OpenMDAO · jkirk5 · Jun 29, 2026 · Jun 5, 2026 · Jun 5, 2026 · Jun 9, 2026
diff --git a/aviary/core/aviary_group.py b/aviary/core/aviary_group.py
@@ -295,7 +295,7 @@ def load_inputs(
         ## LOAD PHASE_INFO ###
         # if phase info is a file, load it
         if isinstance(phase_info, str) or isinstance(phase_info, Path):
-            phase_info_path = get_path(phase_info)
+            phase_info_path = get_path(phase_info, verbosity)
             spec = spec_from_file_location('phase_info_file', str(phase_info_path))
             phase_info_file = module_from_spec(spec)
             sys.modules['phase_info_file'] = phase_info_file

diff --git a/aviary/core/aviary_problem.py b/aviary/core/aviary_problem.py
@@ -2156,7 +2156,7 @@ def reload_aviary_problem(
     # Initialize a new aviary problem and aviary_input data structure
     prob = AviaryProblem()
 
-    filename = get_path(filename)
+    filename = get_path(filename, verbosity)
 
     aviary_inputs = _read_sizing_json(filename, metadata, verbosity)
 

diff --git a/aviary/docs/user_guide_unreviewed/aviary_commands.ipynb b/aviary/docs/user_guide_unreviewed/aviary_commands.ipynb
@@ -140,7 +140,9 @@
     "{glue:md}`aviary run_mission models/aircraft/small_single_aisle/small_single_aisle_GASP.csv` in\n",
     "{glue:md}`aviary/models/aircraft/small_single_aisle`\n",
     "\n",
-    "SNOPT is the default optimizer, but IPOPT is available as well."
+    "SNOPT is the default optimizer, but IPOPT is available as well.\n",
+    "\n",
+    "Note: Do not use the test models in `validation_cases/validation_data/test_models`. They are for testing purpose only."
    ]
   },
   {

diff --git a/aviary/interface/run_aviary.py b/aviary/interface/run_aviary.py
@@ -144,7 +144,7 @@ def run_aviary_cmd(
     }
 
     if isinstance(phase_info, str):
-        phase_info_path = get_path(phase_info)
+        phase_info_path = get_path(phase_info, verbosity)
         spec = spec_from_file_location('phase_info_file', str(phase_info_path))
         phase_info_file = module_from_spec(spec)
         sys.modules['phase_info_file'] = phase_info_file

diff --git a/aviary/interface/test/test_interface_bugs.py b/aviary/interface/test/test_interface_bugs.py
@@ -10,13 +10,14 @@
 )
 from aviary.subsystems.subsystem_builder import SubsystemBuilder
 from aviary.utils.functions import get_aviary_resource_path
+from aviary.variable_info.functions import add_aviary_input, add_aviary_output
 from aviary.variable_info.variables import Aircraft
 
 
 class WingWeightSubsys(om.ExplicitComponent):
     def setup(self):
-        self.add_input(Aircraft.Engine.MASS, 1.0, units='lbm')
-        self.add_output(Aircraft.Canard.ASPECT_RATIO, 1.0, units='unitless')
+        add_aviary_input(self, Aircraft.Engine.MASS, 1.0, units='lbm')
+        add_aviary_output(self, Aircraft.Canard.ASPECT_RATIO, 1.0, units='unitless')
         self.add_output('Tail', 1.0, units='unitless')
 
         self.declare_partials(Aircraft.Canard.ASPECT_RATIO, Aircraft.Engine.MASS, val=2.0)

diff --git a/aviary/interface/test/test_shape_by_conn.py b/aviary/interface/test/test_shape_by_conn.py
@@ -108,7 +108,9 @@ def test_shape_bug_two(self):
 
