XFOIL         Version 6.94
  
 Calculated polar for: Eif385mod4                                      
  
 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
 ------- -------- --------- --------- -------- ------- -------
  -3.000  -0.1759   0.04202   0.03413   0.0192  0.9993  0.7222
  -2.750  -0.1393   0.04093   0.03321   0.0158  0.9993  0.7267
  -2.500  -0.0979   0.04005   0.03249   0.0113  0.9993  0.7277
  -2.000   0.2048   0.03347   0.02338  -0.0339  0.4950  0.6801
  -1.750   0.2429   0.03426   0.02329  -0.0365  0.4625  0.6688
  -1.500   0.2805   0.03477   0.02340  -0.0385  0.4445  0.6655
  -1.250   0.3183   0.03535   0.02364  -0.0405  0.4322  0.6644
  -1.000   0.3557   0.03579   0.02405  -0.0422  0.4216  0.6718
  -0.750   0.3921   0.03628   0.02457  -0.0435  0.4121  0.7113
  -0.500   0.4404   0.03671   0.02512  -0.0473  0.4030  1.0007
  -0.250   0.4772   0.03782   0.02600  -0.0491  0.3962  1.0007
   0.000   0.5132   0.03903   0.02701  -0.0507  0.3914  1.0007
   0.250   0.5487   0.04033   0.02818  -0.0521  0.3888  1.0007
   0.500   0.5832   0.04172   0.02951  -0.0534  0.3870  1.0007
   0.750   0.6167   0.04322   0.03100  -0.0547  0.3859  1.0007
   1.000   0.6492   0.04483   0.03265  -0.0559  0.3855  1.0007
   1.250   0.6800   0.04655   0.03447  -0.0570  0.3858  1.0007
   1.500   0.7091   0.04841   0.03649  -0.0580  0.3868  1.0007
   1.750   0.7360   0.05050   0.03880  -0.0589  0.3886  1.0007
   2.000   0.7601   0.05294   0.04151  -0.0599  0.3915  1.0007
   2.250   0.7817   0.05574   0.04457  -0.0608  0.3949  1.0007
   2.500   0.8009   0.05883   0.04786  -0.0616  0.3982  1.0007
   2.750   0.8167   0.06222   0.05143  -0.0622  0.4013  1.0007
   3.000   0.8301   0.06585   0.05519  -0.0626  0.4043  1.0007
   3.250   0.8431   0.06962   0.05904  -0.0630  0.4071  1.0007
   3.750   0.7921   0.08367   0.07369  -0.0636  0.4304  1.0007