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 =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.1274   0.00743   0.00310  -0.0207  0.9249  1.0000
   0.500   0.1672   0.00727   0.00285  -0.0173  0.9040  1.0000
   1.000   0.2094   0.00709   0.00263  -0.0142  0.8815  1.0000
   1.500   0.2539   0.00693   0.00243  -0.0115  0.8552  1.0000
   2.000   0.2995   0.00682   0.00223  -0.0087  0.8221  1.0000
   2.500   0.3494   0.00679   0.00216  -0.0069  0.7675  1.0000
   3.000   0.3979   0.00727   0.00199  -0.0048  0.5949  1.0000
   3.500   0.4494   0.00912   0.00254  -0.0052  0.3133  1.0000
   4.000   0.5035   0.01011   0.00317  -0.0056  0.2312  1.0000
   4.500   0.5581   0.01085   0.00379  -0.0059  0.1944  1.0000
   5.000   0.6128   0.01150   0.00442  -0.0061  0.1629  1.0000
   5.500   0.6676   0.01205   0.00499  -0.0063  0.1237  1.0000
   6.000   0.7197   0.01353   0.00612  -0.0064  0.0541  1.0000
   6.500   0.7698   0.01554   0.00808  -0.0060  0.0353  1.0000
   7.500   0.8675   0.02017   0.01297  -0.0045  0.0253  1.0000
   8.500   0.9586   0.02723   0.02102  -0.0024  0.0197  1.0000
   9.000   0.9957   0.03234   0.02658  -0.0012  0.0177  1.0000
   9.500   1.0048   0.04181   0.03750   0.0019  0.0172  1.0000
  10.000   0.9903   0.05210   0.04865   0.0039  0.0174  1.0000
  10.500   0.9609   0.06086   0.05781   0.0041  0.0175  1.0000