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EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E854 AIRFOIL (e854-il)
Reynolds number: 100,000
Max Cl/Cd: 57.37 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e854-il-100000.txt
Download as CSV file: xf-e854-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3733   0.09816   0.09363  -0.0426   1.0000   0.1241
  -8.750  -0.4009   0.09532   0.09095  -0.0448   1.0000   0.1305
  -8.500  -0.4470   0.09265   0.08850  -0.0468   1.0000   0.1314
  -8.250  -0.4036   0.08909   0.08487  -0.0416   1.0000   0.1357
  -8.000  -0.4105   0.08678   0.08265  -0.0397   1.0000   0.1391
  -7.750  -0.4374   0.08490   0.08092  -0.0380   1.0000   0.1427
  -7.250  -0.5402   0.07932   0.07559  -0.0414   1.0000   0.1454
  -6.750  -0.5644   0.05043   0.04476  -0.0558   0.9954   0.0503
  -6.500  -0.5337   0.04480   0.03875  -0.0599   0.9891   0.0493
  -6.250  -0.4965   0.04013   0.03336  -0.0645   0.9833   0.0496
  -6.000  -0.4631   0.03595   0.02863  -0.0671   0.9761   0.0491
  -5.750  -0.4207   0.03279   0.02480  -0.0704   0.9710   0.0500
  -5.500  -0.3889   0.02976   0.02169  -0.0722   0.9635   0.0550
  -5.250  -0.3458   0.02773   0.01933  -0.0750   0.9586   0.0640
  -5.000  -0.3132   0.02598   0.01761  -0.0764   0.9499   0.0785
  -4.750  -0.2742   0.02444   0.01608  -0.0787   0.9436   0.1030
  -4.500  -0.2397   0.02275   0.01471  -0.0806   0.9358   0.1447
  -4.250  -0.2038   0.02005   0.01353  -0.0841   0.9301   0.3558
  -4.000  -0.1694   0.02059   0.01424  -0.0845   0.9208   0.4986
  -3.750  -0.1389   0.02110   0.01463  -0.0843   0.9112   0.5405
  -3.500  -0.0993   0.02143   0.01486  -0.0855   0.9053   0.5744
  -3.250  -0.0723   0.02168   0.01503  -0.0848   0.8951   0.5976
  -3.000  -0.0304   0.02170   0.01492  -0.0866   0.8906   0.6224
  -2.750  -0.0058   0.02184   0.01500  -0.0855   0.8804   0.6403
  -2.500   0.0348   0.02175   0.01485  -0.0867   0.8765   0.6616
  -2.250   0.0590   0.02180   0.01483  -0.0858   0.8666   0.6776
  -2.000   0.1032   0.02147   0.01436  -0.0884   0.8628   0.6923
  -1.750   0.1295   0.02140   0.01421  -0.0882   0.8533   0.7028
  -1.500   0.1731   0.02100   0.01369  -0.0911   0.8490   0.7140
  -1.250   0.2008   0.02095   0.01354  -0.0914   0.8401   0.7243
  -1.000   0.2400   0.02061   0.01313  -0.0932   0.8351   0.7335
  -0.750   0.2671   0.02059   0.01305  -0.0934   0.8264   0.7432
  -0.500   0.3055   0.02032   0.01269  -0.0954   0.8209   0.7538
  -0.250   0.3296   0.02037   0.01273  -0.0948   0.8126   0.7627
   0.000   0.3649   0.02016   0.01247  -0.0962   0.8067   0.7731
   0.250   0.3901   0.02026   0.01255  -0.0960   0.7986   0.7842
   0.500   0.4211   0.02016   0.01243  -0.0965   0.7925   0.7950
   0.750   0.4438   0.02029   0.01258  -0.0957   0.7847   0.8064
   1.000   0.4727   0.02024   0.01255  -0.0959   0.7783   0.8191
   1.250   0.4955   0.02040   0.01273  -0.0951   0.7712   0.8329
   1.500   0.5204   0.02045   0.01281  -0.0946   0.7644   0.8483
   1.750   0.5451   0.02052   0.01291  -0.0940   0.7582   0.8659
   2.000   0.5635   0.02072   0.01320  -0.0924   0.7508   0.8870
   2.250   0.5976   0.02047   0.01299  -0.0931   0.7467   0.9123
   2.500   0.6222   0.02092   0.01358  -0.0934   0.7376   0.9497
   2.750   0.6825   0.02075   0.01345  -0.1002   0.7333   1.0000
   3.000   0.7041   0.02151   0.01420  -0.1012   0.7246   1.0000
