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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.21 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e582-il-1000000-n5.txt
Download as CSV file: xf-e582-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3656   0.03162   0.02834  -0.1354   0.7767   0.0024
 -10.000  -0.3967   0.02668   0.02294  -0.1300   0.7692   0.0023
  -9.500  -0.3965   0.02136   0.01688  -0.1244   0.7589   0.0025
  -9.250  -0.3820   0.02003   0.01533  -0.1230   0.7543   0.0025
  -9.000  -0.3652   0.01892   0.01402  -0.1218   0.7500   0.0026
  -8.750  -0.3454   0.01813   0.01308  -0.1210   0.7462   0.0026
  -8.500  -0.3249   0.01728   0.01208  -0.1202   0.7426   0.0026
  -8.250  -0.3093   0.01562   0.01014  -0.1188   0.7389   0.0029
  -8.000  -0.2869   0.01500   0.00941  -0.1182   0.7353   0.0030
  -7.750  -0.2636   0.01453   0.00885  -0.1178   0.7319   0.0031
  -7.500  -0.2394   0.01403   0.00828  -0.1174   0.7289   0.0032
  -7.250  -0.2155   0.01348   0.00765  -0.1170   0.7259   0.0033
  -7.000  -0.1910   0.01306   0.00715  -0.1167   0.7226   0.0034
  -6.750  -0.1664   0.01266   0.00666  -0.1164   0.7195   0.0035
  -6.500  -0.1416   0.01228   0.00621  -0.1161   0.7165   0.0037
  -6.250  -0.1160   0.01191   0.00580  -0.1159   0.7140   0.0038
  -6.000  -0.0906   0.01153   0.00536  -0.1157   0.7112   0.0039
  -5.750  -0.0649   0.01120   0.00498  -0.1155   0.7082   0.0041
  -5.500  -0.0392   0.01089   0.00460  -0.1153   0.7052   0.0042
  -5.250  -0.0134   0.01061   0.00427  -0.1151   0.7024   0.0042
  -5.000   0.0131   0.01036   0.00398  -0.1151   0.6999   0.0043
  -4.750   0.0396   0.01008   0.00368  -0.1151   0.6971   0.0045
  -4.500   0.0661   0.00980   0.00338  -0.1150   0.6942   0.0050
  -4.250   0.0930   0.00962   0.00317  -0.1150   0.6913   0.0054
  -4.000   0.1199   0.00945   0.00296  -0.1150   0.6884   0.0059
  -3.750   0.1469   0.00929   0.00276  -0.1150   0.6856   0.0064
  -3.500   0.1744   0.00908   0.00256  -0.1151   0.6830   0.0076
  -3.250   0.2019   0.00891   0.00239  -0.1153   0.6800   0.0107
  -3.000   0.2291   0.00871   0.00223  -0.1154   0.6767   0.0227
  -2.750   0.2564   0.00856   0.00211  -0.1155   0.6736   0.0371
  -2.500   0.2835   0.00838   0.00201  -0.1156   0.6706   0.0608
  -2.250   0.3109   0.00809   0.00191  -0.1159   0.6675   0.1145
  -2.000   0.3380   0.00772   0.00182  -0.1162   0.6640   0.1994
  -1.750   0.3655   0.00745   0.00174  -0.1166   0.6604   0.2725
  -1.500   0.3929   0.00716   0.00166  -0.1169   0.6569   0.3559
  -1.250   0.4211   0.00663   0.00156  -0.1177   0.6536   0.5043
  -1.000   0.4495   0.00604   0.00156  -0.1184   0.6498   0.6939
  -0.750   0.4776   0.00608   0.00165  -0.1185   0.6457   0.7350
  -0.500   0.5056   0.00615   0.00168  -0.1186   0.6416   0.7467
  -0.250   0.5342   0.00620   0.00171  -0.1189   0.6375   0.7561
   0.000   0.5625   0.00629   0.00177  -0.1191   0.6324   0.7675
   0.250   0.5893   0.00642   0.00189  -0.1189   0.6272   0.7793
   0.500   0.6171   0.00653   0.00199  -0.1189   0.6224   0.7878
   0.750   0.6447   0.00659   0.00204  -0.1190   0.6171   0.7910
   1.000   0.6722   0.00666   0.00206  -0.1191   0.6120   0.7921
   1.250   0.7004   0.00670   0.00209  -0.1193   0.6068   0.7930
   1.500   0.7280   0.00676   0.00211  -0.1195   0.6005   0.7940
   1.750   0.7553   0.00683   0.00215  -0.1196   0.5942   0.7949
   2.000   0.7828   0.00689   0.00219  -0.1197   0.5867   0.7957
   2.250   0.8096   0.00698   0.00224  -0.1197   0.5795   0.7964
   2.500   0.8368   0.00705   0.00229  -0.1198   0.5717   0.7971
   2.750   0.8632   0.00715   0.00235  -0.1197   0.5637   0.7979
   3.000   0.8897   0.00725   0.00242  -0.1197   0.5549   0.7987
   3.250   0.9160   0.00736   0.00250  -0.1196   0.5460   0.7994
