added new test files

openaerostruct/aerodynamics/solve_matrix.py

@@ -50,7 +50,6 @@ def solve_nonlinear(self, inputs, outputs):
 
     def linearize(self, inputs, outputs, partials):
         system_size = self.system_size
-
         self.lu = lu_factor(inputs['mtx'])
 
         partials['circulations', 'circulations'] = inputs['mtx'].flatten()

openaerostruct/aerodynamics/tests/test_collocation_points.py

@@ -0,0 +1,17 @@
+import unittest
+
+from openaerostruct.aerodynamics.collocation_points import CollocationPoints
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = CollocationPoints(surfaces=surfaces)
+
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_convert_velocity.py

@@ -0,0 +1,18 @@
+import unittest
+
+from openaerostruct.aerodynamics.convert_velocity import ConvertVelocity
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = ConvertVelocity(surfaces=surfaces)
+
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_eval_velocities.py

@@ -0,0 +1,18 @@
+import unittest
+
+from openaerostruct.aerodynamics.eval_velocities import EvalVelocities
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = EvalVelocities(surfaces=surfaces, eval_name='TestEval', num_eval_points=11)
+
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_functionals.py

@@ -0,0 +1,18 @@
+import unittest
+
+from openaerostruct.aerodynamics.functionals import VLMFunctionals
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = VLMFunctionals(surface=surfaces[0])
+
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_horseshoe_circulations.py

@@ -0,0 +1,17 @@
+import unittest
+
+from openaerostruct.aerodynamics.horseshoe_circulations import HorseshoeCirculations
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = HorseshoeCirculations(surfaces=surfaces)
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_mtx_rhs.py

@@ -0,0 +1,18 @@
+import unittest
+
+from openaerostruct.aerodynamics.mtx_rhs import VLMMtxRHSComp
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = VLMMtxRHSComp(surfaces=surfaces)
+
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_panel_forces.py

@@ -0,0 +1,18 @@
+import unittest
+
+from openaerostruct.aerodynamics.panel_forces import PanelForces
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = PanelForces(surfaces=surfaces)
+
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_panel_forces_surf.py

@@ -0,0 +1,18 @@
+import unittest
+
+from openaerostruct.aerodynamics.panel_forces_surf import PanelForcesSurf
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        comp = PanelForcesSurf(surfaces=surfaces)
+
+        run_test(self, comp)
+
+
+if __name__ == '__main__':
+    unittest.main()

openaerostruct/aerodynamics/tests/test_solve_matrix.py

@@ -0,0 +1,38 @@
+import unittest
+import numpy as np
+
+from openmdao.api import Group, IndepVarComp
+
+from openaerostruct.aerodynamics.solve_matrix import SolveMatrix
+from openaerostruct.utils.testing import run_test, get_default_surfaces
+
+
+class Test(unittest.TestCase):
+
+    def test(self):
+        surfaces = get_default_surfaces()
+
+        group = Group()
+        comp = SolveMatrix(surfaces=surfaces)
+
+        indep_var_comp = IndepVarComp()
+
+        system_size = 0
+        for surface in surfaces:
+            nx = surface['num_x']
+            ny = surface['num_y']
+            system_size += (nx - 1) * (ny - 1)
+
+
+        indep_var_comp.add_output('rhs', val=np.ones((system_size)), units='m/s')
+        indep_var_comp.add_output('mtx', val=np.identity((system_size)), units='1/m')
+
+        group.add_subsystem('indep_var_comp', indep_var_comp, promotes=['*'])
+        group.add_subsystem('solve_matrix', comp, promotes=['*'])
+
+
+        run_test(self, group)
+
+
+if __name__ == '__main__':
+    unittest.main()