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 =     0.045 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000   0.0096   0.04402   0.03576  -0.0304  0.4042  0.2210
  -2.750   0.0559   0.04164   0.03244  -0.0331  0.3939  0.1785
  -2.500   0.0942   0.03977   0.02979  -0.0341  0.3860  0.1601
  -2.250   0.1254   0.03736   0.02726  -0.0344  0.3800  0.1546
  -1.750   0.1930   0.03451   0.02353  -0.0347  0.3729  0.1472
  -1.500   0.2251   0.03356   0.02231  -0.0347  0.3700  0.1523
  -1.250   0.2572   0.03285   0.02124  -0.0343  0.3677  0.1580
  -1.000   0.2883   0.03199   0.02024  -0.0338  0.3657  0.1694
  -0.750   0.3196   0.03139   0.01945  -0.0332  0.3640  0.1834
  -0.500   0.3498   0.03085   0.01890  -0.0327  0.3627  0.2099
  -0.250   0.3805   0.03034   0.01863  -0.0326  0.3618  0.2534
   0.000   0.4103   0.02794   0.01814  -0.0306  0.3609  1.0001
   0.250   0.4408   0.02898   0.01868  -0.0308  0.3594  1.0001
   0.500   0.4705   0.03008   0.01949  -0.0312  0.3572  1.0001
   0.750   0.4995   0.03120   0.02038  -0.0316  0.3547  1.0001
   1.000   0.5283   0.03245   0.02144  -0.0321  0.3528  1.0001
   1.250   0.5573   0.03417   0.02314  -0.0331  0.3531  1.0001
   1.500   0.5855   0.03638   0.02544  -0.0346  0.3542  1.0001
   1.750   0.6124   0.03913   0.02833  -0.0366  0.3562  1.0001
   2.000   0.6374   0.04223   0.03155  -0.0387  0.3584  1.0001
   2.250   0.6601   0.04563   0.03506  -0.0409  0.3600  1.0001
   2.500   0.6802   0.04929   0.03882  -0.0431  0.3612  1.0001
   2.750   0.6976   0.05335   0.04297  -0.0454  0.3629  1.0001