XFOIL         Version 6.94
  
 Calculated polar for: FXW-120                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.040 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000   0.0133   0.04480   0.03654  -0.0311  0.4375  0.2135
  -2.750   0.0525   0.04226   0.03336  -0.0331  0.4264  0.1891
  -2.500   0.0905   0.04036   0.03077  -0.0344  0.4169  0.1740
  -2.250   0.1258   0.03856   0.02838  -0.0351  0.4085  0.1650
  -2.000   0.1608   0.03729   0.02660  -0.0355  0.4015  0.1627
  -1.750   0.1931   0.03609   0.02520  -0.0357  0.3963  0.1666
  -1.500   0.2256   0.03517   0.02395  -0.0356  0.3925  0.1707
  -1.250   0.2589   0.03458   0.02293  -0.0353  0.3894  0.1783
  -1.000   0.2917   0.03386   0.02220  -0.0354  0.3867  0.1913
  -0.750   0.3234   0.03339   0.02173  -0.0352  0.3844  0.2097
  -0.250   0.3847   0.03227   0.02134  -0.0352  0.3812  0.3149
   0.000   0.4156   0.03075   0.02104  -0.0331  0.3802  1.0001
   0.250   0.4456   0.03195   0.02176  -0.0335  0.3789  1.0001
   0.500   0.4745   0.03307   0.02250  -0.0338  0.3769  1.0001
   0.750   0.5034   0.03457   0.02381  -0.0346  0.3746  1.0001
   1.000   0.5317   0.03641   0.02560  -0.0359  0.3725  1.0001
   1.250   0.5592   0.03856   0.02771  -0.0374  0.3719  1.0001
   1.500   0.5855   0.04117   0.03033  -0.0392  0.3730  1.0001
   1.750   0.6103   0.04407   0.03324  -0.0410  0.3746  1.0001
   2.250   0.6369   0.05659   0.04635  -0.0516  0.3870  1.0001
   2.500   0.6524   0.06053   0.05023  -0.0535  0.3895  1.0001