"""
Estimation of total aircraft wet area
"""
# 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
[docs]class ComputeTotalArea(ExplicitComponent):
# TODO: Document equations. Cite sources
""" Total aircraft wet area estimation """
[docs] def setup(self):
self.add_input("data:geometry:wing:wetted_area", val=np.nan, units="m**2")
self.add_input("data:geometry:fuselage:wetted_area", val=np.nan, units="m**2")
self.add_input("data:geometry:horizontal_tail:wetted_area", val=np.nan, units="m**2")
self.add_input("data:geometry:vertical_tail:wetted_area", val=np.nan, units="m**2")
self.add_input("data:geometry:propulsion:nacelle:wetted_area", val=np.nan, units="m**2")
self.add_input("data:geometry:propulsion:pylon:wetted_area", val=np.nan, units="m**2")
self.add_input("data:geometry:propulsion:engine:count", val=np.nan)
self.add_output("data:geometry:aircraft:wetted_area", units="m**2")
[docs] def setup_partials(self):
self.declare_partials("data:geometry:aircraft:wetted_area", "*", method="fd")
[docs] def compute(self, inputs, outputs):
wet_area_wing = inputs["data:geometry:wing:wetted_area"]
wet_area_fus = inputs["data:geometry:fuselage:wetted_area"]
wet_area_ht = inputs["data:geometry:horizontal_tail:wetted_area"]
wet_area_vt = inputs["data:geometry:vertical_tail:wetted_area"]
wet_area_nac = inputs["data:geometry:propulsion:nacelle:wetted_area"]
wet_area_pylon = inputs["data:geometry:propulsion:pylon:wetted_area"]
n_engines = inputs["data:geometry:propulsion:engine:count"]
wet_area_total = (
wet_area_wing
+ wet_area_fus
+ wet_area_ht
+ wet_area_vt
+ n_engines * (wet_area_nac + wet_area_pylon)
)
outputs["data:geometry:aircraft:wetted_area"] = wet_area_total