XFOIL         Version 6.94
  
 Calculated polar for: EPPLER EC 86(-3)-914 AIRFOIL                    
  
 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   0.6520   0.01158   0.00706  -0.1716  0.8613  0.6557
   0.500   0.6821   0.01206   0.00774  -0.1649  0.8469  0.7010
   1.000   0.7552   0.01123   0.00697  -0.1673  0.8415  0.7097
   1.500   0.8034   0.01104   0.00679  -0.1655  0.8226  0.7181
   2.000   0.8469   0.01095   0.00674  -0.1623  0.7944  0.7266
   2.500   0.9302   0.01032   0.00594  -0.1669  0.7493  0.7357
   3.500   0.9617   0.01315   0.00732  -0.1506  0.4789  0.7519
   4.500   1.0201   0.01611   0.00914  -0.1424  0.2816  0.7629
   5.000   1.0614   0.01702   0.00979  -0.1406  0.2309  0.7652
   5.500   1.1053   0.01778   0.01045  -0.1391  0.2035  0.7676
   6.000   1.1487   0.01861   0.01117  -0.1376  0.1803  0.7704
   6.500   1.1910   0.01960   0.01201  -0.1360  0.1494  0.7728
   7.000   1.2339   0.02055   0.01289  -0.1346  0.1258  0.7754
   7.500   1.2533   0.02365   0.01529  -0.1300  0.0145  0.7778
   8.000   1.2914   0.02514   0.01678  -0.1280  0.0015  0.7803
   8.500   1.3306   0.02645   0.01820  -0.1262  0.0013  0.7830
   9.000   1.3681   0.02785   0.01976  -0.1242  0.0014  0.7854
   9.500   1.4022   0.02945   0.02156  -0.1217  0.0015  0.7878
  10.000   1.4332   0.03131   0.02363  -0.1189  0.0017  0.7904
  10.500   1.4604   0.03359   0.02615  -0.1158  0.0019  0.7932
  11.000   1.4807   0.03656   0.02939  -0.1122  0.0021  0.7961
  11.500   1.4903   0.04063   0.03375  -0.1080  0.0022  0.7990
  12.000   1.4931   0.04553   0.03893  -0.1040  0.0024  0.8017
  12.500   1.4959   0.05082   0.04450  -0.1008  0.0027  0.8046
  13.000   1.4812   0.05854   0.05257  -0.0978  0.0030  0.8074
  13.500   1.4621   0.06778   0.06214  -0.0964  0.0033  0.8097
  14.000   1.4451   0.07765   0.07230  -0.0964  0.0037  0.8118
  14.500   1.4410   0.08625   0.08108  -0.0964  0.0040  0.8139
  15.000   1.4487   0.09427   0.08964  -0.0955  0.0052  0.8159
  15.500   1.2185   0.12227   0.11860  -0.1033  0.0040  0.7983
  16.000   1.2274   0.12590   0.12265  -0.1005  0.0059  0.7992
  16.500   1.1864   0.14109   0.13851  -0.1082  0.0080  0.7993
  17.000   1.1457   0.15726   0.15507  -0.1191  0.0079  0.7998
  18.500   1.0396   0.21256   0.21123  -0.1536  0.0065  0.8010
  19.000   1.0268   0.22698   0.22573  -0.1610  0.0062  0.8021