text: """This is script is an example of running Ptera Software's steady ring vortex
  lattice method solver on three airplanes (with geometry similar to the NMT
  experimental setup) flying in formation."""
  import pterasoftware as ps
  
  horseshoe_vortex_method = False
  
  alpha = 5
  x_spacing = 0.5
  y_spacing = 0.5
  
  experimental_lead_airplane = ps.geometry.Airplane(
      name="Experimental Lead Airplane",
      wings=[
          ps.geometry.Wing(
              name="Main Wing",
              symmetric=True,
              chordwise_spacing="uniform",
              wing_cross_sections=[
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      chord=0.1094,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      y_le=0.2275,
                      chord=0.1094,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      y_le=0.350,
                      chord=0.0219,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
              ],
          ),
      ],
  )
  
  experimental_right_airplane = ps.geometry.Airplane(
      name="Experimental Right Airplane",
      x_ref=x_spacing,
      y_ref=y_spacing,
      wings=[
          ps.geometry.Wing(
              name="Main Wing",
              symmetric=True,
              chordwise_spacing="uniform",
              x_le=x_spacing,
              y_le=y_spacing,
              wing_cross_sections=[
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      chord=0.1094,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      y_le=0.2275,
                      chord=0.1094,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      y_le=0.350,
                      chord=0.0219,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
              ],
          ),
      ],
  )
  
  experimental_left_airplane = ps.geometry.Airplane(
      name="Experimental Left Airplane",
      x_ref=x_spacing,
      y_ref=-y_spacing,
      wings=[
          ps.geometry.Wing(
              name="Main Wing",
              symmetric=True,
              chordwise_spacing="uniform",
              x_le=x_spacing,
              y_le=-y_spacing,
              wing_cross_sections=[
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      chord=0.1094,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      y_le=0.2275,
                      chord=0.1094,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
                  ps.geometry.WingCrossSection(
                      twist=alpha,
                      y_le=0.350,
                      chord=0.0219,
                      airfoil=ps.geometry.Airfoil(name="naca0012"),
                  ),
              ],
          ),
      ],
  )
  
  
  experimental_operating_point = ps.operating_point.OperatingPoint(
      density=1.225,
      velocity=1.0,
      alpha=0.0,
      nu=15.06e-6,
  )
  
  
  experimental_problem = ps.problems.SteadyProblem(
      airplanes=[
          experimental_lead_airplane,
          experimental_right_airplane,
          experimental_left_airplane,
      ],
      operating_point=experimental_operating_point,
  )
  
  del experimental_lead_airplane
  del experimental_right_airplane
  del experimental_left_airplane
  del experimental_operating_point
  
  if horseshoe_vortex_method:
      experimental_solver = ps.steady_horseshoe_vortex_lattice_method.SteadyHorseshoeVortexLatticeMethodSolver(
          steady_problem=experimental_problem,
      )
  else:
      experimental_solver = (
          ps.steady_ring_vortex_lattice_method.SteadyRingVortexLatticeMethodSolver(
              steady_problem=experimental_problem,
          )
      )
  
  del experimental_problem
  
  experimental_solver.run()
  
  ps.output.print_steady_results(steady_solver=experimental_solver)
  
  ps.output.draw(
      solver=experimental_solver, show_delta_pressures=True, show_streamlines=True
  )
  