XFOIL         Version 6.94
  
 Calculated polar for: AG38                                            
  
 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   0.3532   0.00589   0.00144  -0.0458  0.7257  1.0000
   0.500   0.4057   0.00637   0.00147  -0.0449  0.6279  1.0000
   1.000   0.4597   0.00685   0.00164  -0.0445  0.5744  1.0000
   1.500   0.5147   0.00723   0.00185  -0.0444  0.5344  1.0000
   2.000   0.5697   0.00758   0.00206  -0.0442  0.4931  1.0000
   2.500   0.6246   0.00794   0.00229  -0.0441  0.4381  1.0000
   3.000   0.6782   0.00854   0.00259  -0.0439  0.3579  1.0000
   3.500   0.7310   0.00931   0.00304  -0.0437  0.2779  1.0000
   4.000   0.7837   0.01014   0.00360  -0.0435  0.2068  1.0000
   4.500   0.8357   0.01107   0.00426  -0.0433  0.1412  1.0000
   5.000   0.8865   0.01221   0.00513  -0.0429  0.0852  1.0000
   5.500   0.9367   0.01344   0.00625  -0.0424  0.0551  1.0000
   6.000   0.9864   0.01468   0.00755  -0.0416  0.0422  1.0000
   7.000   1.0803   0.01776   0.01084  -0.0395  0.0297  1.0000
   9.000   1.2438   0.02686   0.02097  -0.0323  0.0191  1.0000
   9.500   1.2737   0.03034   0.02468  -0.0298  0.0172  1.0000
  10.000   1.2949   0.03461   0.02955  -0.0262  0.0161  1.0000
  10.500   1.3056   0.03907   0.03453  -0.0219  0.0150  1.0000
  11.000   1.3033   0.04289   0.03869  -0.0167  0.0142  1.0000
  11.500   1.2946   0.04757   0.04366  -0.0136  0.0136  1.0000
  12.000   1.2743   0.05541   0.05182  -0.0147  0.0132  1.0000
  12.500   1.2407   0.06790   0.06473  -0.0214  0.0131  1.0000
  13.000   1.1890   0.08663   0.08394  -0.0338  0.0134  1.0000