original_docstring: 
      Generates a simetric NACA airfoil.
      Inputs:
      :param c: chord
      :param t: max thickness normalized by the chord (t/c)
      :param x_list: points between 0 and c (chord lenght)
      :param TE_t: trailing edge thickness. If False it is the standard
                   thickness for a NACA airfoil. Otherwise it is the given value.
      :param return_dict: return dictionary y('y') or x and y ('xy')
      Returns dictionary y coordinates with keys 'u'pper and 'l'ower
      
      The Naca function can be found in: https://en.wikipedia.org/wiki/NACA_airfoil  
  
      Created on Wed Feb 03 12:50:52 2016
      
      @author: Endryws and Pedro Leal
      
docstring: Generates a simetric NACA airfoil.
  Inputs.
docstring_tokens: Generates a simetric NACA airfoil . Inputs .
code: def Naca00XX(c, t, x_list, TE_t = False, return_dict = 'y', for_xfoil = True):
      """
      Generates a simetric NACA airfoil.
      Inputs:
      :param c: chord
      :param t: max thickness normalized by the chord (t/c)
      :param x_list: points between 0 and c (chord lenght)
      :param TE_t: trailing edge thickness. If False it is the standard
                   thickness for a NACA airfoil. Otherwise it is the given value.
      :param return_dict: return dictionary y('y') or x and y ('xy')
      Returns dictionary y coordinates with keys 'u'pper and 'l'ower
      
      The Naca function can be found in: https://en.wikipedia.org/wiki/NACA_airfoil  
  
      Created on Wed Feb 03 12:50:52 2016
      
      @author: Endryws and Pedro Leal
      """
      y_upper = []
      y_lower = []
      for x in x_list:
          xc= x/c # Is just for increase speed and facilitate future changes.
          a1 = 5*t*c
          t1 = 0.2969*(math.sqrt(xc))
          t2 = -0.1260*xc
          t3 = -0.3516*(xc**2)
          t4 = 0.2843*(xc**3)
          if TE_t == False:
              t5 = -0.1015*(xc**4)
          else:
              t5 = (TE_t/(10*t) - 0.1036)*(xc**4)
          y = (a1*(t1+t2+t3+t4+t5))
          y_upper.append(y)
          y_lower.append(y*(-1)) # is just for pick the y axis
                                         # negative numbers
  
      if len(x_list) == 1:
          y = {'u': y_upper[0],
               'l': y_lower[0]}        
      else:
          if for_xfoil:
              y = {'u': y_upper[:-1],
                   'l':y_lower[-2::-1]}
          else:
              y = {'u': y_upper,
                   'l':y_lower}            
      if return_dict == 'y':
          return y
          
      elif return_dict == 'xy':
          x = {'u':x_list[:-1],
               'l':x_list[-2::-1]}
          return x, y
code_tokens: def Naca00XX ( c , t , x_list , TE_t = False , return_dict = 'y' , for_xfoil = True ) : y_upper = [ ] y_lower = [ ] for x in x_list : xc = x / c a1 = 5 * t * c t1 = 0.2969 * ( math . sqrt ( xc ) ) t2 = - 0.1260 * xc t3 = - 0.3516 * ( xc ** 2 ) t4 = 0.2843 * ( xc ** 3 ) if TE_t == False : t5 = - 0.1015 * ( xc ** 4 ) else : t5 = ( TE_t / ( 10 * t ) - 0.1036 ) * ( xc ** 4 ) y = ( a1 * ( t1 + t2 + t3 + t4 + t5 ) ) y_upper . append ( y ) y_lower . append ( y * ( - 1 ) ) if len ( x_list ) == 1 : y = { 'u' : y_upper [ 0 ] , 'l' : y_lower [ 0 ] } else : if for_xfoil : y = { 'u' : y_upper [ : - 1 ] , 'l' : y_lower [ - 2 : : - 1 ] } else : y = { 'u' : y_upper , 'l' : y_lower } if return_dict == 'y' : return y elif return_dict == 'xy' : x = { 'u' : x_list [ : - 1 ] , 'l' : x_list [ - 2 : : - 1 ] } return x , y
short_docstring: Generates a simetric NACA airfoil.
short_docstring_tokens: Generates a simetric NACA airfoil .
comment: """
      Generates a simetric NACA airfoil.
      Inputs:
      :param c: chord
      :param t: max thickness normalized by the chord (t/c)
      :param x_list: points between 0 and c (chord lenght)
      :param TE_t: trailing edge thickness. If False it is the standard
                   thickness for a NACA airfoil. Otherwise it is the given value.
      :param return_dict: return dictionary y('y') or x and y ('xy')
      Returns dictionary y coordinates with keys 'u'pper and 'l'ower
      
      The Naca function can be found in: https://en.wikipedia.org/wiki/NACA_airfoil  
  
      Created on Wed Feb 03 12:50:52 2016
      
      @author: Endryws and Pedro Leal
      """$SEP$# Is just for increase speed and facilitate future changes.$SEP$# is just for pick the y axis$SEP$# negative numbers