XFOIL         Version 6.94
  
 Calculated polar for: SIKORSKY SSC-A07 AIRFOIL                        
  
 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   0.0583   0.00587   0.00222  -0.0041  0.8836  0.9890
   0.500   0.1332   0.00575   0.00200  -0.0081  0.8659  0.9991
   1.000   0.1841   0.00562   0.00178  -0.0071  0.8441  1.0000
   1.500   0.2343   0.00556   0.00163  -0.0059  0.8154  1.0000
   2.000   0.2860   0.00558   0.00153  -0.0049  0.7735  1.0000
   2.500   0.3387   0.00583   0.00144  -0.0040  0.6661  1.0000
   3.000   0.3926   0.00726   0.00174  -0.0045  0.3959  1.0000
   3.500   0.4477   0.00835   0.00219  -0.0053  0.2526  1.0000
   4.000   0.5034   0.00900   0.00265  -0.0059  0.1996  1.0000
   4.500   0.5593   0.00953   0.00312  -0.0063  0.1698  1.0000
   5.000   0.6150   0.01006   0.00362  -0.0067  0.1416  1.0000
   5.500   0.6703   0.01065   0.00411  -0.0071  0.1004  1.0000
   6.000   0.7228   0.01213   0.00525  -0.0073  0.0406  1.0000
   6.500   0.7753   0.01364   0.00679  -0.0071  0.0271  1.0000
   7.000   0.8264   0.01535   0.00863  -0.0068  0.0224  1.0000
   7.500   0.8759   0.01732   0.01075  -0.0063  0.0195  1.0000
   8.000   0.9232   0.01984   0.01343  -0.0056  0.0175  1.0000
   8.500   0.9702   0.02216   0.01601  -0.0050  0.0149  1.0000
  10.500   1.0622   0.04410   0.04075   0.0023  0.0093  1.0000
  11.000   1.0273   0.05303   0.05026   0.0032  0.0092  1.0000
  11.500   0.9943   0.06553   0.06308  -0.0054  0.0094  1.0000