"""
Estimation of wing ToC
"""
# 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 math
import numpy as np
from openmdao.core.explicitcomponent import ExplicitComponent
# TODO: computes relative thickness and generates profiles --> decompose
[docs]class ComputeToCWing(ExplicitComponent):
# TODO: Document equations. Cite sources
""" Wing ToC estimation """
[docs] def setup(self):
self.add_input("data:TLAR:cruise_mach", val=np.nan)
self.add_input("data:geometry:wing:sweep_25", val=np.nan, units="deg")
self.add_output("data:geometry:wing:thickness_ratio")
self.add_output("data:geometry:wing:root:thickness_ratio")
self.add_output("data:geometry:wing:kink:thickness_ratio")
self.add_output("data:geometry:wing:tip:thickness_ratio")
[docs] def setup_partials(self):
self.declare_partials("data:geometry:wing:thickness_ratio", "*", method="fd")
self.declare_partials("data:geometry:wing:root:thickness_ratio", "*", method="fd")
self.declare_partials("data:geometry:wing:kink:thickness_ratio", "*", method="fd")
self.declare_partials("data:geometry:wing:tip:thickness_ratio", "*", method="fd")
[docs] def compute(self, inputs, outputs):
cruise_mach = inputs["data:TLAR:cruise_mach"]
sweep_25 = inputs["data:geometry:wing:sweep_25"]
# Relative thickness
el_aero = 0.89 - (cruise_mach + 0.02) * math.sqrt(math.cos(sweep_25 / 180.0 * math.pi))
el_emp = 1.24 * el_aero
el_break = 0.94 * el_aero
el_ext = 0.86 * el_aero
outputs["data:geometry:wing:thickness_ratio"] = el_aero
outputs["data:geometry:wing:root:thickness_ratio"] = el_emp
outputs["data:geometry:wing:kink:thickness_ratio"] = el_break
outputs["data:geometry:wing:tip:thickness_ratio"] = el_ext