         class PostComponent(om.ExplicitComponent):
             def setup(self):
-                self.add_input(Aircraft.Design.DRAG_POLAR, shape_by_conn=True, units='unitless')
+                add_aviary_input(
+                    self, Aircraft.Design.DRAG_POLAR, shape_by_conn=True, units='unitless'
+                )
                 add_aviary_input(
                     self, Aircraft.Design.LIFT_POLAR, shape_by_conn=True, units='unitless'
                 )

diff --git a/aviary/mission/energy_state/ode/landing_eom.py b/aviary/mission/energy_state/ode/landing_eom.py
@@ -164,7 +164,7 @@ def setup(self):
         add_aviary_input(self, Dynamic.Vehicle.LIFT, val=np.ones(nn), units='N')
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
+        add_aviary_input(self, Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad')
 
@@ -322,7 +322,7 @@ def setup(self):
         add_aviary_input(self, Dynamic.Vehicle.Propulsion.THRUST_TOTAL, val=np.ones(nn), units='N')
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
+        add_aviary_input(self, Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad')
 

diff --git a/aviary/mission/energy_state/ode/range_rate.py b/aviary/mission/energy_state/ode/range_rate.py
@@ -1,5 +1,6 @@
 import numpy as np
 import openmdao.api as om
+from aviary.variable_info.functions import add_aviary_input, add_aviary_output
 
 from aviary.variable_info.variables import Dynamic
 
@@ -16,19 +17,22 @@ def initialize(self):
     def setup(self):
         nn = self.options['num_nodes']
 
-        self.add_input(
+        add_aviary_input(
+            self,
             Dynamic.Mission.ALTITUDE_RATE,
             val=np.ones(nn),
             desc='climb rate',
             units='m/s',
         )
-        self.add_input(
+        add_aviary_input(
+            self,
             Dynamic.Mission.VELOCITY,
             val=np.ones(nn),
             desc='current velocity',
             units='m/s',
         )
-        self.add_output(
+        add_aviary_output(
+            self,
             Dynamic.Mission.DISTANCE_RATE,
             val=np.ones(nn),
             desc='current horizontal velocity (assumed no wind)',

diff --git a/aviary/mission/energy_state/ode/required_thrust.py b/aviary/mission/energy_state/ode/required_thrust.py
@@ -1,5 +1,6 @@
 import numpy as np
 import openmdao.api as om
+from aviary.variable_info.functions import add_aviary_input
 
 from aviary.constants import GRAV_METRIC_FLOPS as gravity
 from aviary.variable_info.variables import Dynamic
@@ -17,27 +18,30 @@ def initialize(self):
     def setup(self):
         nn = self.options['num_nodes']
 
-        self.add_input(Dynamic.Vehicle.DRAG, val=np.zeros(nn), units='N', desc='drag force')
-        self.add_input(
+        add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.zeros(nn), units='N', desc='drag force')
+        add_aviary_input(
+            self,
             Dynamic.Mission.ALTITUDE_RATE,
             val=np.zeros(nn),
             units='m/s',
             desc='rate of change of altitude',
         )
-        self.add_input(
+        add_aviary_input(
+            self,
             Dynamic.Mission.VELOCITY,
             val=np.zeros(nn),
             units='m/s',
             desc=Dynamic.Mission.VELOCITY,
         )
-        self.add_input(
+        add_aviary_input(
+            self,
             Dynamic.Mission.VELOCITY_RATE,
             val=np.zeros(nn),
             units='m/s**2',
             desc='rate of change of velocity',
         )
-        self.add_input(
-            Dynamic.Vehicle.MASS, val=np.zeros(nn), units='kg', desc='mass of the aircraft'
+        add_aviary_input(
+            self, Dynamic.Vehicle.MASS, val=np.zeros(nn), units='kg', desc='mass of the aircraft'
         )
         self.add_output('thrust_required', val=np.zeros(nn), units='N', desc='required thrust')
 

diff --git a/aviary/mission/energy_state/ode/takeoff_eom.py b/aviary/mission/energy_state/ode/takeoff_eom.py
@@ -544,7 +544,7 @@ def setup(self):
         add_aviary_input(self, Dynamic.Vehicle.Propulsion.THRUST_TOTAL, val=np.ones(nn), units='N')
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
+        add_aviary_input(self, Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad')
 
