XFOIL         Version 6.94
  
 Calculated polar for: davissm                                         
  
 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   0.7149   0.01185   0.00503  -0.1674  0.8654  0.0612
   0.500   0.7701   0.01128   0.00446  -0.1669  0.8500  0.0715
   1.000   0.8257   0.01030   0.00426  -0.1670  0.8341  0.3814
   2.000   0.9343   0.00933   0.00407  -0.1657  0.7976  1.0000
   2.500   0.9866   0.00938   0.00403  -0.1644  0.7676  1.0000
   3.000   1.0391   0.00954   0.00410  -0.1634  0.7369  1.0000
   3.500   1.0904   0.00979   0.00425  -0.1620  0.6985  1.0000
   4.000   1.1403   0.01016   0.00452  -0.1605  0.6523  1.0000
   4.500   1.1862   0.01082   0.00491  -0.1581  0.5811  1.0000
   5.000   1.2233   0.01219   0.00567  -0.1542  0.4502  1.0000
   5.500   1.2315   0.01675   0.00811  -0.1463  0.0948  1.0000
   6.000   1.2683   0.01859   0.00993  -0.1428  0.0624  1.0000
   6.500   1.3028   0.02044   0.01190  -0.1389  0.0453  1.0000
   7.000   1.3312   0.02258   0.01414  -0.1339  0.0354  1.0000
   7.500   1.3599   0.02455   0.01623  -0.1290  0.0300  1.0000
   8.000   1.3784   0.02881   0.02064  -0.1226  0.0265  1.0000
   8.500   1.4133   0.03095   0.02306  -0.1189  0.0238  1.0000
   9.000   1.4557   0.03454   0.02693  -0.1167  0.0217  1.0000
   9.500   1.4971   0.03912   0.03188  -0.1146  0.0201  1.0000
  10.000   1.5255   0.04753   0.04089  -0.1115  0.0183  1.0000
  11.000   1.5054   0.06342   0.05809  -0.0942  0.0182  1.0000
  11.500   1.4857   0.06838   0.06346  -0.0854  0.0185  1.0000