The code that encounters this error is as below:

##############################################################################################
import numpy as np
from parafoil import TurboRowPassage, TurboStagePassage, TurboMeshParameters
from parafoil import CamberThicknessAirfoil

rotor_airfoil = CamberThicknessAirfoil(
inlet_angle=np.radians(-60),
outlet_angle=np.radians(-51),
upper_thick_prop=[0.015, 0.05, 0.05 , 0.015],
lower_thick_prop=[0.015, 0.05, 0.05, 0.015],
leading_prop=0.5,
trailing_prop=0.5,
chord_length=0.018,
)

stator_airfoil = CamberThicknessAirfoil(
inlet_angle=np.radians(26),
outlet_angle=np.radians(12),
upper_thick_prop=[0.015, 0.05, 0.05 , 0.015],
lower_thick_prop=[0.015, 0.05, 0.05, 0.015],
leading_prop=0.5,
trailing_prop=0.5,
chord_length=0.018,
)

axial_turbo_passage = TurboStagePassage(
inflow_passage=TurboRowPassage(
airfoil=rotor_airfoil,
spacing_to_chord=0.5,
leading_edge_gap_to_chord=1.0,
trailing_edge_gap_to_chord=0.25,
type="camber",
mesh_params=TurboMeshParameters(
airfoil_label="wall1",
bottom_label="periodic1",
top_label="periodic2",
inlet_label="inflow",
outlet_label="outmix",
)
),
outflow_passage=TurboRowPassage(
airfoil=stator_airfoil,
spacing_to_chord=0.5,
leading_edge_gap_to_chord=0.25,
trailing_edge_gap_to_chord=1.0,
type="camber",
mesh_params=TurboMeshParameters(
airfoil_label="wall2",
bottom_label="periodic3",
top_label="periodic4",
inlet_label="inmix",
outlet_label="outflow",
)
)
)

##############################################################################################

from paraflow import run_simulation, get_flasher, SimulationParams, get_frames, display_frame
from paraflow.simulation.su2 import Su2SimulationConfig

flasher = get_flasher("air", "gas")
sim_results = run_simulation(
axial_turbo_passage,
params=SimulationParams(
inlet_total_state=flasher.flash(P=87909, T=276, mach_number=0.4098),
target_outlet_static_state=flasher.flash(P=108932, T=296),
translation=[
np.array([0.0, 266, 0.0]),
None
]
),
working_directory="./simulation_out",
id="1",
auto_delete=True,
verbose=True,
# num_procs=9,
cfg=Su2SimulationConfig(
custom_repo_url= "https://github.com/su2code/SU2/tree/master",
version= "8.0.0"
)
)
sim_results.to_file("./simulation_out/cached.pkl")

sim_results = SimulationResult.from_file("./simulation_out/cached.pkl")

frames = get_frames(
sim_results,
property_names=["Pressure"],
num_pnts=500,
)
display_frame(frames, "Pressure")
sim_results.eval_values.loc[sim_results.eval_values.index[-1], ' "TotTotEff[1]" ']

from su2.

Line 78 TURBO_PERF_KIND: invalid option name. Check current SU2 options in config_template.cfg.

I am not so familiar with the turbomachinery implementation so I hope somebody else will chime in, but this option was deprecated. Maybe have a look at the testcases/turbomachinery folder that we have, there might be a testcase that matches what you would like to do, maybe transonic_stator_2D?

from su2.