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 =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2731   0.00706   0.00288  -0.0657  0.9187  0.9883
   0.500   0.3379   0.00685   0.00258  -0.0673  0.8957  1.0000
   1.000   0.3874   0.00677   0.00239  -0.0654  0.8672  1.0000
   1.500   0.4367   0.00680   0.00233  -0.0634  0.8329  1.0000
   2.000   0.4870   0.00689   0.00231  -0.0617  0.7920  1.0000
   2.500   0.5375   0.00707   0.00236  -0.0600  0.7412  1.0000
   3.000   0.5871   0.00741   0.00248  -0.0582  0.6758  1.0000
   3.500   0.6347   0.00796   0.00273  -0.0561  0.5876  1.0000
   4.000   0.6766   0.00905   0.00310  -0.0533  0.4329  1.0000
   4.500   0.7225   0.01008   0.00369  -0.0517  0.3198  1.0000
   5.000   0.7676   0.01136   0.00443  -0.0501  0.1990  1.0000
   5.500   0.8066   0.01373   0.00587  -0.0477  0.0414  1.0000
   6.000   0.8527   0.01520   0.00746  -0.0459  0.0293  1.0000
   7.000   0.9373   0.01943   0.01209  -0.0410  0.0248  1.0000
   7.500   0.9808   0.02238   0.01529  -0.0388  0.0240  1.0000
   8.000   1.0249   0.02581   0.01912  -0.0367  0.0230  1.0000
   8.500   1.0649   0.02994   0.02372  -0.0344  0.0221  1.0000
   9.000   1.0900   0.03710   0.03176  -0.0302  0.0230  1.0000
   9.500   1.0842   0.04813   0.04371  -0.0246  0.0259  1.0000