"""
Estimation of wing sweeps
"""
# 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 ComputeSweepWing(ExplicitComponent):
# TODO: Document equations. Cite sources
""" Wing sweeps estimation """
[docs] def setup(self):
self.add_input("data:geometry:wing:kink:leading_edge:x:local", val=np.nan, units="m")
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:kink: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:chord", val=np.nan, units="m")
self.add_input("data:geometry:wing:kink:chord", val=np.nan, units="m")
self.add_input("data:geometry:wing:tip:chord", val=np.nan, units="m")
self.add_output("data:geometry:wing:sweep_0", units="deg")
self.add_output("data:geometry:wing:sweep_100_inner", units="deg")
self.add_output("data:geometry:wing:sweep_100_outer", units="deg")
[docs] def setup_partials(self):
self.declare_partials(
"data:geometry:wing:sweep_0",
[
"data:geometry:wing:kink:leading_edge:x:local",
"data:geometry:wing:root:y",
"data:geometry:wing:kink:y",
],
method="fd",
)
self.declare_partials(
"data:geometry:wing:sweep_100_inner",
[
"data:geometry:wing:kink:leading_edge:x:local",
"data:geometry:wing:root:chord",
"data:geometry:wing:root:y",
"data:geometry:wing:kink:y",
"data:geometry:wing:kink:chord",
],
method="fd",
)
self.declare_partials(
"data:geometry:wing:sweep_100_outer",
[
"data:geometry:wing:kink:leading_edge:x:local",
"data:geometry:wing:tip:leading_edge:x:local",
"data:geometry:wing:kink:y",
"data:geometry:wing:tip:y",
"data:geometry:wing:kink:chord",
"data:geometry:wing:tip:chord",
],
method="fd",
)
[docs] def compute(self, inputs, outputs):
x3_wing = inputs["data:geometry:wing:kink:leading_edge:x:local"]
x4_wing = inputs["data:geometry:wing:tip:leading_edge:x:local"]
y2_wing = inputs["data:geometry:wing:root:y"]
y3_wing = inputs["data:geometry:wing:kink:y"]
y4_wing = inputs["data:geometry:wing:tip:y"]
l2_wing = inputs["data:geometry:wing:root:chord"]
l3_wing = inputs["data:geometry:wing:kink:chord"]
l4_wing = inputs["data:geometry:wing:tip:chord"]
outputs["data:geometry:wing:sweep_0"] = (
math.atan(x3_wing / (y3_wing - y2_wing)) / math.pi * 180.0
)
outputs["data:geometry:wing:sweep_100_inner"] = (
math.atan((x3_wing + l3_wing - l2_wing) / (y3_wing - y2_wing)) / math.pi * 180
)
outputs["data:geometry:wing:sweep_100_outer"] = (
math.atan((x4_wing + l4_wing - x3_wing - l3_wing) / (y4_wing - y3_wing))
/ math.pi
* 180.0
)