<cross_section name="airfoil_skin_only">

  <include>
    <material>{material_file_stem}</material>
  </include>

  <analysis>
    <!-- Timoshenko beam model -->
    <model>1</model>
  </analysis>


  <general>
    <translate>{translate_x} {translate_y}</translate>
    <scale>{scale}</scale>
    <mesh_size>{mesh_size}</mesh_size>
    <element_shape>{element_shape}</element_shape>
    <element_type>{element_type}</element_type>
  </general>

  <baselines>

    <line name="ln_af" type="airfoil">
      <points data="file" format="1" header="1">{airfoil_file}</points>
      <leading_edge>{le_x} {le_y}</leading_edge>
      <trailing_edge>{te_x} {te_y}</trailing_edge>
    </line>

  </baselines>

  <materials>
    <lamina name="ply">
      <material>{material_name}</material>
      <thickness>{lamina_thickness}</thickness>
    </lamina>
  </materials>

  <layups>
    <layup name="layup1">
      <layer lamina="ply">{fiber_angle}</layer>
    </layup>
  </layups>


  <!-- Surface layup -->
  <component name="surface">
    <segment name="sg_le">
      <baseline>ln_af</baseline>
      <layup>layup1</layup>
    </segment>
  </component>

</cross_section>
