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EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 395 AIRFOIL (e395-il)
Reynolds number: 200,000
Max Cl/Cd: 92.15 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e395-il-200000.txt
Download as CSV file: xf-e395-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 395 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2421   0.10526   0.10199  -0.0636   0.9834   0.0523
  -9.250  -0.2307   0.10105   0.09779  -0.0675   0.9777   0.0542
  -9.000  -0.3590   0.05638   0.05302  -0.1010   0.9598   0.0205
  -8.750  -0.2293   0.08479   0.08157  -0.0818   0.9663   0.0409
  -8.500  -0.2068   0.08349   0.08027  -0.0850   0.9619   0.0506
  -8.250  -0.3243   0.03251   0.02751  -0.1382   0.9321   0.0211
  -8.000  -0.3001   0.03169   0.02674  -0.1391   0.9258   0.0229
  -7.750  -0.2699   0.02849   0.02298  -0.1427   0.9212   0.0245
  -7.500  -0.2335   0.02509   0.01903  -0.1466   0.9190   0.0263
  -7.250  -0.1937   0.02325   0.01704  -0.1500   0.9176   0.0300
  -7.000  -0.1529   0.02161   0.01524  -0.1535   0.9162   0.0365
  -6.750  -0.1328   0.02079   0.01434  -0.1528   0.9077   0.0436
  -6.500  -0.0947   0.01980   0.01323  -0.1554   0.9051   0.0551
  -6.250  -0.0551   0.01887   0.01217  -0.1582   0.9031   0.0676
  -6.000  -0.0228   0.01811   0.01134  -0.1595   0.8988   0.0790
  -5.750   0.0053   0.01748   0.01066  -0.1599   0.8929   0.0903
  -5.500   0.0417   0.01678   0.00990  -0.1618   0.8897   0.1046
  -5.250   0.0796   0.01614   0.00918  -0.1640   0.8872   0.1215
  -5.000   0.1044   0.01584   0.00886  -0.1636   0.8804   0.1370
  -4.750   0.1370   0.01539   0.00838  -0.1647   0.8760   0.1561
  -4.500   0.1725   0.01496   0.00795  -0.1664   0.8728   0.1777
  -4.250   0.1997   0.01480   0.00776  -0.1664   0.8669   0.1985
  -4.000   0.2293   0.01455   0.00754  -0.1669   0.8616   0.2198
  -3.750   0.2631   0.01430   0.00725  -0.1681   0.8580   0.2441
  -3.500   0.2909   0.01418   0.00716  -0.1682   0.8526   0.2658
  -3.250   0.3189   0.01408   0.00706  -0.1683   0.8469   0.2885
  -3.000   0.3515   0.01389   0.00686  -0.1692   0.8430   0.3125
  -2.750   0.3793   0.01384   0.00682  -0.1693   0.8378   0.3356
  -2.500   0.4066   0.01378   0.00679  -0.1692   0.8320   0.3585
  -2.250   0.4382   0.01364   0.00665  -0.1699   0.8279   0.3836
  -2.000   0.4659   0.01362   0.00667  -0.1700   0.8228   0.4075
  -1.750   0.4927   0.01361   0.00669  -0.1698   0.8170   0.4330
  -1.500   0.5237   0.01348   0.00661  -0.1703   0.8128   0.4600
  -1.250   0.5511   0.01349   0.00667  -0.1703   0.8077   0.4875
  -1.000   0.5775   0.01349   0.00675  -0.1700   0.8018   0.5164
  -0.750   0.6080   0.01340   0.00670  -0.1704   0.7976   0.5481
  -0.500   0.6345   0.01343   0.00683  -0.1701   0.7923   0.5805
  -0.250   0.6604   0.01343   0.00694  -0.1697   0.7864   0.6145
   0.000   0.6901   0.01335   0.00692  -0.1698   0.7822   0.6526
   0.250   0.7144   0.01340   0.00710  -0.1690   0.7765   0.6901
   0.500   0.7390   0.01340   0.00721  -0.1682   0.7707   0.7313
   0.750   0.7658   0.01330   0.00719  -0.1675   0.7665   0.7760
   1.000   0.7839   0.01335   0.00740  -0.1653   0.7601   0.8236
   1.250   0.8010   0.01323   0.00739  -0.1625   0.7545   0.8847
   1.500   0.8316   0.01302   0.00716  -0.1627   0.7505   1.0000
   1.750   0.8572   0.01326   0.00739  -0.1627   0.7432   1.0000
   2.000   0.8886   0.01333   0.00740  -0.1634   0.7381   1.0000
   2.250   0.9186   0.01346   0.00747  -0.1639   0.7327   1.0000
   2.500   0.9450   0.01362   0.00764  -0.1638   0.7258   1.0000
   2.750   0.9772   0.01365   0.00760  -0.1645   0.7209   1.0000
   3.000   1.0016   0.01387   0.00785  -0.1640   0.7134   1.0000
   3.250   1.0315   0.01391   0.00786  -0.1643   0.7074   1.0000
   3.500   1.0583   0.01406   0.00803  -0.1642   0.7004   1.0000
   3.750   1.0861   0.01413   0.00810  -0.1641   0.6932   1.0000
   4.000   1.1139   0.01422   0.00820  -0.1640   0.6862   1.0000
