Source code for openaerostruct.aerodynamics.total_lift

import openmdao.api as om


[docs] class TotalLift(om.ExplicitComponent): """ Calculate total lift in force units by summing the induced CL with the CL0. Parameters ---------- CL1 : float Induced coefficient of lift (CL) for the lifting surface. Returns ------- CL : float Total coefficient of lift (CL) for the lifting surface. """ def initialize(self): self.options.declare("surface", types=dict) def setup(self): surface = self.options["surface"] self.add_input("CL1", val=1.0) self.add_output("CL", val=1.0, tags=["mphys_result"]) self.CL0 = surface["CL0"] self.declare_partials("CL", "CL1", val=1.0) def compute(self, inputs, outputs): outputs["CL"] = inputs["CL1"] + self.CL0