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       XFOIL         Version 6.90
  
 Calculated polar for: Eppler 387                                       1 elements
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)     element  1
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top Xtr Bot Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000   0.1048   0.01946   0.01072  -0.1011  0.9086  0.0922
  -2.900   0.1145   0.01905   0.01039  -0.1009  0.9029  0.0999
  -2.800   0.1271   0.01856   0.00992  -0.1010  0.8993  0.1103
  -2.700   0.1402   0.01812   0.00956  -0.1013  0.8964  0.1268
  -2.600   0.1505   0.01776   0.00923  -0.1010  0.8914  0.1446
  -2.500   0.1617   0.01730   0.00895  -0.1011  0.8875  0.1717
  -2.400   0.1736   0.01670   0.00860  -0.1011  0.8845  0.2145
  -2.300   0.1837   0.01611   0.00840  -0.1011  0.8804  0.2881
  -2.200   0.1924   0.01544   0.00832  -0.1008  0.8761  0.4082
  -2.100   0.2001   0.01482   0.00828  -0.0998  0.8729  0.5607
  -2.000   0.2043   0.01437   0.00830  -0.0974  0.8701  0.7026
  -1.900   0.2064   0.01411   0.00836  -0.0945  0.8652  0.8362
  -1.800   0.2267   0.01386   0.00804  -0.0956  0.8620  1.0000
  -1.700   0.2383   0.01389   0.00790  -0.0955  0.8590  1.0000
  -1.600   0.2490   0.01398   0.00786  -0.0955  0.8547  1.0000
  -1.500   0.2599   0.01406   0.00781  -0.0955  0.8505  1.0000
  -1.400   0.2710   0.01411   0.00773  -0.0953  0.8474  1.0000
  -1.200   0.2926   0.01429   0.00768  -0.0953  0.8397  1.0000
  -1.000   0.3145   0.01440   0.00757  -0.0949  0.8337  1.0000
  -0.800   0.3359   0.01461   0.00763  -0.0949  0.8258  1.0000
  -0.600   0.3576   0.01473   0.00755  -0.0945  0.8204  1.0000
  -0.400   0.3791   0.01498   0.00767  -0.0946  0.8125  1.0000
  -0.200   0.4008   0.01510   0.00763  -0.0942  0.8075  1.0000
   0.000   0.4222   0.01538   0.00782  -0.0943  0.7998  1.0000
   0.200   0.4439   0.01551   0.00781  -0.0939  0.7950  1.0000
   0.400   0.4654   0.01581   0.00804  -0.0941  0.7874  1.0000
   0.600   0.4871   0.01596   0.00806  -0.0937  0.7827  1.0000
   0.800   0.5086   0.01628   0.00835  -0.0939  0.7755  1.0000
   1.000   0.5304   0.01644   0.00841  -0.0935  0.7706  1.0000
   1.200   0.5518   0.01678   0.00872  -0.0937  0.7638  1.0000
   1.400   0.5736   0.01697   0.00884  -0.0934  0.7588  1.0000
   1.600   0.5950   0.01730   0.00916  -0.0935  0.7525  1.0000
   1.800   0.6167   0.01754   0.00936  -0.0933  0.7471  1.0000
   2.000   0.6382   0.01784   0.00964  -0.0933  0.7416  1.0000
   2.200   0.6596   0.01813   0.00992  -0.0932  0.7355  1.0000
   2.400   0.6814   0.01834   0.01009  -0.0929  0.7311  1.0000
   2.600   0.7025   0.01875   0.01057  -0.0931  0.7240  1.0000
   2.800   0.7244   0.01891   0.01069  -0.0927  0.7198  1.0000
   3.000   0.7451   0.01938   0.01122  -0.0929  0.7124  1.0000
   3.200   0.7669   0.01953   0.01136  -0.0924  0.7077  1.0000
   3.400   0.7875   0.01998   0.01191  -0.0925  0.7003  1.0000
   3.600   0.8092   0.02011   0.01203  -0.0920  0.6953  1.0000