   4.250   1.1406   0.01429   0.00829  -0.1637   0.6781   1.0000
   4.500   1.1673   0.01438   0.00840  -0.1634   0.6702   1.0000
   4.750   1.1948   0.01441   0.00844  -0.1632   0.6619   1.0000
   5.000   1.2191   0.01453   0.00863  -0.1625   0.6526   1.0000
   5.250   1.2490   0.01452   0.00858  -0.1627   0.6446   1.0000
   5.500   1.2707   0.01465   0.00881  -0.1615   0.6338   1.0000
   5.750   1.2952   0.01474   0.00895  -0.1607   0.6235   1.0000
   6.000   1.3212   0.01478   0.00900  -0.1602   0.6129   1.0000
   6.250   1.3443   0.01486   0.00912  -0.1591   0.6006   1.0000
   6.500   1.3657   0.01498   0.00931  -0.1578   0.5870   1.0000
   6.750   1.3869   0.01512   0.00950  -0.1564   0.5725   1.0000
   7.000   1.4076   0.01528   0.00969  -0.1549   0.5567   1.0000
   7.250   1.4274   0.01549   0.00990  -0.1533   0.5394   1.0000
   7.500   1.4439   0.01577   0.01024  -0.1511   0.5195   1.0000
   7.750   1.4593   0.01611   0.01058  -0.1487   0.4978   1.0000
   8.000   1.4723   0.01654   0.01098  -0.1460   0.4735   1.0000
   8.250   1.4816   0.01707   0.01145  -0.1426   0.4464   1.0000
   8.500   1.4863   0.01773   0.01201  -0.1384   0.4173   1.0000
   8.750   1.4887   0.01856   0.01273  -0.1341   0.3856   1.0000
   9.000   1.4890   0.01959   0.01362  -0.1297   0.3524   1.0000
   9.250   1.4875   0.02082   0.01471  -0.1253   0.3194   1.0000
   9.500   1.4851   0.02225   0.01601  -0.1212   0.2875   1.0000
   9.750   1.4822   0.02387   0.01748  -0.1173   0.2569   1.0000
  10.000   1.4795   0.02564   0.01912  -0.1137   0.2274   1.0000
  10.250   1.4770   0.02755   0.02091  -0.1105   0.1992   1.0000
  10.500   1.4744   0.02963   0.02286  -0.1076   0.1719   1.0000
  10.750   1.4721   0.03183   0.02495  -0.1049   0.1466   1.0000
  11.000   1.4689   0.03424   0.02724  -0.1025   0.1234   1.0000
  11.250   1.4658   0.03677   0.02966  -0.1002   0.1025   1.0000
  11.500   1.4621   0.03949   0.03229  -0.0981   0.0856   1.0000
  11.750   1.4593   0.04226   0.03504  -0.0963   0.0712   1.0000
  12.000   1.4556   0.04522   0.03798  -0.0946   0.0604   1.0000
  12.250   1.4498   0.04853   0.04124  -0.0930   0.0524   1.0000
  12.500   1.4503   0.05130   0.04409  -0.0918   0.0452   1.0000
  12.750   1.4470   0.05458   0.04744  -0.0907   0.0399   1.0000
  13.000   1.4444   0.05789   0.05077  -0.0898   0.0356   1.0000
  13.250   1.4422   0.06128   0.05427  -0.0889   0.0321   1.0000
  13.500   1.4416   0.06454   0.05758  -0.0884   0.0289   1.0000
  13.750   1.4383   0.06823   0.06133  -0.0878   0.0264   1.0000
  14.000   1.4403   0.07135   0.06458  -0.0875   0.0239   1.0000
  14.250   1.4388   0.07492   0.06815  -0.0873   0.0222   1.0000
  14.500   1.4403   0.07821   0.07158  -0.0866   0.0208   1.0000
  14.750   1.4433   0.08137   0.07489  -0.0864   0.0193   1.0000
  15.000   1.4452   0.08467   0.07824  -0.0865   0.0181   1.0000
  15.250   1.4486   0.08775   0.08132  -0.0861   0.0168   1.0000
  15.500   1.4488   0.09148   0.08530  -0.0865   0.0158   1.0000
  15.750   1.4501   0.09505   0.08903  -0.0869   0.0149   1.0000
  16.000   1.4519   0.09855   0.09265  -0.0873   0.0143   1.0000
  16.250   1.4547   0.10188   0.09606  -0.0877   0.0137   1.0000
  16.500   1.4622   0.10468   0.09890  -0.0870   0.0132   1.0000
  16.750   1.4564   0.10956   0.10406  -0.0884   0.0130   1.0000
  17.000   1.4499   0.11468   0.10947  -0.0900   0.0128   1.0000
  17.250   1.4416   0.12023   0.11529  -0.0921   0.0127   1.0000
  17.500   1.4319   0.12614   0.12146  -0.0946   0.0126   1.0000
  17.750   1.4211   0.13239   0.12796  -0.0977   0.0126   1.0000
  18.000   1.4092   0.13900   0.13482  -0.1012   0.0126   1.0000
  18.250   1.3958   0.14617   0.14223  -0.1054   0.0126   1.0000
  18.500   1.3820   0.15367   0.14995  -0.1101   0.0126   1.0000
  18.750   1.3674   0.16169   0.15818  -0.1155   0.0127   1.0000
  19.000   1.3527   0.17004   0.16671  -0.1212   0.0128   1.0000
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