XFOIL         Version 6.94
  
 Calculated polar for: nabac                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.030 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.0675   0.03854   0.02439   0.0098  0.2341  0.1373
   0.750   0.2181   0.03892   0.02787  -0.0008  0.2489  1.0001
   1.000   0.2489   0.04030   0.02915  -0.0008  0.2551  1.0001
   1.250   0.2784   0.04201   0.03065  -0.0007  0.2606  1.0001
   1.500   0.3085   0.04353   0.03202  -0.0008  0.2666  1.0001
   1.750   0.3441   0.04478   0.03350  -0.0025  0.2801  1.0001
   2.000   0.3726   0.04708   0.03558  -0.0030  0.2883  1.0001
   2.250   0.4097   0.04860   0.03736  -0.0060  0.3062  1.0001
   2.500   0.4364   0.05147   0.03995  -0.0064  0.3162  1.0001
   2.750   0.4728   0.05385   0.04261  -0.0105  0.3399  1.0001
   3.750   0.4173   0.08034   0.07100  -0.0627  0.7330  1.0001
   4.000   0.1872   0.07434   0.06560  -0.0289  0.9999  1.0001
   4.250   0.1996   0.07676   0.06778  -0.0293  0.9999  1.0001
   4.500   0.2119   0.07922   0.06999  -0.0297  0.9999  1.0001
   4.750   0.2241   0.08171   0.07225  -0.0302  0.9999  1.0001
   5.000   0.2363   0.08423   0.07454  -0.0306  0.9999  1.0001