XFOIL         Version 6.94
  
 Calculated polar for: N-11                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.6314   0.01092   0.00280  -0.0997  0.6061  0.0440
   0.500   0.6845   0.01098   0.00273  -0.0996  0.5882  0.0447
   1.000   0.7359   0.01115   0.00271  -0.0990  0.5558  0.0474
   1.500   0.7819   0.01095   0.00300  -0.0979  0.5030  0.3106
   2.500   0.8829   0.01055   0.00367  -0.0970  0.4072  1.0000
   3.000   0.9299   0.01115   0.00401  -0.0960  0.3722  1.0000
   3.500   0.9739   0.01196   0.00445  -0.0945  0.3362  1.0000
   4.000   1.0225   0.01274   0.00518  -0.0938  0.3106  1.0000
   4.500   1.0739   0.01353   0.00608  -0.0937  0.2989  1.0000
   5.500   1.1733   0.01370   0.00621  -0.0930  0.2857  1.0000
   6.000   1.2198   0.01430   0.00672  -0.0921  0.2634  1.0000
   6.500   1.2522   0.01563   0.00754  -0.0890  0.1946  1.0000
   7.000   1.2804   0.01728   0.00856  -0.0855  0.1504  1.0000
   7.500   1.3018   0.01924   0.01004  -0.0809  0.0942  1.0000
   8.000   1.3053   0.02257   0.01270  -0.0740  0.0224  1.0000
   8.500   1.3240   0.02471   0.01505  -0.0690  0.0165  1.0000
  10.500   1.3111   0.04430   0.03720  -0.0444  0.0276  1.0000
  12.000   1.2182   0.08257   0.07875  -0.0352  0.0828  1.0000
  12.500   1.1712   0.09633   0.09274  -0.0404  0.0816  1.0000
  13.000   1.1286   0.11122   0.10776  -0.0475  0.0797  1.0000