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EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E854 AIRFOIL (e854-il)
Reynolds number: 50,000
Max Cl/Cd: 31.85 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e854-il-50000-n5.txt
Download as CSV file: xf-e854-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3974   0.10427   0.09729  -0.0521   1.0000   0.0384
 -10.250  -0.4016   0.09968   0.09279  -0.0534   1.0000   0.0384
 -10.000  -0.4071   0.09495   0.08814  -0.0548   1.0000   0.0382
  -9.750  -0.4144   0.09007   0.08334  -0.0563   1.0000   0.0380
  -9.500  -0.4264   0.08484   0.07819  -0.0583   1.0000   0.0379
  -9.250  -0.4403   0.08008   0.07351  -0.0598   1.0000   0.0375
  -9.000  -0.4554   0.07600   0.06951  -0.0606   1.0000   0.0370
  -8.750  -0.4790   0.07211   0.06570  -0.0610   1.0000   0.0367
  -8.500  -0.5020   0.06897   0.06262  -0.0604   1.0000   0.0362
  -8.250  -0.5219   0.06558   0.05922  -0.0599   1.0000   0.0358
  -8.000  -0.5389   0.06224   0.05580  -0.0590   1.0000   0.0357
  -7.750  -0.5516   0.05897   0.05238  -0.0580   1.0000   0.0356
  -7.500  -0.5608   0.05553   0.04869  -0.0571   1.0000   0.0362
  -7.250  -0.5640   0.05221   0.04503  -0.0563   1.0000   0.0367
  -7.000  -0.5624   0.04883   0.04119  -0.0557   1.0000   0.0377
  -6.750  -0.5379   0.04462   0.03636  -0.0587   0.9944   0.0391
  -6.500  -0.5078   0.04133   0.03277  -0.0615   0.9871   0.0410
  -6.250  -0.4755   0.03873   0.02976  -0.0639   0.9799   0.0449
  -6.000  -0.4415   0.03628   0.02674  -0.0658   0.9727   0.0505
  -5.750  -0.4115   0.03434   0.02475  -0.0670   0.9648   0.0562
  -5.500  -0.3783   0.03265   0.02286  -0.0684   0.9577   0.0663
  -5.250  -0.3485   0.03114   0.02123  -0.0693   0.9489   0.0791
  -5.000  -0.3187   0.02967   0.01972  -0.0705   0.9402   0.0971
  -4.750  -0.2847   0.02806   0.01810  -0.0728   0.9329   0.1277
  -4.500  -0.2560   0.02628   0.01665  -0.0746   0.9234   0.1822
  -4.250  -0.2253   0.02464   0.01611  -0.0768   0.9159   0.3417
  -4.000  -0.1950   0.02485   0.01641  -0.0768   0.9066   0.4568
  -3.750  -0.1668   0.02519   0.01657  -0.0764   0.8968   0.5097
  -3.500  -0.1322   0.02547   0.01661  -0.0769   0.8902   0.5509
  -3.250  -0.1082   0.02573   0.01674  -0.0755   0.8798   0.5804
  -3.000  -0.0806   0.02591   0.01677  -0.0747   0.8714   0.6075
  -2.750  -0.0507   0.02593   0.01665  -0.0744   0.8640   0.6286
  -2.500  -0.0233   0.02588   0.01639  -0.0742   0.8552   0.6447
  -2.250   0.0121   0.02568   0.01597  -0.0754   0.8489   0.6587
  -2.000   0.0400   0.02558   0.01569  -0.0757   0.8399   0.6705
  -1.750   0.0773   0.02536   0.01524  -0.0776   0.8342   0.6826
  -1.500   0.1030   0.02533   0.01508  -0.0774   0.8249   0.6926
  -1.250   0.1393   0.02512   0.01471  -0.0789   0.8194   0.7032
  -1.000   0.1642   0.02515   0.01461  -0.0788   0.8100   0.7138
  -0.750   0.2011   0.02495   0.01427  -0.0805   0.8047   0.7253
  -0.500   0.2233   0.02505   0.01431  -0.0798   0.7952   0.7353
  -0.250   0.2588   0.02488   0.01404  -0.0811   0.7902   0.7465
   0.000   0.2803   0.02504   0.01417  -0.0804   0.7808   0.7581
   0.250   0.3153   0.02489   0.01395  -0.0817   0.7758   0.7708
   0.500   0.3352   0.02512   0.01417  -0.0807   0.7665   0.7840
   0.750   0.3684   0.02500   0.01403  -0.0815   0.7615   0.7984
   1.000   0.3865   0.02527   0.01433  -0.0801   0.7524   0.8137
   1.250   0.4179   0.02516   0.01424  -0.0806   0.7474   0.8311
   1.500   0.4351   0.02546   0.01461  -0.0791   0.7387   0.8520
   1.750   0.4671   0.02537   0.01457  -0.0798   0.7336   0.8770
   2.000   0.4931   0.02566   0.01495  -0.0801   0.7256   0.9134