@@ -770,7 +770,7 @@ def setup(self):
         add_aviary_input(self, Dynamic.Vehicle.Propulsion.THRUST_TOTAL, val=np.ones(nn), units='N')
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
+        add_aviary_input(self, Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad')
 

diff --git a/aviary/mission/energy_state/ode/test/test_landing_eom.py b/aviary/mission/energy_state/ode/test/test_landing_eom.py
@@ -3,6 +3,7 @@
 import numpy as np
 import openmdao.api as om
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.ode.landing_eom import (
     FlareEOM,
@@ -21,6 +22,7 @@
 from aviary.variable_info.variables import Dynamic
 
 
+@use_tempdirs
 class FlareEOMTest(unittest.TestCase):
     """Test against data of detailed_landing_flare from models/aircraft/advanced_single_aisle/advanced_single_aisle_data.py."""
 
@@ -201,7 +203,4 @@ def test_GroundSumForces(self):
 
 
 if __name__ == '__main__':
-    # unittest.main()
-    test = FlareEOMTest()
-    test.setUp()
-    test.test_case()
+    unittest.main()
diff --git a/aviary/mission/energy_state/ode/test/test_landing_ode.py b/aviary/mission/energy_state/ode/test/test_landing_ode.py
@@ -1,6 +1,7 @@
 import unittest
 
 import openmdao.api as om
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.ode.landing_ode import FlareODE
 from aviary.validation_cases.validation_data.test_data.advanced_single_aisle_data import (
@@ -18,6 +19,7 @@
 from aviary.variable_info.variables import Aircraft, Dynamic
 
 
+@use_tempdirs
 class FlareODETest(unittest.TestCase):
     """Test against data of detailed_landing_flare from models/aircraft/advanced_single_aisle/advanced_single_aisle_data.py."""
 

diff --git a/aviary/mission/energy_state/ode/test/test_mission_eom.py b/aviary/mission/energy_state/ode/test/test_mission_eom.py
@@ -3,12 +3,15 @@
 import numpy as np
 import openmdao.api as om
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
+from openmdao.utils.testing_utils import use_tempdirs
+
 
 from aviary.mission.energy_state.ode.mission_EOM import MissionEOM
 from aviary.utils.test_utils.variable_test import assert_match_varnames
 from aviary.variable_info.variables import Dynamic
 
 
+@use_tempdirs
 class MissionEOMTest(unittest.TestCase):
     """Test energy-method equations of motion."""
 

diff --git a/aviary/mission/energy_state/ode/test/test_range_rate.py b/aviary/mission/energy_state/ode/test/test_range_rate.py
@@ -1,6 +1,7 @@
 import unittest
 
 import openmdao.api as om
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.ode.range_rate import RangeRate
 from aviary.utils.test_utils.variable_test import assert_match_varnames
@@ -9,6 +10,7 @@
 from aviary.variable_info.variables import Dynamic
 
 
+@use_tempdirs
 class RangeRateTest(unittest.TestCase):
     def setUp(self):
         """Test using data from validation_cases/validation_data/flops_data/full_mission_test_data.py."""

diff --git a/aviary/mission/energy_state/ode/test/test_required_thrust.py b/aviary/mission/energy_state/ode/test/test_required_thrust.py
@@ -3,12 +3,14 @@
 import numpy as np
 import openmdao.api as om
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.ode.required_thrust import RequiredThrust
 from aviary.utils.test_utils.variable_test import assert_match_varnames
 from aviary.variable_info.variables import Dynamic
 
 
+@use_tempdirs
 class RequiredThrustTest(unittest.TestCase):
     """Test required thrust."""
 

