XFOIL         Version 6.94
  
 Calculated polar for: eif385mod5                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.026 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -2.750  -0.1850   0.04604   0.03918   0.0386  0.9993  0.8215
  -2.500  -0.1300   0.04478   0.03811   0.0270  0.9993  0.8042
  -2.250   0.2124   0.03835   0.02956  -0.0416  0.5203  0.7042
  -2.000   0.2652   0.03943   0.02935  -0.0493  0.4691  0.6811
  -1.750   0.3165   0.04028   0.02940  -0.0562  0.4460  0.6618
  -1.500   0.3652   0.04101   0.02950  -0.0619  0.4299  0.6452
  -1.250   0.4095   0.04156   0.02960  -0.0661  0.4167  0.6346
  -1.000   0.4562   0.04242   0.03000  -0.0708  0.4065  0.6200
  -0.750   0.4988   0.04301   0.03037  -0.0742  0.3989  0.6133
  -0.500   0.5408   0.04370   0.03087  -0.0774  0.3942  0.6057
  -0.250   0.5838   0.04479   0.03172  -0.0808  0.3907  0.5945
   0.000   0.6238   0.04581   0.03262  -0.0834  0.3882  0.5871
   0.250   0.6619   0.04689   0.03368  -0.0857  0.3866  0.5843
   0.750   0.7342   0.04947   0.03635  -0.0897  0.3854  0.5777
   1.000   0.7684   0.05106   0.03806  -0.0915  0.3857  0.5725
   1.250   0.8005   0.05270   0.03987  -0.0930  0.3867  0.5684
   1.500   0.8302   0.05445   0.04185  -0.0944  0.3879  0.5655
   1.750   0.8576   0.05648   0.04416  -0.0956  0.3891  0.5631
   2.000   0.8823   0.05881   0.04679  -0.0967  0.3902  0.5616
   2.250   0.9038   0.06149   0.04978  -0.0977  0.3918  0.5624
   2.500   0.9212   0.06466   0.05331  -0.0987  0.3944  0.5645
   2.750   0.9331   0.06852   0.05751  -0.0997  0.3987  0.5668
   3.250   0.9586   0.07664   0.06613  -0.1015  0.4098  0.5735
   3.500   0.9041   0.08717   0.07710  -0.1028  0.4299  0.5688
   3.750   0.9315   0.09075   0.08082  -0.1045  0.4367  0.5747