XFOIL         Version 6.94
  
 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-1                
  
 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   0.2773   0.01467   0.01106  -0.0540  0.0522  2.0772
   0.500   0.3387   0.01445   0.01078  -0.0548  0.0533  2.0470
   1.500   0.4203   0.01403   0.01036  -0.0512  0.0809  2.0016
   2.000   0.4657   0.01304   0.00934  -0.0509  0.0854  2.0010
   4.000   0.6479   0.00707   0.00327  -0.0473  0.1591  2.0010
   4.500   0.6411   0.00713   0.00333  -0.0398  0.2520  2.0010
   5.000   0.7071   0.00571   0.00153  -0.0413  0.4498  2.0010
   5.500   0.6987   0.00602   0.00151  -0.0336  0.7408  2.0010
   6.000   0.6795   0.00664   0.00186  -0.0250  1.0389  2.0010
   6.500   0.6529   0.00755   0.00241  -0.0161  1.4781  2.0010
   7.000   0.6318   0.00852   0.00298  -0.0084  2.0437  2.0010
   7.500   0.5916   0.01030   0.00392   0.0002  3.5428  2.0010
   8.000   0.5918   0.01093   0.00447   0.0051  4.2282  2.0010
   8.500   0.6025   0.01122   0.00487   0.0089  4.2360  2.0010
   9.000   0.6120   0.01155   0.00534   0.0127  4.2374  2.0010
   9.500   0.6195   0.01197   0.00589   0.0165  4.2370  2.0010
  10.000   0.6248   0.01248   0.00656   0.0203  4.2356  2.0010
  10.500   0.6284   0.01308   0.00731   0.0239  4.2325  2.0010
  11.000   0.6302   0.01378   0.00816   0.0275  4.2280  2.0010
  11.500   0.6267   0.01475   0.00927   0.0310  4.2219  2.0010
  12.000   0.6194   0.01594   0.01059   0.0342  4.2174  2.0010
  12.500   0.6149   0.01707   0.01185   0.0371  4.2106  2.0010
  13.000   0.6106   0.01823   0.01313   0.0398  4.1998  2.0010
  13.500   0.6109   0.01921   0.01421   0.0422  4.1884  2.0010
  14.000   0.6198   0.01976   0.01480   0.0446  4.1678  2.0010
  14.500   0.6509   0.01942   0.01446   0.0474  4.1257  2.0010