   3.800   0.8295   0.02053   0.01253  -0.0920  0.6875  1.0000
   4.000   0.8514   0.02053   0.01252  -0.0913  0.6820  1.0000
   4.100   0.8607   0.02079   0.01286  -0.0912  0.6764  1.0000
   4.200   0.8712   0.02078   0.01286  -0.0908  0.6724  1.0000
   4.300   0.8823   0.02067   0.01275  -0.0903  0.6695  1.0000
   4.400   0.8916   0.02091   0.01307  -0.0902  0.6636  1.0000
   4.500   0.9021   0.02088   0.01305  -0.0898  0.6596  1.0000
   4.600   0.9133   0.02079   0.01293  -0.0893  0.6568  1.0000
   4.700   0.9226   0.02106   0.01330  -0.0893  0.6512  1.0000
   4.800   0.9332   0.02110   0.01337  -0.0890  0.6475  1.0000
   4.900   0.9444   0.02106   0.01333  -0.0886  0.6448  1.0000
   5.000   0.9540   0.02130   0.01366  -0.0885  0.6400  1.0000
   5.100   0.9643   0.02140   0.01381  -0.0883  0.6358  1.0000
   5.200   0.9754   0.02136   0.01378  -0.0880  0.6328  1.0000
   5.300   0.9854   0.02152   0.01400  -0.0878  0.6284  1.0000
   5.400   0.9954   0.02162   0.01420  -0.0875  0.6234  1.0000
   5.500   1.0066   0.02145   0.01402  -0.0870  0.6197  1.0000
   5.600   1.0157   0.02157   0.01424  -0.0867  0.6130  1.0000
   5.700   1.0266   0.02137   0.01403  -0.0861  0.6079  1.0000
   5.800   1.0360   0.02136   0.01410  -0.0856  0.6009  1.0000
   5.900   1.0468   0.02109   0.01382  -0.0849  0.5951  1.0000
   6.000   1.0560   0.02107   0.01389  -0.0844  0.5873  1.0000
   6.100   1.0671   0.02078   0.01357  -0.0838  0.5817  1.0000
   6.200   1.0760   0.02080   0.01370  -0.0834  0.5735  1.0000
   6.300   1.0870   0.02056   0.01344  -0.0828  0.5676  1.0000
   6.400   1.0961   0.02053   0.01356  -0.0823  0.5593  1.0000
   6.500   1.1060   0.02045   0.01353  -0.0818  0.5519  1.0000
   6.600   1.1163   0.02029   0.01341  -0.0813  0.5450  1.0000
   6.700   1.1255   0.02029   0.01352  -0.0808  0.5365  1.0000
   6.800   1.1358   0.02015   0.01341  -0.0803  0.5292  1.0000
   6.900   1.1453   0.02008   0.01342  -0.0798  0.5203  1.0000
   7.000   1.1544   0.02003   0.01348  -0.0793  0.5104  1.0000
   7.100   1.1637   0.01995   0.01348  -0.0787  0.4999  1.0000
   7.200   1.1728   0.01985   0.01346  -0.0781  0.4882  1.0000
   7.300   1.1816   0.01977   0.01346  -0.0775  0.4749  1.0000
   7.400   1.1903   0.01971   0.01347  -0.0768  0.4599  1.0000
   7.500   1.1984   0.01965   0.01346  -0.0761  0.4411  1.0000
   7.600   1.2055   0.01965   0.01347  -0.0753  0.4143  1.0000
   7.700   1.2113   0.01978   0.01352  -0.0743  0.3772  1.0000
   7.800   1.2151   0.02018   0.01362  -0.0731  0.3296  1.0000
   7.900   1.2166   0.02093   0.01397  -0.0719  0.2827  1.0000
   8.000   1.2176   0.02184   0.01455  -0.0708  0.2438  1.0000
   8.100   1.2191   0.02276   0.01522  -0.0698  0.2131  1.0000
   8.200   1.2206   0.02367   0.01595  -0.0688  0.1885  1.0000
   8.300   1.2220   0.02459   0.01671  -0.0678  0.1669  1.0000
   8.400   1.2224   0.02557   0.01750  -0.0667  0.1477  1.0000
   8.500   1.2228   0.02655   0.01835  -0.0655  0.1267  1.0000
   8.600   1.2212   0.02767   0.01929  -0.0642  0.1086  1.0000