"""Initialization of CL vector."""
# This file is part of FAST-OAD_CS25
# Copyright (C) 2022 ONERA & ISAE-SUPAERO
# FAST is free software: you can redistribute it and/or modify
# it under the terms of the GNU General Public License as published by
# the Free Software Foundation, either version 3 of the License, or
# (at your option) any later version.
# This program is distributed in the hope that it will be useful,
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
# You should have received a copy of the GNU General Public License
# along with this program. If not, see <https://www.gnu.org/licenses/>.
import fastoad.api as oad
import numpy as np
import openmdao.api as om
from ..constants import POLAR_POINT_COUNT, SERVICE_INITIALIZE_CL
[docs]
@oad.RegisterSubmodel(SERVICE_INITIALIZE_CL, "fastoad.submodel.aerodynamics.initialize_CL.legacy")
class InitializeClPolar(om.ExplicitComponent):
"""Initialization of CL vector."""
[docs]
def initialize(self):
self.options.declare("low_speed_aero", default=False, types=bool)
[docs]
def setup(self):
self.add_input("tuning:aerodynamics:aircraft:high_speed:CL:k", val=np.nan, units="unitless")
self.add_input(
"tuning:aerodynamics:aircraft:high_speed:CL:offset", val=np.nan, units="unitless"
)
self.add_input(
"tuning:aerodynamics:aircraft:high_speed:CL:winglet_effect:k",
val=np.nan,
units="unitless",
)
self.add_input(
"tuning:aerodynamics:aircraft:high_speed:CL:winglet_effect:offset",
val=np.nan,
units="unitless",
)
if self.options["low_speed_aero"]:
self.add_output(
"data:aerodynamics:aircraft:low_speed:CL", shape=POLAR_POINT_COUNT, units="unitless"
)
else:
self.add_output(
"data:aerodynamics:aircraft:high_speed:CL",
shape=POLAR_POINT_COUNT,
units="unitless",
)
[docs]
def setup_partials(self):
self.declare_partials("*", "*", method="fd")
[docs]
def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
k_cl = inputs["tuning:aerodynamics:aircraft:high_speed:CL:k"]
offset_cl = inputs["tuning:aerodynamics:aircraft:high_speed:CL:offset"]
k_winglet_cl = inputs["tuning:aerodynamics:aircraft:high_speed:CL:winglet_effect:k"]
offset_winglet_cl = inputs[
"tuning:aerodynamics:aircraft:high_speed:CL:winglet_effect:offset"
]
# FIXME: initialization of CL range should be done more directly, without these coefficients
cl = np.arange(0.0, 1.5, 0.01) * k_cl * k_winglet_cl + offset_cl + offset_winglet_cl
if self.options["low_speed_aero"]:
outputs["data:aerodynamics:aircraft:low_speed:CL"] = cl
else:
outputs["data:aerodynamics:aircraft:high_speed:CL"] = cl