autopep8

OpenMDAO · Jan 8, 2025 · c28aabe · c28aabe
1 parent 8100368
commit c28aabe
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Showing 4 changed files with 12 additions and 12 deletions.
diff --git 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
@@ -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
@@ -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
@@ -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)