   3.500   0.9413   0.00749   0.00259  -0.1193   0.5358   0.8000
   3.750   0.9667   0.00761   0.00269  -0.1191   0.5245   0.8007
   4.000   0.9915   0.00775   0.00280  -0.1187   0.5128   0.8014
   4.250   1.0154   0.00792   0.00293  -0.1182   0.4989   0.8022
   4.500   1.0386   0.00812   0.00308  -0.1175   0.4840   0.8029
   4.750   1.0611   0.00833   0.00324  -0.1168   0.4684   0.8037
   5.000   1.0825   0.00858   0.00343  -0.1158   0.4509   0.8045
   5.250   1.1031   0.00885   0.00364  -0.1146   0.4331   0.8053
   5.500   1.1229   0.00914   0.00386  -0.1133   0.4148   0.8063
   5.750   1.1407   0.00944   0.00409  -0.1117   0.3961   0.8074
   6.000   1.1571   0.00974   0.00433  -0.1097   0.3778   0.8084
   6.250   1.1727   0.01010   0.00462  -0.1076   0.3592   0.8094
   6.500   1.1877   0.01050   0.00495  -0.1055   0.3400   0.8104
   6.750   1.2030   0.01090   0.00528  -0.1035   0.3218   0.8114
   7.000   1.2169   0.01136   0.00566  -0.1012   0.3011   0.8124
   7.250   1.2304   0.01184   0.00606  -0.0990   0.2831   0.8134
   7.750   1.2581   0.01281   0.00692  -0.0947   0.2509   0.8152
   8.000   1.2710   0.01334   0.00740  -0.0926   0.2352   0.8163
   8.250   1.2827   0.01393   0.00794  -0.0903   0.2185   0.8175
   8.500   1.2933   0.01460   0.00855  -0.0879   0.2010   0.8187
   8.750   1.3032   0.01532   0.00922  -0.0855   0.1843   0.8199
   9.000   1.3120   0.01614   0.00997  -0.0830   0.1674   0.8213
   9.250   1.3204   0.01703   0.01079  -0.0806   0.1504   0.8228
   9.500   1.3260   0.01811   0.01177  -0.0779   0.1294   0.8244
   9.750   1.3337   0.01913   0.01273  -0.0757   0.1143   0.8259
  10.000   1.3469   0.01989   0.01351  -0.0742   0.1079   0.8272
  10.250   1.3504   0.02124   0.01475  -0.0717   0.0887   0.8285
  10.500   1.3566   0.02250   0.01594  -0.0696   0.0744   0.8298
  10.750   1.3589   0.02405   0.01740  -0.0672   0.0561   0.8312
  11.000   1.3689   0.02515   0.01850  -0.0657   0.0495   0.8326
  11.250   1.3758   0.02649   0.01981  -0.0640   0.0405   0.8342
  11.500   1.3829   0.02786   0.02118  -0.0624   0.0331   0.8357
  11.750   1.3897   0.02929   0.02261  -0.0609   0.0264   0.8374
  12.250   1.4047   0.03220   0.02552  -0.0583   0.0175   0.8409
  12.500   1.4113   0.03379   0.02713  -0.0570   0.0133   0.8426
  12.750   1.4196   0.03529   0.02865  -0.0560   0.0109   0.8444
  13.250   1.4355   0.03843   0.03189  -0.0541   0.0076   0.8482
  13.500   1.4436   0.04004   0.03355  -0.0533   0.0063   0.8504
  13.750   1.4509   0.04177   0.03534  -0.0524   0.0054   0.8530
  14.000   1.4569   0.04365   0.03726  -0.0517   0.0039   0.8558
  14.250   1.4622   0.04566   0.03933  -0.0509   0.0028   0.8585
  14.750   1.4753   0.04956   0.04337  -0.0498   0.0020   0.8645
  15.000   1.4804   0.05173   0.04562  -0.0494   0.0017   0.8681
  15.250   1.4831   0.05421   0.04818  -0.0489   0.0009   0.8718
  15.750   1.4916   0.05898   0.05312  -0.0483   0.0006   0.8805
  16.000   1.4942   0.06163   0.05586  -0.0482   0.0005   0.8861
  16.250   1.4967   0.06434   0.05867  -0.0481   0.0003   0.8926
  16.500   1.4986   0.06712   0.06157  -0.0481   0.0003   0.9016
  16.750   1.4998   0.06995   0.06452  -0.0480   0.0002   0.9156
  17.000   1.4995   0.07292   0.06767  -0.0481   0.0002   0.9783
  17.250   1.5007   0.07603   0.07086  -0.0484   0.0002   1.0000
  17.500   1.4999   0.07955   0.07449  -0.0490   0.0002   1.0000
  17.750   1.5001   0.08299   0.07801  -0.0497   0.0002   1.0000
  18.000   1.4962   0.08709   0.08222  -0.0506   0.0001   1.0000
  18.250   1.4935   0.09109   0.08632  -0.0517   0.0001   1.0000
  18.750   1.4852   0.09978   0.09522  -0.0542   0.0001   1.0000
  19.000   1.4814   0.10414   0.09969  -0.0557   0.0001   1.0000
  19.250   1.4768   0.10868   0.10434  -0.0574   0.0001   1.0000
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