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EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E854 AIRFOIL (e854-il)
Reynolds number: 100,000
Max Cl/Cd: 58.15 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e854-il-100000-n5.txt
Download as CSV file: xf-e854-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E854 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4051   0.09412   0.08925  -0.0504   1.0000   0.0184
 -10.000  -0.4150   0.08849   0.08370  -0.0522   1.0000   0.0180
  -9.750  -0.4304   0.08131   0.07660  -0.0549   1.0000   0.0174
  -9.500  -0.4841   0.06708   0.06233  -0.0629   1.0000   0.0158
  -9.250  -0.5219   0.06092   0.05609  -0.0649   1.0000   0.0154
  -9.000  -0.5576   0.05755   0.05263  -0.0635   1.0000   0.0150
  -8.750  -0.5803   0.05459   0.04957  -0.0622   1.0000   0.0150
  -8.500  -0.5876   0.05057   0.04528  -0.0635   0.9970   0.0151
  -8.250  -0.5715   0.04521   0.03944  -0.0689   0.9884   0.0152
  -8.000  -0.5490   0.04162   0.03551  -0.0728   0.9811   0.0158
  -7.750  -0.5239   0.03899   0.03259  -0.0757   0.9733   0.0168
  -7.500  -0.4992   0.03621   0.02941  -0.0778   0.9650   0.0183
  -7.250  -0.4695   0.03315   0.02580  -0.0801   0.9589   0.0197
  -7.000  -0.4439   0.03063   0.02280  -0.0806   0.9500   0.0207
  -6.750  -0.4149   0.02819   0.02018  -0.0820   0.9437   0.0220
  -6.500  -0.3862   0.02655   0.01841  -0.0830   0.9358   0.0238
  -6.250  -0.3550   0.02525   0.01686  -0.0841   0.9288   0.0282
  -6.000  -0.3252   0.02370   0.01531  -0.0853   0.9215   0.0327
  -5.750  -0.2949   0.02243   0.01392  -0.0863   0.9139   0.0402
  -5.500  -0.2628   0.02126   0.01270  -0.0877   0.9071   0.0516
  -5.250  -0.2318   0.02018   0.01159  -0.0889   0.8993   0.0685
  -5.000  -0.1977   0.01909   0.01054  -0.0908   0.8925   0.0957
  -4.750  -0.1659   0.01803   0.00962  -0.0924   0.8842   0.1403
  -4.500  -0.1310   0.01663   0.00873  -0.0950   0.8777   0.2508
  -4.250  -0.1003   0.01598   0.00857  -0.0960   0.8686   0.3856
  -4.000  -0.0627   0.01587   0.00838  -0.0978   0.8621   0.4488
  -3.750  -0.0315   0.01587   0.00828  -0.0982   0.8519   0.4820
  -3.500   0.0031   0.01585   0.00809  -0.0994   0.8435   0.5081
  -3.250   0.0370   0.01584   0.00794  -0.1003   0.8348   0.5297
  -3.000   0.0682   0.01588   0.00784  -0.1007   0.8249   0.5509
  -2.750   0.1015   0.01588   0.00774  -0.1015   0.8165   0.5685
  -2.500   0.1328   0.01584   0.00755  -0.1020   0.8068   0.5814
  -2.250   0.1633   0.01578   0.00738  -0.1025   0.7971   0.5908
  -2.000   0.1963   0.01570   0.00716  -0.1035   0.7889   0.5990
  -1.750   0.2257   0.01566   0.00700  -0.1038   0.7790   0.6076
  -1.500   0.2554   0.01562   0.00688  -0.1042   0.7701   0.6146
  -1.250   0.2868   0.01558   0.00670  -0.1049   0.7620   0.6232
  -1.000   0.3141   0.01558   0.00667  -0.1048   0.7528   0.6299
  -0.750   0.3450   0.01557   0.00654  -0.1055   0.7454   0.6384
  -0.500   0.3718   0.01560   0.00655  -0.1052   0.7366   0.6454
  -0.250   0.4010   0.01562   0.00649  -0.1056   0.7292   0.6538
   0.000   0.4282   0.01566   0.00651  -0.1055   0.7213   0.6616
   0.250   0.4563   0.01570   0.00652  -0.1056   0.7142   0.6701
   0.500   0.4837   0.01576   0.00657  -0.1055   0.7068   0.6791
   0.750   0.5110   0.01582   0.00663  -0.1055   0.7001   0.6879
   1.000   0.5378   0.01590   0.00672  -0.1053   0.6930   0.6979
   1.250   0.5657   0.01598   0.00679  -0.1053   0.6870   0.7081
   1.500   0.5912   0.01608   0.00694  -0.1049   0.6798   0.7186
   1.750   0.6198   0.01616   0.00703  -0.1051   0.6744   0.7303
   2.000   0.6439   0.01629   0.00725  -0.1045   0.6673   0.7430
   2.250   0.6711   0.01638   0.00738  -0.1043   0.6616   0.7569
   2.500   0.6956   0.01651   0.00761  -0.1037   0.6553   0.7721
   2.750   0.7204   0.01661   0.00781  -0.1031   0.6493   0.7893
   3.000   0.7461   0.01670   0.00798  -0.1026   0.6441   0.8097
