"""
Estimation of wing B50
"""
# 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
[docs]class ComputeB50(ExplicitComponent):
# TODO: Document equations. Cite sources
""" Wing B50 estimation """
[docs] def setup(self):
self.add_input("data:geometry:wing:tip:leading_edge:x:local", val=np.nan, units="m")
self.add_input("data:geometry:wing:root:y", val=np.nan, units="m")
self.add_input("data:geometry:wing:tip:y", val=np.nan, units="m")
self.add_input("data:geometry:wing:root:virtual_chord", val=np.nan, units="m")
self.add_input("data:geometry:wing:tip:chord", val=np.nan, units="m")
self.add_input("data:geometry:wing:span", val=np.nan, units="m")
self.add_output("data:geometry:wing:b_50", units="m")
[docs] def setup_partials(self):
self.declare_partials("data:geometry:wing:b_50", "*", method="fd")
[docs] def compute(self, inputs, outputs):
x4_wing = inputs["data:geometry:wing:tip:leading_edge:x:local"]
y2_wing = inputs["data:geometry:wing:root:y"]
y4_wing = inputs["data:geometry:wing:tip:y"]
l1_wing = inputs["data:geometry:wing:root:virtual_chord"]
l4_wing = inputs["data:geometry:wing:tip:chord"]
span = inputs["data:geometry:wing:span"]
sweep_50 = math.atan((x4_wing + l4_wing * 0.5 - 0.5 * l1_wing) / (y4_wing - y2_wing))
b_50 = span / math.cos(sweep_50)
outputs["data:geometry:wing:b_50"] = b_50