"""Computation of form drag for Vertical Tail Plane."""
# This file is part of FAST-OAD_CS25
# Copyright (C) 2024 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 fastoad.api as oad
import numpy as np
import openmdao.api as om
from .utils.cd0_lifting_surface import (
LiftingSurfaceGeometry,
compute_cd0_lifting_surface,
)
from ..constants import SERVICE_CD0_VERTICAL_TAIL
[docs]
@oad.RegisterSubmodel(
SERVICE_CD0_VERTICAL_TAIL, "fastoad.submodel.aerodynamics.CD0.vertical_tail.legacy"
)
class Cd0VerticalTail(om.ExplicitComponent):
"""
Computation of form drag for Vertical Tail Plane.
See :meth:`~fastoad_cs25.models.aerodynamics.components.utils.cd0_lifting_surface`
for used method.
"""
[docs]
def initialize(self):
self.options.declare("low_speed_aero", default=False, types=bool)
[docs]
def setup(self):
self.add_input("data:geometry:vertical_tail:MAC:length", val=np.nan, units="m")
self.add_input("data:geometry:vertical_tail:thickness_ratio", val=np.nan, units="unitless")
self.add_input("data:geometry:vertical_tail:sweep_25", val=np.nan, units="deg")
self.add_input("data:geometry:vertical_tail:wetted_area", val=np.nan, units="m**2")
self.add_input("data:geometry:wing:area", val=np.nan, units="m**2")
if self.options["low_speed_aero"]:
self.add_input(
"data:aerodynamics:aircraft:low_speed:unit_reynolds", val=np.nan, units="unitless"
)
self.add_input("data:aerodynamics:aircraft:takeoff:mach", val=np.nan, units="unitless")
self.add_output("data:aerodynamics:vertical_tail:low_speed:CD:CD0", units="unitless")
else:
self.add_input(
"data:aerodynamics:aircraft:high_speed:unit_reynolds", val=np.nan, units="unitless"
)
self.add_input("data:TLAR:cruise_mach", val=np.nan, units="unitless")
self.add_output("data:aerodynamics:vertical_tail:high_speed:CD:CD0", units="unitless")
[docs]
def setup_partials(self):
self.declare_partials("*", "*", method="fd")
[docs]
def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
vt_geometry = LiftingSurfaceGeometry(
thickness_ratio=inputs["data:geometry:vertical_tail:thickness_ratio"],
MAC_length=inputs["data:geometry:vertical_tail:MAC:length"],
sweep_angle_25=inputs["data:geometry:vertical_tail:sweep_25"],
wet_area=inputs["data:geometry:vertical_tail:wetted_area"],
cambered=False,
interaction_coeff=0.005,
)
wing_area = inputs["data:geometry:wing:area"]
if self.options["low_speed_aero"]:
mach = inputs["data:aerodynamics:aircraft:takeoff:mach"]
reynolds = inputs["data:aerodynamics:aircraft:low_speed:unit_reynolds"]
else:
mach = inputs["data:TLAR:cruise_mach"]
reynolds = inputs["data:aerodynamics:aircraft:high_speed:unit_reynolds"]
cd0_vt = compute_cd0_lifting_surface(vt_geometry, mach, reynolds, wing_area)
if self.options["low_speed_aero"]:
outputs["data:aerodynamics:vertical_tail:low_speed:CD:CD0"] = cd0_vt
else:
outputs["data:aerodynamics:vertical_tail:high_speed:CD:CD0"] = cd0_vt