XFOIL         Version 6.94
  
 Calculated polar for: MA409 (smoothed)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4129   0.00800   0.00364  -0.1051  0.9399  1.0000
   0.500   0.4800   0.00772   0.00329  -0.1068  0.9260  1.0000
   1.000   0.5427   0.00744   0.00298  -0.1074  0.9081  1.0000
   1.500   0.6024   0.00721   0.00273  -0.1073  0.8848  1.0000
   2.000   0.6587   0.00713   0.00261  -0.1065  0.8519  1.0000
   2.500   0.7136   0.00719   0.00261  -0.1055  0.8096  1.0000
   3.000   0.7657   0.00743   0.00274  -0.1040  0.7534  1.0000
   3.500   0.8137   0.00796   0.00296  -0.1016  0.6661  1.0000
   4.000   0.8547   0.00905   0.00341  -0.0981  0.5222  1.0000
   4.500   0.8944   0.01052   0.00411  -0.0951  0.3566  1.0000
   5.000   0.9261   0.01356   0.00558  -0.0916  0.0725  1.0000
   5.500   0.9655   0.01612   0.00812  -0.0883  0.0309  1.0000
   6.000   1.0087   0.01796   0.01015  -0.0858  0.0260  1.0000
   6.500   1.0503   0.02037   0.01273  -0.0829  0.0228  1.0000
   7.000   1.0926   0.02394   0.01650  -0.0801  0.0208  1.0000
   7.500   1.1334   0.02964   0.02279  -0.0773  0.0181  1.0000
   8.000   1.1690   0.03528   0.02912  -0.0735  0.0175  1.0000
   8.500   1.1284   0.02764   0.02250  -0.0584  0.0206  1.0000