From 225f641131790c49b87d0639c59ccfeb5b082de7 Mon Sep 17 00:00:00 2001 From: Xun Jiang Date: Fri, 10 Jan 2025 14:08:03 -0800 Subject: [PATCH] remove a few vals --- aviary/subsystems/mass/gasp_based/design_load.py | 2 +- aviary/subsystems/mass/gasp_based/fixed.py | 2 +- aviary/subsystems/mass/gasp_based/fuel.py | 8 ++++---- 3 files changed, 6 insertions(+), 6 deletions(-) diff --git a/aviary/subsystems/mass/gasp_based/design_load.py b/aviary/subsystems/mass/gasp_based/design_load.py index 9ee38682f..4ae47d870 100644 --- a/aviary/subsystems/mass/gasp_based/design_load.py +++ b/aviary/subsystems/mass/gasp_based/design_load.py @@ -616,7 +616,7 @@ def setup(self): add_aviary_input(self, Aircraft.Wing.SWEEP, units="rad") add_aviary_input(self, Mission.Design.MACH) - add_aviary_output(self, Aircraft.Design.LIFT_CURVE_SLOPE, val=7.1765) + add_aviary_output(self, Aircraft.Design.LIFT_CURVE_SLOPE) self.declare_partials(Aircraft.Design.LIFT_CURVE_SLOPE, "*") diff --git a/aviary/subsystems/mass/gasp_based/fixed.py b/aviary/subsystems/mass/gasp_based/fixed.py index 224e9113b..cfb170e9d 100644 --- a/aviary/subsystems/mass/gasp_based/fixed.py +++ b/aviary/subsystems/mass/gasp_based/fixed.py @@ -535,7 +535,7 @@ def setup(self): add_aviary_output(self, Aircraft.Nacelle.MASS, shape=num_engine_type) self.add_output('pylon_mass', units='lbm', desc='WPYLON: mass of each pylon', val=np.zeros(num_engine_type)) - add_aviary_output(self, Aircraft.Propulsion.TOTAL_ENGINE_POD_MASS, val=0) + add_aviary_output(self, Aircraft.Propulsion.TOTAL_ENGINE_POD_MASS) add_aviary_output(self, Aircraft.Engine.ADDITIONAL_MASS, shape=num_engine_type) self.add_output("eng_comb_mass", val=0, units="lbm", diff --git a/aviary/subsystems/mass/gasp_based/fuel.py b/aviary/subsystems/mass/gasp_based/fuel.py index 6ef437e89..79bede620 100644 --- a/aviary/subsystems/mass/gasp_based/fuel.py +++ b/aviary/subsystems/mass/gasp_based/fuel.py @@ -337,7 +337,7 @@ class FuelAndOEMOutputs(om.ExplicitComponent): def setup(self): - add_aviary_input(self, Aircraft.Fuel.DENSITY, val=6.687, units="lbm/ft**3") + add_aviary_input(self, Aircraft.Fuel.DENSITY, units="lbm/ft**3") add_aviary_input(self, Mission.Design.GROSS_MASS) add_aviary_input(self, Aircraft.Propulsion.MASS) add_aviary_input(self, Aircraft.Controls.TOTAL_MASS) @@ -823,10 +823,10 @@ def setup(self): self.add_input("fus_mass_full", val=4000, units="lbm", desc="WX: mass of fuselage and contents, including empennage") - add_aviary_input(self, Aircraft.Fuselage.MASS_COEFFICIENT, val=128) - add_aviary_input(self, Aircraft.Fuselage.WETTED_AREA, val=4000) + add_aviary_input(self, Aircraft.Fuselage.MASS_COEFFICIENT) + add_aviary_input(self, Aircraft.Fuselage.WETTED_AREA) add_aviary_input(self, Aircraft.Fuselage.AVG_DIAMETER) - add_aviary_input(self, Aircraft.TailBoom.LENGTH, val=129.4) + add_aviary_input(self, Aircraft.TailBoom.LENGTH) self.add_input("pylon_len", val=0, units="ft", desc="ELRW: length of pylon for fuselage mounted engines") self.add_input("min_dive_vel", val=419.75918333, units="kn",