"""
FAST - Copyright (c) 2016 ONERA ISAE
"""
# This file is part of FAST-OAD : A framework for rapid Overall Aircraft Design
# Copyright (C) 2021 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 openmdao.api as om
from fastoad.module_management.constants import ModelDomain
from fastoad.module_management.service_registry import RegisterOpenMDAOSystem
from .components.cd0_fuselage import Cd0Fuselage
from .components.cd0_ht import Cd0HorizontalTail
from .components.cd0_nacelle_pylons import Cd0NacelleAndPylons
from .components.cd0_total import Cd0Total
from .components.cd0_vt import Cd0VerticalTail
from .components.cd0_wing import Cd0Wing
from .components.cd_trim import CdTrim
from .components.compute_low_speed_aero import ComputeAerodynamicsLowSpeed
from .components.compute_polar import ComputePolar, PolarType
from .components.compute_reynolds import ComputeReynolds
from .components.initialize_cl import InitializeClPolar
from .components.oswald import OswaldCoefficient
[docs]@RegisterOpenMDAOSystem("fastoad.aerodynamics.lowspeed.legacy", domain=ModelDomain.AERODYNAMICS)
class AerodynamicsLowSpeed(om.Group):
"""
Models for low speed aerodynamics
"""
[docs] def setup(self):
self.add_subsystem("compute_low_speed_aero", ComputeAerodynamicsLowSpeed(), promotes=["*"])
ivc = om.IndepVarComp("data:aerodynamics:aircraft:takeoff:mach", val=0.2)
self.add_subsystem("mach_low_speed", ivc, promotes=["*"])
self.add_subsystem(
"compute_oswald_coeff", OswaldCoefficient(low_speed_aero=True), promotes=["*"]
)
self.add_subsystem("comp_re", ComputeReynolds(low_speed_aero=True), promotes=["*"])
self.add_subsystem("initialize_cl", InitializeClPolar(low_speed_aero=True), promotes=["*"])
self.add_subsystem("cd0_wing", Cd0Wing(low_speed_aero=True), promotes=["*"])
self.add_subsystem("cd0_fuselage", Cd0Fuselage(low_speed_aero=True), promotes=["*"])
self.add_subsystem("cd0_ht", Cd0HorizontalTail(low_speed_aero=True), promotes=["*"])
self.add_subsystem("cd0_vt", Cd0VerticalTail(low_speed_aero=True), promotes=["*"])
self.add_subsystem(
"cd0_nac_pylons", Cd0NacelleAndPylons(low_speed_aero=True), promotes=["*"]
)
self.add_subsystem("cd0_total", Cd0Total(low_speed_aero=True), promotes=["*"])
self.add_subsystem("cd_trim", CdTrim(low_speed_aero=True), promotes=["*"])
self.add_subsystem("get_polar", ComputePolar(type=PolarType.LOW_SPEED), promotes=["*"])