From c28aabe34e19f3a9f11c22b408da3d0ae47e0d48 Mon Sep 17 00:00:00 2001 From: Xun Jiang Date: Wed, 8 Jan 2025 13:48:02 -0800 Subject: [PATCH] autopep8 --- .../subsystems/mass/flops_based/test/test_engine.py | 3 ++- aviary/subsystems/mass/gasp_based/fuel.py | 3 ++- aviary/subsystems/mass/gasp_based/mass_premission.py | 6 ------ aviary/subsystems/mass/gasp_based/test/test_fixed.py | 12 ++++++++---- 4 files changed, 12 insertions(+), 12 deletions(-) diff --git a/aviary/subsystems/mass/flops_based/test/test_engine.py b/aviary/subsystems/mass/flops_based/test/test_engine.py index c510b8d7d..b03c90f63 100644 --- a/aviary/subsystems/mass/flops_based/test/test_engine.py +++ b/aviary/subsystems/mass/flops_based/test/test_engine.py @@ -38,7 +38,8 @@ def test_case(self, case_name): prob.model_options['*'] = get_flops_options(case_name, preprocess=True) prob.setup(check=False, force_alloc_complex=True) - prob.set_val(Aircraft.Engine.MASS_SCALER, val=np.zeros(1)) # TODO: should we test MASS_SCALER = 1? + # TODO: should we test MASS_SCALER = 1? + prob.set_val(Aircraft.Engine.MASS_SCALER, val=np.zeros(1)) flops_validation_test( prob, diff --git a/aviary/subsystems/mass/gasp_based/fuel.py b/aviary/subsystems/mass/gasp_based/fuel.py index 7cad3c3cc..6ef437e89 100644 --- a/aviary/subsystems/mass/gasp_based/fuel.py +++ b/aviary/subsystems/mass/gasp_based/fuel.py @@ -1150,7 +1150,8 @@ def setup(self): add_aviary_input(self, Aircraft.Controls.TOTAL_MASS) add_aviary_input(self, Aircraft.Design.FIXED_EQUIPMENT_MASS) add_aviary_input(self, Aircraft.Design.FIXED_USEFUL_LOAD) - self.add_input("payload_mass_des", val=36000, units="lbm", desc="WPLDES: design payload") + self.add_input("payload_mass_des", val=36000, units="lbm", + desc="WPLDES: design payload") add_aviary_input(self, Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER) add_aviary_input(self, Aircraft.Fuel.FUEL_SYSTEM_MASS_COEFFICIENT) add_aviary_input(self, Aircraft.Fuel.DENSITY) diff --git a/aviary/subsystems/mass/gasp_based/mass_premission.py b/aviary/subsystems/mass/gasp_based/mass_premission.py index bdae3a35a..d6a36a94d 100644 --- a/aviary/subsystems/mass/gasp_based/mass_premission.py +++ b/aviary/subsystems/mass/gasp_based/mass_premission.py @@ -6,8 +6,6 @@ from aviary.subsystems.mass.gasp_based.fixed import FixedMassGroup from aviary.subsystems.mass.gasp_based.fuel import FuelMassGroup from aviary.subsystems.mass.gasp_based.wing import WingMassGroup -from aviary.variable_info.variables import Aircraft - class MassPremission(om.Group): @@ -91,7 +89,3 @@ def setup(self): "aircraft:*", "mission:*" ], ) - - #self.set_input_defaults(Aircraft.Fuselage.LENGTH, 200, 'ft') - #self.set_input_defaults(Aircraft.HorizontalTail.AREA, 20, 'ft**2') - #self.set_input_defaults(Aircraft.VerticalTail.AREA, 20, 'ft**2') diff --git a/aviary/subsystems/mass/gasp_based/test/test_fixed.py b/aviary/subsystems/mass/gasp_based/test/test_fixed.py index 73aa3489e..6f99b3284 100644 --- a/aviary/subsystems/mass/gasp_based/test/test_fixed.py +++ b/aviary/subsystems/mass/gasp_based/test/test_fixed.py @@ -970,8 +970,10 @@ def test_case1(self): self.prob.model.set_input_defaults( Aircraft.Nacelle.AVG_DIAMETER, val=[7.5, 8.22], units='ft' ) - self.prob.model.set_input_defaults(Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04) - self.prob.model.set_input_defaults(Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MASS_COEFFICIENT, val=0.04) + self.prob.model.set_input_defaults( + Aircraft.LandingGear.MAIN_GEAR_MASS_COEFFICIENT, val=0.85) self.prob.model.set_input_defaults(Mission.Design.GROSS_MASS, val=152000) self.prob.model_options['*'] = extract_options(options) @@ -1170,7 +1172,8 @@ def setUp(self): self.prob.model.set_input_defaults(Aircraft.Wing.FLAP_CHORD_RATIO, val=.3) self.prob.model.set_input_defaults(Aircraft.Wing.SLAT_SPAN_RATIO, val=.9) self.prob.model.set_input_defaults(Aircraft.Wing.LOADING, val=128) - self.prob.model.set_input_defaults(Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=.15) + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=.15) self.prob.model.set_input_defaults(Aircraft.Wing.CENTER_CHORD, val=17.48974) setup_model_options(self.prob, options) @@ -1483,7 +1486,8 @@ def setUp(self): self.prob.model.set_input_defaults(Aircraft.Wing.FLAP_CHORD_RATIO, val=.3) self.prob.model.set_input_defaults(Aircraft.Wing.SLAT_SPAN_RATIO, val=.9) self.prob.model.set_input_defaults(Aircraft.Wing.LOADING, val=128) - self.prob.model.set_input_defaults(Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=.15) + self.prob.model.set_input_defaults( + Aircraft.Wing.THICKNESS_TO_CHORD_ROOT, val=.15) self.prob.model.set_input_defaults(Aircraft.Wing.CENTER_CHORD, val=17.48974) setup_model_options(self.prob, options)