XFOIL         Version 6.94
  
 Calculated polar for: S2060 8%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2462   0.00556   0.00188  -0.0589  0.8794  0.9212
   0.500   0.3152   0.00546   0.00175  -0.0609  0.8547  0.9775
   1.000   0.3856   0.00546   0.00163  -0.0638  0.8236  1.0000
   1.500   0.4344   0.00559   0.00161  -0.0620  0.7853  1.0000
   2.000   0.4846   0.00580   0.00164  -0.0605  0.7370  1.0000
   2.500   0.5345   0.00613   0.00175  -0.0590  0.6743  1.0000
   3.000   0.5831   0.00665   0.00194  -0.0573  0.5890  1.0000
   3.500   0.6282   0.00756   0.00226  -0.0552  0.4513  1.0000
   4.500   0.7233   0.00950   0.00327  -0.0526  0.2292  1.0000
   5.000   0.7687   0.01091   0.00406  -0.0511  0.1032  1.0000
   5.500   0.8133   0.01260   0.00532  -0.0493  0.0254  1.0000
   6.000   0.8622   0.01363   0.00651  -0.0479  0.0220  1.0000
   6.500   0.9069   0.01525   0.00829  -0.0459  0.0197  1.0000
   7.000   0.9452   0.01802   0.01131  -0.0429  0.0185  1.0000
   7.500   0.9888   0.02039   0.01390  -0.0408  0.0181  1.0000
   8.000   1.0328   0.02295   0.01675  -0.0388  0.0173  1.0000
   8.500   1.0732   0.02673   0.02095  -0.0365  0.0170  1.0000
   9.000   1.1047   0.03208   0.02691  -0.0332  0.0169  1.0000
   9.500   1.1205   0.03880   0.03435  -0.0286  0.0169  1.0000
  10.000   1.1179   0.04614   0.04235  -0.0231  0.0169  1.0000