diff --git a/aviary/mission/energy_state/ode/test/test_takeoff_eom.py b/aviary/mission/energy_state/ode/test/test_takeoff_eom.py
@@ -3,6 +3,7 @@
 import numpy as np
 import openmdao.api as om
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.ode.takeoff_eom import (
     Accelerations,
@@ -27,6 +28,7 @@
 inputs.set_val(Aircraft.Engine.NUM_ENGINES, np.array([2]))
 
 
+@use_tempdirs
 class TakeoffEOMTest(unittest.TestCase):
     """Test detailed takeoff equation of motion."""
 

diff --git a/aviary/mission/energy_state/ode/test/test_takeoff_ode.py b/aviary/mission/energy_state/ode/test/test_takeoff_ode.py
@@ -2,6 +2,7 @@
 from copy import deepcopy
 
 import openmdao.api as om
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.ode.takeoff_ode import TakeoffODE
 from aviary.validation_cases.validation_data.test_data.advanced_single_aisle_data import (
@@ -22,6 +23,7 @@
 takeoff_subsystem_options = deepcopy(takeoff_subsystem_options)
 
 
+@use_tempdirs
 class TakeoffODETest(unittest.TestCase):
     """Test detailed takeoff ODE."""
 

diff --git a/aviary/mission/energy_state/phases/simplified_takeoff.py b/aviary/mission/energy_state/phases/simplified_takeoff.py
@@ -21,7 +21,8 @@ def setup(self):
             desc='mass of the aircraft',
         )
 
-        self.add_input(
+        add_aviary_input(
+            self,
             Dynamic.Atmosphere.DENSITY,
             val=1.225,
             units='kg/m**3',
@@ -105,7 +106,8 @@ def setup(self):
 
         add_aviary_input(self, Mission.Takeoff.FUEL_MASS, val=10.0e3)
 
-        self.add_input(
+        add_aviary_input(
+            self,
             Dynamic.Atmosphere.DENSITY,
             val=1.225,
             units='kg/m**3',

diff --git a/aviary/mission/energy_state/phases/test/test_building_landing.py b/aviary/mission/energy_state/phases/test/test_building_landing.py
@@ -2,11 +2,13 @@
 
 import openmdao.api as om
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.phases.build_landing import Landing
 from aviary.variable_info.variables import Mission
 
 
+@use_tempdirs
 class LandingPhaseTest(unittest.TestCase):
     """Test landing phase builder."""
 

diff --git a/aviary/mission/energy_state/phases/test/test_building_takeoff.py b/aviary/mission/energy_state/phases/test/test_building_takeoff.py
@@ -2,11 +2,13 @@
 
 import openmdao.api as om
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary.mission.energy_state.phases.build_takeoff import Takeoff
 from aviary.variable_info.variables import Aircraft, Mission
 
 
+@use_tempdirs
 class TakeoffPhaseTest(unittest.TestCase):
     """Test takeoff phase builder."""
 

diff --git a/aviary/mission/energy_state/phases/test/test_simplified_landing.py b/aviary/mission/energy_state/phases/test/test_simplified_landing.py
@@ -2,12 +2,14 @@
 
 import openmdao.api as om
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
+from openmdao.utils.testing_utils import use_tempdirs
 
 from aviary import constants
 from aviary.mission.energy_state.phases.simplified_landing import LandingCalc, LandingGroup
 from aviary.variable_info.variables import Aircraft, Dynamic, Mission
 
 
+@use_tempdirs
 class LandingCalcTest(unittest.TestCase):
     """Test computation in LandingCalc class (the simplified landing)."""
 
@@ -77,6 +79,7 @@ def test_case1(self):
         assert_check_partials(partial_data, atol=1e-12, rtol=1e-12)
 
 
+@use_tempdirs
 class LandingGroupTest(unittest.TestCase):
     """Test the computation of LandingGroup."""