XFOIL         Version 6.94
  
 Calculated polar for: AG08                                            
  
 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   0.1878   0.00606   0.00186  -0.0397  0.9760  1.0000
   0.500   0.2631   0.00600   0.00171  -0.0432  0.9343  1.0000
   1.000   0.3184   0.00607   0.00160  -0.0418  0.8645  1.0000
   1.500   0.3676   0.00637   0.00157  -0.0393  0.7773  1.0000
   2.000   0.4179   0.00688   0.00165  -0.0374  0.6785  1.0000
   2.500   0.4694   0.00749   0.00183  -0.0361  0.5758  1.0000
   3.000   0.5218   0.00815   0.00211  -0.0352  0.4794  1.0000
   3.500   0.5746   0.00884   0.00249  -0.0346  0.3963  1.0000
   4.000   0.6278   0.00953   0.00295  -0.0341  0.3247  1.0000
   4.500   0.6808   0.01026   0.00351  -0.0336  0.2593  1.0000
   5.000   0.7335   0.01109   0.00417  -0.0332  0.1946  1.0000
   5.500   0.7855   0.01211   0.00497  -0.0327  0.1275  1.0000
   6.000   0.8357   0.01360   0.00619  -0.0320  0.0632  1.0000
   7.000   0.9299   0.01838   0.01113  -0.0291  0.0229  1.0000
   7.500   0.9750   0.02115   0.01408  -0.0275  0.0188  1.0000
   9.000   1.0771   0.03895   0.03420  -0.0200  0.0162  1.0000
   9.500   1.0773   0.04864   0.04484  -0.0175  0.0162  1.0000
  10.000   1.0492   0.05904   0.05586  -0.0165  0.0170  1.0000
  10.500   1.0111   0.07085   0.06801  -0.0243  0.0174  1.0000