Source code for openaerostruct.functionals.total_aero_performance

import openmdao.api as om

from openaerostruct.functionals.moment_coefficient import MomentCoefficient
from openaerostruct.functionals.total_lift_drag import TotalLiftDrag
from openaerostruct.functionals.sum_areas import SumAreas




class TotalAeroPerformance(om.Group):
    """
    Group to contain the total aerodynamic performance components.
    """

    def initialize(self):
        self.options.declare("surfaces", types=list)
        self.options.declare("user_specified_Sref", types=bool)

    def setup(self):
        surfaces = self.options["surfaces"]

        if not self.options["user_specified_Sref"]:
            self.add_subsystem(
                "sum_areas", SumAreas(surfaces=surfaces), promotes_inputs=["*S_ref"], promotes_outputs=["S_ref_total"]
            )

        self.add_subsystem(
            "CL_CD",
            TotalLiftDrag(surfaces=surfaces),
            promotes_inputs=["*CL", "*CD", "*S_ref", "S_ref_total", "rho", "v"],
            promotes_outputs=["CL", "CD", "L", "D"],
        )

        self.add_subsystem(
            "moment",
            MomentCoefficient(surfaces=surfaces),
            promotes_inputs=["v", "cg", "rho", "*S_ref", "*b_pts", "*widths", "*chords", "*sec_forces", "S_ref_total"],
            promotes_outputs=["CM"],
        )