XFOIL         Version 6.94
  
 Calculated polar for: HT22                                            
  
 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   0.0767   0.00553   0.00148  -0.0086  1.0001  0.9999
   0.500   0.1360   0.00558   0.00149  -0.0092  0.9873  0.9999
   1.000   0.2015   0.00608   0.00143  -0.0096  0.7640  0.9999
   1.500   0.2504   0.00696   0.00147  -0.0075  0.5815  0.9999
   2.500   0.3585   0.00816   0.00184  -0.0064  0.3995  0.9999
   3.000   0.4134   0.00866   0.00211  -0.0061  0.3301  0.9999
   3.500   0.4682   0.00924   0.00243  -0.0058  0.2556  0.9999
   4.000   0.5224   0.01005   0.00291  -0.0056  0.1728  0.9999
   4.500   0.5764   0.01112   0.00368  -0.0054  0.1052  0.9999
   5.000   0.6301   0.01232   0.00476  -0.0051  0.0730  0.9999
   5.500   0.6833   0.01366   0.00611  -0.0046  0.0575  0.9999
   6.500   0.7873   0.01702   0.00964  -0.0033  0.0430  0.9999
   7.000   0.8378   0.01934   0.01208  -0.0026  0.0388  0.9999
   7.500   0.8884   0.02157   0.01462  -0.0018  0.0351  0.9999
   8.500   0.9797   0.02908   0.02308  -0.0003  0.0292  0.9999
  10.000   1.0125   0.05738   0.05429  -0.0049  0.0248  0.9999
  10.500   0.9832   0.07283   0.07002  -0.0209  0.0252  0.9999