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 =     0.035 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000   0.0180   0.04597   0.03760  -0.0325  0.4756  0.2142
  -2.750   0.0577   0.04388   0.03484  -0.0347  0.4625  0.1961
  -2.500   0.0921   0.04192   0.03249  -0.0357  0.4519  0.1891
  -2.250   0.1270   0.04039   0.03042  -0.0365  0.4423  0.1865
  -2.000   0.1613   0.03915   0.02879  -0.0372  0.4335  0.1871
  -1.750   0.1946   0.03805   0.02724  -0.0372  0.4259  0.1881
  -1.500   0.2286   0.03732   0.02605  -0.0373  0.4200  0.1948
  -1.250   0.2633   0.03668   0.02523  -0.0377  0.4155  0.2047
  -1.000   0.2968   0.03629   0.02464  -0.0378  0.4119  0.2189
  -0.750   0.3276   0.03575   0.02417  -0.0376  0.4091  0.2427
  -0.500   0.3578   0.03530   0.02387  -0.0373  0.4068  0.2791
  -0.250   0.3865   0.03256   0.02363  -0.0358  0.4052  1.0001
   0.000   0.4204   0.03413   0.02420  -0.0361  0.4038  1.0001
   0.250   0.4506   0.03592   0.02566  -0.0373  0.4030  1.0001
   0.500   0.4796   0.03796   0.02751  -0.0389  0.4020  1.0001
   0.750   0.5072   0.04022   0.02965  -0.0407  0.4003  1.0001
   1.000   0.5333   0.04261   0.03195  -0.0425  0.3980  1.0001
   1.250   0.5577   0.04529   0.03455  -0.0444  0.3965  1.0001
   1.500   0.5785   0.04927   0.03859  -0.0477  0.3985  1.0001
   1.750   0.5965   0.05350   0.04283  -0.0508  0.4020  1.0001
   2.000   0.6154   0.05706   0.04631  -0.0527  0.4050  1.0001