"""
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 numpy as np
from openmdao.core.explicitcomponent import ExplicitComponent
from fastoad.models.aerodynamics.constants import POLAR_POINT_COUNT
[docs]class InitializeClPolar(ExplicitComponent):
[docs] def initialize(self):
self.options.declare("low_speed_aero", default=False, types=bool)
[docs] def setup(self):
self.low_speed_aero = self.options["low_speed_aero"]
self.add_input("tuning:aerodynamics:aircraft:cruise:CL:k", val=np.nan)
self.add_input("tuning:aerodynamics:aircraft:cruise:CL:offset", val=np.nan)
self.add_input("tuning:aerodynamics:aircraft:cruise:CL:winglet_effect:k", val=np.nan)
self.add_input("tuning:aerodynamics:aircraft:cruise:CL:winglet_effect:offset", val=np.nan)
if self.low_speed_aero:
self.add_output("data:aerodynamics:aircraft:low_speed:CL", shape=POLAR_POINT_COUNT)
else:
self.add_output("data:aerodynamics:aircraft:cruise:CL", shape=POLAR_POINT_COUNT)
[docs] def setup_partials(self):
self.declare_partials("*", "*", method="fd")
[docs] def compute(self, inputs, outputs):
k_cl = inputs["tuning:aerodynamics:aircraft:cruise:CL:k"]
offset_cl = inputs["tuning:aerodynamics:aircraft:cruise:CL:offset"]
k_winglet_cl = inputs["tuning:aerodynamics:aircraft:cruise:CL:winglet_effect:k"]
offset_winglet_cl = inputs["tuning:aerodynamics:aircraft:cruise: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.low_speed_aero:
outputs["data:aerodynamics:aircraft:low_speed:CL"] = cl
else:
outputs["data:aerodynamics:aircraft:cruise:CL"] = cl