text: from __future__ import print_function, division
  import numpy as np
  
  import unittest
  
  from openmdao.api import Problem, Group
  
  from openaerostruct.geometry.geometry_mesh import GeometryMesh
  
  from openaerostruct.utils.testing import run_test
  
  
  class Test(unittest.TestCase):
  
      def test(self):
          surface = {}
          surface['symmetry'] = False
          surface['type'] = 'aero'
          span = 1
          ny = 5
          mesh = np.zeros((2, ny, 3))
          mesh[0, :, 0] = -1.
          mesh[:, :, 1] = np.linspace(0, span, ny)
          surface['mesh'] = mesh
          surface['name'] = 'wing'
          surface['num_y'] = ny
  
          # The way this is currently set up, we don't actually use the values here
          surface['twist_cp'] = np.zeros((5))
          surface['chord_cp'] = np.zeros((5))
          surface['xshear_cp'] = np.zeros((5))
          surface['yshear_cp'] = np.zeros((5))
          surface['zshear_cp'] = np.zeros((5))
  
          surface['span'] = span
          surface['t_over_c_cp'] = np.array([.12])
  
          comp = GeometryMesh(surface=surface)
  
          run_test(self, comp)
  
  
  if __name__ == '__main__':
      unittest.main()
  