="Freestream", surfaces=[farfield.farfield]),
fl.Fluid(
navier_stokes_solver=fl.NavierStokesSolver(relative_tolerance=0.01),
turbulence_model_solver=fl.SpalartAllmaras(
relative_tolerance=0.01, hybrid_model=fl.DetachedEddySimulation()
),
),
fl.Rotation(
name="Rotation",
volumes=[rotating_cylinder],
spec=fl.AngularVelocity(value=200 * fl.u.rpm),
),
],
time_stepping=fl.Unsteady(
steps=600,
step_size=0.0025,
max_pseudo_steps=35,
CFL=fl.AdaptiveCFL(
min=0.1, max=10000, max_relative_change=1, convergence_limiting_factor=0.5
),
),
outputs=[
fl.SurfaceOutput(
name="Surface output",
output_fields=["Cp", "yPlus", "Cf", "CfVec"],
surfaces=[geometry["*"]],
),
fl.SliceOutput(
name="Slice output",
output_fields=["qcriterion", "vorticity", "Mach"],
slices=[slice],
),
],
)


project.run_case(params, name="Isolated propeller case")
4 changes: 4 additions & 0 deletions flow360/examples/__init__.py
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@@ -1,12 +1,14 @@
from .actuator_disk import ActuatorDisk
from .airplane import Airplane
from .bet_evtol import BETEVTOL
from .bet_example_data import BETExampleData
from .bet_line import BETLine
from .convergence import Convergence
from .cylinder2D import Cylinder2D
from .cylinder3D import Cylinder3D
from .drivaer import DrivAer
from .evtol import EVTOL
from .isolated_propeller import IsolatedPropeller
from .monitors import MonitorsAndSlices
from .om6wing import OM6wing
from .quadcopter import Quadcopter
Expand All @@ -25,13 +27,15 @@
__all__ = [
"ActuatorDisk",
"Airplane",
"BETEVTOL",
"BETExampleData",
"BETLine",
"Convergence",
"Cylinder2D",
"Cylinder3D",
"DrivAer",
"EVTOL",
"IsolatedPropeller",
"MonitorsAndSlices",
"OM6wing",
"RotatingSpheres",
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