   3.250   0.7436   0.02163   0.01428  -0.1039   0.7195   1.0000
   3.500   0.7645   0.02243   0.01509  -0.1039   0.7113   1.0000
   3.750   0.7991   0.02262   0.01530  -0.1054   0.7057   1.0000
   4.000   0.8194   0.02337   0.01609  -0.1048   0.6978   1.0000
   4.250   0.8514   0.02359   0.01634  -0.1057   0.6916   1.0000
   4.500   0.8719   0.02428   0.01711  -0.1049   0.6835   1.0000
   4.750   0.9049   0.02437   0.01724  -0.1056   0.6768   1.0000
   5.000   0.9236   0.02505   0.01802  -0.1045   0.6678   1.0000
   5.250   0.9625   0.02479   0.01780  -0.1058   0.6612   1.0000
   5.500   0.9805   0.02536   0.01851  -0.1043   0.6506   1.0000
   5.750   1.0108   0.02526   0.01848  -0.1041   0.6407   1.0000
   6.000   1.0522   0.02447   0.01773  -0.1052   0.6302   1.0000
   6.250   1.0817   0.02413   0.01749  -0.1047   0.6174   1.0000
   6.500   1.1079   0.02393   0.01738  -0.1037   0.6038   1.0000
   6.750   1.1342   0.02370   0.01725  -0.1028   0.5900   1.0000
   7.000   1.1616   0.02336   0.01700  -0.1019   0.5753   1.0000
   7.250   1.1902   0.02288   0.01659  -0.1010   0.5592   1.0000
   7.500   1.2081   0.02272   0.01662  -0.0987   0.5406   1.0000
   7.750   1.2281   0.02232   0.01633  -0.0964   0.5192   1.0000
   8.000   1.2430   0.02206   0.01618  -0.0934   0.4944   1.0000
   8.250   1.2537   0.02187   0.01608  -0.0897   0.4634   1.0000
   8.500   1.2586   0.02194   0.01616  -0.0852   0.4224   1.0000
   8.750   1.2541   0.02245   0.01644  -0.0793   0.3616   1.0000
   9.000   1.2392   0.02382   0.01729  -0.0724   0.2922   1.0000
   9.250   1.2218   0.02591   0.01888  -0.0662   0.2372   1.0000
   9.500   1.2074   0.02824   0.02084  -0.0611   0.1973   1.0000
   9.750   1.1967   0.03064   0.02297  -0.0570   0.1675   1.0000
  10.000   1.1903   0.03304   0.02515  -0.0537   0.1447   1.0000
  10.250   1.1881   0.03536   0.02732  -0.0510   0.1253   1.0000
  10.500   1.1884   0.03770   0.02951  -0.0488   0.1091   1.0000
  10.750   1.1940   0.03995   0.03164  -0.0469   0.0944   1.0000
  11.000   1.2031   0.04214   0.03375  -0.0453   0.0816   1.0000
  11.250   1.2122   0.04424   0.03589  -0.0439   0.0715   1.0000
  11.500   1.2238   0.04651   0.03828  -0.0425   0.0622   1.0000
  11.750   1.2393   0.04899   0.04079  -0.0415   0.0542   1.0000
  12.000   1.2523   0.05135   0.04319  -0.0405   0.0483   1.0000
  12.250   1.2673   0.05453   0.04663  -0.0394   0.0433   1.0000
  12.500   1.2710   0.05719   0.04951  -0.0381   0.0399   1.0000
  12.750   1.2835   0.06035   0.05279  -0.0374   0.0375   1.0000
  13.000   1.2965   0.06618   0.05892  -0.0369   0.0357   1.0000
  13.250   1.2847   0.06969   0.06280  -0.0354   0.0353   1.0000
  13.500   1.2710   0.07367   0.06712  -0.0344   0.0349   1.0000
  13.750   1.2552   0.07801   0.07179  -0.0340   0.0345   1.0000
  14.000   1.2384   0.08286   0.07694  -0.0341   0.0343   1.0000
  14.250   1.2205   0.08810   0.08246  -0.0349   0.0343   1.0000
  14.500   1.2009   0.09378   0.08840  -0.0363   0.0343   1.0000
  14.750   1.1806   0.09987   0.09473  -0.0383   0.0344   1.0000
  15.000   1.1598   0.10646   0.10154  -0.0410   0.0346   1.0000
  15.250   1.1401   0.11344   0.10870  -0.0443   0.0350   1.0000
  15.500   1.1193   0.12098   0.11641  -0.0483   0.0353   1.0000
  15.750   1.1014   0.12881   0.12432  -0.0525   0.0357   1.0000
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