XFOIL         Version 6.94
  
 Calculated polar for: N-10                                            
  
 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   0.5980   0.00875   0.00276  -0.0846  0.5188  0.9781
   0.500   0.6457   0.00959   0.00288  -0.0837  0.4250  1.0001
   1.000   0.6940   0.01008   0.00315  -0.0828  0.3823  1.0001
   1.500   0.7404   0.01080   0.00350  -0.0817  0.3488  1.0001
   2.000   0.7898   0.01145   0.00404  -0.0811  0.3271  1.0001
   2.500   0.8413   0.01207   0.00468  -0.0809  0.3145  1.0001
   3.000   0.8936   0.01269   0.00540  -0.0810  0.3088  1.0001
   3.500   0.9457   0.01342   0.00625  -0.0811  0.3036  1.0001
   4.000   0.9970   0.01435   0.00737  -0.0812  0.2980  1.0001
   4.500   1.0493   0.01426   0.00720  -0.0813  0.2963  1.0001
   5.500   1.1500   0.01379   0.00652  -0.0807  0.2734  1.0001
   6.000   1.1836   0.01515   0.00718  -0.0779  0.1872  1.0001
   6.500   1.2190   0.01657   0.00813  -0.0756  0.1448  1.0001
   7.000   1.2572   0.01783   0.00918  -0.0737  0.1199  1.0001
   7.500   1.2633   0.02112   0.01158  -0.0672  0.0263  1.0001
   8.000   1.2825   0.02336   0.01393  -0.0619  0.0168  1.0001
   9.000   1.2556   0.03347   0.02596  -0.0439  0.0216  1.0001