text: """Task 5: Show difference between a thick/thin airfoil using XFOIL."""
  
  from matplotlib import pyplot as plt
  
  from numfoil.legacy.panel.thick import Solver, ThickPanelledAirfoil
  
  
  def get_data(Naca="0012", alpha=0):
      foil = ThickPanelledAirfoil(Naca=Naca, n_panels=100)
      # foil.panels.plt()
      solver = Solver(foil.panels)
      Cp = solver.solve_Cp(alpha=alpha, plot=False)
      Cl = solver.get_cl(alpha=alpha)
      return Cp, Cl, foil
  
  
  # * ### effect of thickness on Cp ###
  
  # fig, ax = plt.subplots()
  
  # for t in range(6, 30, 4):
  #     Cp, _, foil = get_data(Naca='00{0:0=2d}'.format(t), alpha=5)
  #     ax.plot([i[0] for i in foil.panels.collocation_points], Cp, label="NACA00{0:0=2d}".format(t))
  # ax.invert_yaxis()
  # ax.set_ylabel(r"$C_p$")
  # ax.set_xlabel('x/c')
  # plt.legend(loc="best")
  # plt.show()
  # plt.style.use("ggplot")
  
  
  # * ### effect of thickness on CL ###
  fig, ax = plt.subplots()
  for a in [0, 5, 10, 15]:
      Cl = []
      t = []
      for i in range(6, 30, 4):
          _, cl, _ = get_data(Naca="44{0:0=2d}".format(i), alpha=a)
          Cl.append(cl)
          t.append(i)
  
      ax.plot(t, Cl, label="alpha = {}deg".format(a))
  ax.set_ylabel(r"$C_l$")
  ax.set_xlabel("thickness [%]")
  plt.legend(loc="best")
  
  plt.show()
  plt.style.use("ggplot")
  