Comparison of Om6Wing Test#
V1 Client (old)
1with fl_v1.SI_unit_system:
2 params = fl_v1.Flow360Params(
3 geometry=fl_v1.Geometry(
4 ref_area=0.748844455929999,
5 moment_length=(
6 0.6460682372650963,
7 0.6460682372650963,
8 0.6460682372650963,
9 ),
10 moment_center=(0, 0, 0),
11 mesh_unit=0.8059 * u.m,
12 ),
13 volume_output=fl_v1.VolumeOutput(
14 output_format="paraview",
15 output_fields=[
16 "primitiveVars",
17 "residualNavierStokes",
18 "residualTurbulence",
19 "Mach",
20 ],
21 ),
22 surface_output=fl_v1.SurfaceOutput(
23 output_format="paraview", output_fields=["nuHat"]
24 ),
25 slice_output=fl_v1.SliceOutput(
26 output_format="tecplot",
27 output_fields=[
28 "primitiveVars",
29 "vorticity",
30 "T",
31 "s",
32 "Cp",
33 "mut",
34 "mutRatio",
35 "Mach",
36 ],
37 slices={
38 "sliceName_1": fl_v1.Slice(
39 slice_normal=(0, 1, 0), slice_origin=(0, 0.56413, 0) * u.m
40 )
41 },
42 ),
43 navier_stokes_solver=fl_v1.NavierStokesSolver(
44 absolute_tolerance=1e-10,
45 linear_solver=fl_v1.LinearSolver(max_iterations=25),
46 kappa_MUSCL=-1.0,
47 ),
48 turbulence_model_solver=fl_v1.SpalartAllmaras(
49 absolute_tolerance=1e-8,
50 linear_solver=fl_v1.LinearSolver(max_iterations=15),
51 ),
52 freestream=fl_v1.FreestreamFromMachReynolds(
53 Mach=0.84, Reynolds=14.6e6, temperature=288.15, alpha=3.06, beta=0
54 ),
55 boundaries={
56 "1": fl_v1.NoSlipWall(name="wing"),
57 "2": fl_v1.SlipWall(name="symmetry"),
58 "3": fl_v1.FreestreamBoundary(name="freestream"),
59 },
60 time_stepping=fl_v1.SteadyTimeStepping(
61 max_pseudo_steps=2000,
62 CFL=fl_v1.RampCFL(initial=5, final=200, ramp_steps=40),
63 ),
64 )
V2 Client (new ✅)
1with fl.SI_unit_system:
2 param = fl.SimulationParams(
3 reference_geometry=fl.ReferenceGeometry(
4 area=0.748844455929999,
5 moment_length=0.6460682372650963,
6 moment_center=(0, 0, 0),
7 ),
8 operating_condition=fl.operating_condition_from_mach_reynolds(
9 mach=0.84,
10 reynolds=14.6e6,
11 temperature=288.15,
12 alpha=3.05 * fl.u.deg,
13 beta=0 * fl.u.deg,
14 project_length_unit = 1 * u.m,
15 ),
16 models=[
17 fl.Fluid(
18 navier_stokes_solver=fl.NavierStokesSolver(
19 absolute_tolerance=1e-10,
20 linear_solver=fl.LinearSolver(max_iterations=25),
21 kappa_MUSCL=-1.0,
22 ),
23 turbulence_model_solver=fl.SpalartAllmaras(
24 absolute_tolerance=1e-8,
25 linear_solver=fl.LinearSolver(max_iterations=15),
26 ),
27 ),
28 fl.Wall(name="wing", surfaces=[volume_mesh["1"]]),
29 fl.SlipWall(name="symmetry", entities=[volume_mesh["2"]]),
30 fl.Freestream(name="freestream", entities=[volume_mesh["3"]]),
31 ],
32 time_stepping=fl.Steady(
33 CFL=fl.RampCFL(initial=5, final=200, ramp_steps=40)
34 ),
35 outputs=[
36 fl.VolumeOutput(
37 output_format="paraview",
38 output_fields=[
39 "primitiveVars",
40 "residualNavierStokes",
41 "residualTurbulence",
42 "Mach",
43 ],
44 ),
45 fl.SurfaceOutput(
46 entities=volume_mesh["*"],
47 output_format="paraview",
48 output_fields=["nuHat"],
49 ),
50 fl.SliceOutput(
51 slices=[
52 fl.Slice(
53 name="sliceName_1",
54 normal=(0, 1, 0),
55 origin=(0, 0.56413, 0) * fl.u.m,
56 )
57 ],
58 output_format="tecplot",
59 output_fields=[
60 "primitiveVars",
61 "vorticity",
62 "T",
63 "s",
64 "Cp",
65 "mut",
66 "mutRatio",
67 "Mach",
68 ],
69 ),
70 ],
71 )