old_contents: import pytest
  from wingstructure.structure import section, material, MassAnalysis
  
  
  @pytest.fixture
  def airfoilcoords():
      import numpy as np
  
      # load airfoil coordinates
      return np.loadtxt('docs/usage/FX 61-184.dat', skiprows=1, delimiter=',')
  
  
  def test_structurecreation(airfoilcoords):
      # create material
      amat = material.IsotropicMaterial(1.225, 210e3, 50e3)
  
      # create sectionbase instance
      secbase = section.SectionBase(airfoilcoords)
      
      outerlayer = section.Layer(secbase, amat, thickness=0.001)
      innerlayer = section.Layer(outerlayer, amat, thickness=0.001)
  
      ispar = section.ISpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                  0.5, 0.01)
  
      boxspar = section.BoxSpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                      0.01)
  def test_MassAnalysis():
      # create material
      amat = material.IsotropicMaterial(1.225, 210e3, 50e3)
  
      # create sectionbase instance
      secbase = section.SectionBase(airfoilcoords())
      
      outerlayer = section.Layer(secbase, amat, thickness=0.001)
      innerlayer = section.Layer(outerlayer, amat, thickness=0.001)
  
      ispar = section.ISpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                  0.5, 0.01)
  
      boxspar = section.BoxSpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                      0.01)
  
      massana = MassAnalysis(secbase)
      cg, mass = massana.massproperties
  
      #TODO: write a meaningful test
      assert mass != None
  
new_contents: import pytest
  from wingstructure.structure import section, material, MassAnalysis
  
  
  @pytest.fixture
  def airfoilcoords():
      import numpy as np
  
      # load airfoil coordinates
      return np.loadtxt('docs/usage/FX 61-184.dat', skiprows=1, delimiter=',')
  
  
  def test_structurecreation(airfoilcoords):
      # create material
      amat = material.IsotropicMaterial(1.225, 210e3, 50e3)
  
      # create sectionbase instance
      secbase = section.SectionBase(airfoilcoords)
      
      outerlayer = section.Layer(secbase, amat, thickness=0.001)
      innerlayer = section.Layer(outerlayer, amat, thickness=0.001)
  
      ispar = section.ISpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                  0.5, 0.01)
  
      boxspar = section.BoxSpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                      0.01)
  def test_MassAnalysis(airfoilcoords):
      # create material
      amat = material.IsotropicMaterial(1.225, 210e3, 50e3)
  
      # create sectionbase instance
      secbase = section.SectionBase(airfoilcoords)
      
      outerlayer = section.Layer(secbase, amat, thickness=0.001)
      innerlayer = section.Layer(outerlayer, amat, thickness=0.001)
  
      ispar = section.ISpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                  0.5, 0.01)
  
      boxspar = section.BoxSpar(innerlayer, amat, 0.5, 0.2, 0.01,
                                      0.01)
  
      massana = MassAnalysis(secbase)
      cg, mass = massana.massproperties
  
      #TODO: write a meaningful test
      assert mass != None
  
subject: make test_MassAnalysis use airfoilcoords fixture