XFOIL         Version 6.94
  
 Calculated polar for: GM15 (smoothed)                                 
  
 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   0.5788   0.00716   0.00183  -0.1371  0.8554  0.3623
   0.500   0.6323   0.00705   0.00171  -0.1360  0.8188  0.4054
   1.000   0.6842   0.00704   0.00169  -0.1346  0.7718  0.4638
   1.500   0.7300   0.00668   0.00184  -0.1322  0.7235  0.7132
   3.000   0.8899   0.00743   0.00240  -0.1297  0.6005  1.0000
   3.500   0.9397   0.00784   0.00269  -0.1281  0.5626  1.0000
   4.000   0.9888   0.00830   0.00308  -0.1265  0.5230  1.0000
   4.500   1.0333   0.00903   0.00348  -0.1241  0.4425  1.0000
   5.000   1.0765   0.01001   0.00404  -0.1216  0.3487  1.0000
   5.500   1.1191   0.01121   0.00485  -0.1193  0.2502  1.0000
   6.000   1.1442   0.01458   0.00690  -0.1144  0.0329  1.0000
   6.500   1.1858   0.01610   0.00857  -0.1115  0.0224  1.0000
   7.000   1.2203   0.01830   0.01107  -0.1074  0.0187  1.0000
   7.500   1.2583   0.01995   0.01287  -0.1042  0.0153  1.0000
   8.000   1.2892   0.02243   0.01552  -0.0999  0.0131  1.0000
   8.500   1.3151   0.02876   0.02223  -0.0951  0.0115  1.0000
   9.000   1.3508   0.03036   0.02410  -0.0918  0.0101  1.0000
   9.500   1.3806   0.03468   0.02889  -0.0880  0.0093  1.0000
  10.000   1.3985   0.04013   0.03487  -0.0828  0.0088  1.0000
  10.500   1.3959   0.04586   0.04113  -0.0754  0.0085  1.0000
  11.000   1.3678   0.05344   0.04933  -0.0667  0.0088  1.0000
  11.500   1.3250   0.06271   0.05915  -0.0609  0.0093  1.0000
  12.000   1.2812   0.07314   0.07001  -0.0600  0.0097  1.0000
  12.500   1.2375   0.08579   0.08302  -0.0643  0.0099  1.0000
  13.000   1.1961   0.10094   0.09847  -0.0730  0.0101  1.0000
  13.500   1.1562   0.11947   0.11725  -0.0854  0.0103  1.0000