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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2072   0.00483   0.00132  -0.0427  0.9290  1.0000
   0.500   0.2586   0.00495   0.00119  -0.0407  0.8591  1.0000
   1.000   0.3090   0.00527   0.00114  -0.0388  0.7757  1.0000
   1.500   0.3610   0.00572   0.00118  -0.0374  0.6828  1.0000
   2.000   0.4138   0.00624   0.00129  -0.0365  0.5867  1.0000
   2.500   0.4673   0.00680   0.00148  -0.0359  0.4934  1.0000
   3.000   0.5211   0.00738   0.00175  -0.0355  0.4123  1.0000
   4.000   0.6291   0.00855   0.00248  -0.0348  0.2795  1.0000
   4.500   0.6828   0.00922   0.00294  -0.0344  0.2205  1.0000
   5.000   0.7361   0.00996   0.00352  -0.0340  0.1604  1.0000
   5.500   0.7886   0.01091   0.00425  -0.0336  0.0995  1.0000
   6.000   0.8399   0.01215   0.00527  -0.0331  0.0474  1.0000
   6.500   0.8900   0.01386   0.00699  -0.0321  0.0227  1.0000
   7.000   0.9388   0.01573   0.00903  -0.0309  0.0162  1.0000
   7.500   0.9816   0.01899   0.01254  -0.0290  0.0133  1.0000
   8.000   1.0274   0.02162   0.01555  -0.0273  0.0122  1.0000
   8.500   1.0712   0.02431   0.01857  -0.0258  0.0106  1.0000
   9.000   1.1073   0.02873   0.02346  -0.0238  0.0099  1.0000
   9.500   1.1288   0.03577   0.03127  -0.0210  0.0097  1.0000
  10.000   1.0942   0.05097   0.04799  -0.0171  0.0113  1.0000
  10.500   1.0504   0.06205   0.05955  -0.0200  0.0118  1.0000
  11.000   1.0142   0.08105   0.07887  -0.0386  0.0118  1.0000
  11.500   0.9563   0.10900   0.10689  -0.0557  0.0125  1.0000