XFOIL         Version 6.94
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AI                
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.500   0.6904   0.01062   0.00351  -0.1138  0.5742  0.0584
   1.000   0.7468   0.01055   0.00314  -0.1129  0.5568  0.0654
   1.500   0.8018   0.01098   0.00342  -0.1125  0.5392  0.0815
   2.000   0.8565   0.01101   0.00345  -0.1123  0.5224  0.0903
   2.500   0.9106   0.01097   0.00342  -0.1120  0.5050  0.0983
   3.000   0.9639   0.01099   0.00345  -0.1117  0.4844  0.1092
   3.500   1.0168   0.01111   0.00354  -0.1114  0.4607  0.1257
   4.000   1.0691   0.01127   0.00371  -0.1110  0.4345  0.1502
   4.500   1.1127   0.01062   0.00412  -0.1095  0.3655  1.0000
   5.000   1.1563   0.01175   0.00470  -0.1078  0.2973  1.0000
   5.500   1.1889   0.01394   0.00594  -0.1048  0.1555  1.0000
   6.000   1.2107   0.01702   0.00833  -0.1000  0.0066  1.0000
   6.500   1.2559   0.01777   0.00913  -0.0985  0.0065  1.0000
   7.000   1.2997   0.01856   0.01000  -0.0967  0.0079  1.0000
   7.500   1.3407   0.01949   0.01104  -0.0945  0.0091  1.0000
   8.000   1.3725   0.02078   0.01252  -0.0907  0.0088  1.0000
   8.500   1.3963   0.02257   0.01455  -0.0862  0.0082  1.0000
   9.000   1.4091   0.02529   0.01751  -0.0810  0.0076  1.0000
   9.500   1.4036   0.02974   0.02216  -0.0753  0.0072  1.0000
  10.000   1.4122   0.03355   0.02618  -0.0720  0.0065  1.0000
  10.500   1.3957   0.04022   0.03303  -0.0687  0.0058  1.0000
  11.000   1.3714   0.04813   0.04102  -0.0659  0.0055  1.0000