XFOIL         Version 6.94
  
 Calculated polar for: AH 63-K-127/24                                  
  
 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   0.3609   0.01585   0.01087  -0.0812  0.7382  0.9067
   0.500   0.4066   0.01576   0.01072  -0.0790  0.7319  0.9233
   1.000   0.4545   0.01552   0.01043  -0.0770  0.7269  0.9406
   1.500   0.5111   0.01535   0.01019  -0.0770  0.7229  0.9516
   2.000   0.5628   0.01547   0.01036  -0.0773  0.7141  0.9627
   2.500   0.6264   0.01544   0.01038  -0.0797  0.7058  0.9733
   3.000   0.7010   0.01519   0.01015  -0.0839  0.7002  0.9812
   3.500   0.7756   0.01469   0.00972  -0.0880  0.6960  0.9871
   4.000   0.8516   0.01390   0.00893  -0.0919  0.6908  0.9926
   4.500   0.9001   0.01397   0.00920  -0.0918  0.6772  1.0000
   5.000   0.9609   0.01261   0.00800  -0.0922  0.6673  1.0000
   5.500   1.0172   0.01183   0.00734  -0.0922  0.6502  1.0000
   6.000   1.0760   0.01108   0.00662  -0.0925  0.6246  1.0000
   6.500   1.1264   0.01097   0.00651  -0.0916  0.5785  1.0000
   7.000   1.1689   0.01155   0.00694  -0.0895  0.5173  1.0000
   7.500   1.1815   0.01345   0.00818  -0.0827  0.3887  1.0000
   8.000   1.1424   0.01783   0.01147  -0.0701  0.2108  1.0000
   8.500   1.1313   0.02230   0.01527  -0.0645  0.1122  1.0000
   9.000   1.1475   0.02499   0.01789  -0.0613  0.0768  1.0000
   9.500   1.1563   0.02819   0.02083  -0.0575  0.0402  1.0000
  10.000   1.1545   0.03245   0.02495  -0.0525  0.0130  1.0000
  10.500   1.1644   0.03590   0.02875  -0.0490  0.0155  1.0000