   2.250   0.5394   0.02565   0.01501  -0.0841   0.7201   1.0000
   2.500   0.5657   0.02617   0.01547  -0.0851   0.7126   1.0000
   2.750   0.5969   0.02653   0.01578  -0.0865   0.7064   1.0000
   3.000   0.6250   0.02701   0.01623  -0.0874   0.7000   1.0000
   3.250   0.6502   0.02756   0.01681  -0.0877   0.6928   1.0000
   3.500   0.6858   0.02776   0.01701  -0.0893   0.6883   1.0000
   3.750   0.7002   0.02871   0.01800  -0.0881   0.6791   1.0000
   4.000   0.7361   0.02888   0.01823  -0.0895   0.6748   1.0000
   4.250   0.7479   0.02996   0.01938  -0.0879   0.6654   1.0000
   4.500   0.7828   0.03014   0.01962  -0.0891   0.6607   1.0000
   4.750   0.7938   0.03128   0.02085  -0.0874   0.6512   1.0000
   5.000   0.8292   0.03140   0.02110  -0.0885   0.6463   1.0000
   5.250   0.8390   0.03258   0.02239  -0.0865   0.6363   1.0000
   5.500   0.8771   0.03253   0.02247  -0.0878   0.6314   1.0000
   5.750   0.8855   0.03373   0.02379  -0.0856   0.6206   1.0000
   6.000   0.9066   0.03435   0.02459  -0.0848   0.6119   1.0000
   6.250   0.9376   0.03444   0.02485  -0.0849   0.6040   1.0000
   6.500   0.9504   0.03533   0.02590  -0.0830   0.5928   1.0000
   6.750   0.9737   0.03563   0.02637  -0.0821   0.5824   1.0000
   7.000   1.0133   0.03491   0.02589  -0.0826   0.5723   1.0000
   7.250   1.0421   0.03453   0.02572  -0.0817   0.5590   1.0000
   7.500   1.0606   0.03456   0.02593  -0.0797   0.5435   1.0000
   7.750   1.0728   0.03482   0.02637  -0.0769   0.5266   1.0000
   8.000   1.0847   0.03494   0.02667  -0.0740   0.5089   1.0000
   8.250   1.1026   0.03462   0.02652  -0.0715   0.4894   1.0000
   8.500   1.1092   0.03500   0.02711  -0.0682   0.4689   1.0000
   8.750   1.1179   0.03521   0.02747  -0.0650   0.4450   1.0000
   9.000   1.1189   0.03610   0.02850  -0.0616   0.4181   1.0000
   9.250   1.1227   0.03688   0.02936  -0.0585   0.3851   1.0000
   9.500   1.1266   0.03775   0.03017  -0.0556   0.3427   1.0000
   9.750   1.1286   0.03899   0.03112  -0.0527   0.2930   1.0000
  10.000   1.1237   0.04118   0.03295  -0.0500   0.2502   1.0000
  10.250   1.1165   0.04393   0.03542  -0.0479   0.2176   1.0000
  10.500   1.1095   0.04693   0.03823  -0.0463   0.1904   1.0000
  10.750   1.1041   0.05001   0.04118  -0.0450   0.1672   1.0000
  11.000   1.0996   0.05312   0.04415  -0.0439   0.1493   1.0000
  11.250   1.0974   0.05615   0.04711  -0.0430   0.1326   1.0000
  11.500   1.0969   0.05910   0.05009  -0.0423   0.1185   1.0000
  11.750   1.0976   0.06200   0.05295  -0.0416   0.1063   1.0000
  12.000   1.0989   0.06489   0.05582  -0.0410   0.0955   1.0000
  12.250   1.1042   0.06754   0.05859  -0.0403   0.0853   1.0000
  12.500   1.1093   0.07026   0.06142  -0.0396   0.0764   1.0000
  12.750   1.1140   0.07296   0.06405  -0.0392   0.0694   1.0000
  13.000   1.1223   0.07566   0.06706  -0.0385   0.0623   1.0000
  13.250   1.1284   0.07840   0.06977  -0.0382   0.0568   1.0000
  13.500   1.1354   0.08159   0.07335  -0.0377   0.0518   1.0000
  13.750   1.1399   0.08467   0.07652  -0.0377   0.0480   1.0000
  14.000   1.1414   0.08847   0.08050  -0.0379   0.0448   1.0000
  14.250   1.1365   0.09327   0.08568  -0.0388   0.0426   1.0000
  14.500   1.1305   0.09830   0.09102  -0.0401   0.0409   1.0000
  14.750   1.1223   0.10370   0.09667  -0.0418   0.0398   1.0000
  15.000   1.1122   0.10944   0.10263  -0.0441   0.0388   1.0000
  15.250   1.1003   0.11571   0.10911  -0.0471   0.0382   1.0000
  15.500   1.0858   0.12279   0.11638  -0.0508   0.0378   1.0000
  15.750   1.0594   0.13333   0.12722  -0.0571   0.0388   1.0000
  16.000   1.0270   0.14688   0.14098  -0.0658   0.0406   1.0000
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