"""Estimation of the 3D maximum lift coefficients for wing and tail."""
# This file is part of FAST-OAD_CS23 : A framework for rapid Overall Aircraft Design
# 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 numpy as np
import openmdao.api as om
import fastoad.api as oad
from fastga.models.aerodynamics.constants import SUBMODEL_CL_EXTREME
[docs]@oad.RegisterSubmodel(
SUBMODEL_CL_EXTREME, "fastga.submodel.aerodynamics.aircraft.extreme_lift_coefficient.legacy"
)
class ComputeAircraftMaxCl(om.ExplicitComponent):
"""
Add high-lift contribution (flaps)
"""
[docs] def setup(self):
self.add_input("data:aerodynamics:wing:low_speed:CL_max_clean", val=np.nan)
self.add_input("data:aerodynamics:flaps:takeoff:CL_max", val=np.nan)
self.add_input("data:aerodynamics:flaps:landing:CL_max", val=np.nan)
self.add_output("data:aerodynamics:aircraft:takeoff:CL_max")
self.add_output("data:aerodynamics:aircraft:landing:CL_max")
self.declare_partials(
"data:aerodynamics:aircraft:takeoff:CL_max",
"data:aerodynamics:wing:low_speed:CL_max_clean",
val=1.0,
)
self.declare_partials(
"data:aerodynamics:aircraft:takeoff:CL_max",
"data:aerodynamics:flaps:takeoff:CL_max",
val=1.0,
)
self.declare_partials(
"data:aerodynamics:aircraft:landing:CL_max",
"data:aerodynamics:wing:low_speed:CL_max_clean",
val=1.0,
)
self.declare_partials(
"data:aerodynamics:aircraft:landing:CL_max",
"data:aerodynamics:flaps:landing:CL_max",
val=1.0,
)
[docs] def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
cl_max_clean = inputs["data:aerodynamics:wing:low_speed:CL_max_clean"]
cl_max_takeoff = cl_max_clean + inputs["data:aerodynamics:flaps:takeoff:CL_max"]
cl_max_landing = cl_max_clean + inputs["data:aerodynamics:flaps:landing:CL_max"]
outputs["data:aerodynamics:aircraft:takeoff:CL_max"] = cl_max_takeoff
outputs["data:aerodynamics:aircraft:landing:CL_max"] = cl_max_landing