   3.250   0.7675   0.01682   0.00825  -0.1013   0.6375   0.8343
   3.500   0.7922   0.01686   0.00842  -0.1005   0.6324   0.8663
   3.750   0.8180   0.01694   0.00867  -0.1000   0.6261   0.9189
   4.000   0.8514   0.01709   0.00890  -0.1015   0.6200   1.0000
   4.250   0.8797   0.01736   0.00921  -0.1019   0.6142   1.0000
   4.500   0.9051   0.01766   0.00958  -0.1017   0.6073   1.0000
   4.750   0.9341   0.01789   0.00982  -0.1021   0.6013   1.0000
   5.000   0.9573   0.01819   0.01023  -0.1014   0.5928   1.0000
   5.250   0.9838   0.01840   0.01052  -0.1012   0.5849   1.0000
   5.500   1.0086   0.01860   0.01078  -0.1007   0.5753   1.0000
   5.750   1.0310   0.01879   0.01107  -0.0997   0.5635   1.0000
   6.000   1.0534   0.01893   0.01128  -0.0986   0.5504   1.0000
   6.250   1.0752   0.01906   0.01153  -0.0974   0.5363   1.0000
   6.500   1.0962   0.01922   0.01178  -0.0960   0.5217   1.0000
   6.750   1.1166   0.01941   0.01207  -0.0946   0.5064   1.0000
   7.000   1.1362   0.01961   0.01236  -0.0930   0.4897   1.0000
   7.250   1.1542   0.01985   0.01269  -0.0912   0.4704   1.0000
   7.500   1.1697   0.02014   0.01307  -0.0890   0.4471   1.0000
   7.750   1.1834   0.02050   0.01350  -0.0864   0.4180   1.0000
   8.000   1.1934   0.02101   0.01394  -0.0833   0.3781   1.0000
   8.250   1.1967   0.02178   0.01448  -0.0792   0.3275   1.0000
   8.500   1.1932   0.02300   0.01535  -0.0744   0.2752   1.0000
   8.750   1.1886   0.02451   0.01658  -0.0699   0.2297   1.0000
   9.000   1.1854   0.02612   0.01799  -0.0660   0.1925   1.0000
   9.250   1.1826   0.02784   0.01954  -0.0625   0.1623   1.0000
   9.500   1.1817   0.02957   0.02118  -0.0596   0.1379   1.0000
   9.750   1.1814   0.03139   0.02293  -0.0569   0.1186   1.0000
  10.000   1.1820   0.03327   0.02478  -0.0547   0.1025   1.0000
  10.250   1.1828   0.03524   0.02675  -0.0527   0.0896   1.0000
  10.500   1.1835   0.03733   0.02889  -0.0509   0.0788   1.0000
  10.750   1.1832   0.03961   0.03114  -0.0493   0.0696   1.0000
  11.000   1.1861   0.04173   0.03335  -0.0480   0.0609   1.0000
  11.250   1.1871   0.04410   0.03577  -0.0467   0.0544   1.0000
  11.500   1.1885   0.04652   0.03825  -0.0457   0.0483   1.0000
  11.750   1.1894   0.04908   0.04088  -0.0447   0.0436   1.0000
  12.000   1.1919   0.05154   0.04345  -0.0440   0.0387   1.0000
  12.250   1.1906   0.05448   0.04641  -0.0433   0.0352   1.0000
  12.500   1.1941   0.05702   0.04913  -0.0426   0.0315   1.0000
  12.750   1.1952   0.05984   0.05203  -0.0424   0.0285   1.0000
  13.000   1.1940   0.06302   0.05526  -0.0420   0.0263   1.0000
  13.250   1.1977   0.06579   0.05824  -0.0416   0.0240   1.0000
  13.500   1.1992   0.06883   0.06143  -0.0415   0.0219   1.0000
  13.750   1.1984   0.07219   0.06491  -0.0418   0.0204   1.0000
  14.000   1.1967   0.07580   0.06861  -0.0421   0.0189   1.0000
  14.250   1.1986   0.07914   0.07221  -0.0421   0.0178   1.0000
  14.500   1.1989   0.08279   0.07608  -0.0423   0.0169   1.0000
  14.750   1.1975   0.08674   0.08024  -0.0429   0.0161   1.0000
  15.000   1.1943   0.09099   0.08468  -0.0439   0.0155   1.0000
  15.250   1.1900   0.09545   0.08931  -0.0452   0.0150   1.0000
  15.500   1.1842   0.10017   0.09416  -0.0469   0.0144   1.0000
  15.750   1.1781   0.10509   0.09922  -0.0489   0.0140   1.0000
  16.250   1.1594   0.11675   0.11126  -0.0541   0.0134   1.0000
  16.500   1.1473   0.12353   0.11829  -0.0577   0.0132   1.0000
  16.750   1.1343   0.13082   0.12581  -0.0618   0.0131   1.0000
  17.000   1.1197   0.13881   0.13402  -0.0667   0.0131   1.0000
  17.250   1.1050   0.14729   0.14269  -0.0721   0.0131   1.0000
  17.500   1.0899   0.15635   0.15191  -0.0779   0.0133   1.0000
  17.750   1.0754   0.16575   0.16142  -0.0840   0.0135   1.0000
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