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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.05 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e421-il-1000000.txt
Download as CSV file: xf-e421-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 421 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2181   0.08751   0.08384  -0.1339   0.6095   0.0162
  -9.500   0.2260   0.08516   0.08148  -0.1346   0.6029   0.0162
  -9.250   0.2292   0.08200   0.07830  -0.1355   0.5965   0.0162
  -8.750  -0.0110   0.03744   0.03361  -0.1587   0.6076   0.0099
  -8.500  -0.0069   0.02415   0.01981  -0.1775   0.6025   0.0097
  -8.250   0.0163   0.01999   0.01530  -0.1819   0.5949   0.0098
  -8.000   0.0407   0.01838   0.01347  -0.1830   0.5882   0.0098
  -7.750   0.0657   0.01716   0.01206  -0.1836   0.5814   0.0099
  -7.500   0.0906   0.01623   0.01095  -0.1838   0.5743   0.0101
  -7.250   0.1167   0.01543   0.01000  -0.1840   0.5686   0.0102
  -7.000   0.1430   0.01478   0.00922  -0.1841   0.5626   0.0105
  -6.750   0.1691   0.01424   0.00854  -0.1839   0.5563   0.0106
  -6.500   0.1956   0.01357   0.00772  -0.1840   0.5510   0.0110
  -6.250   0.2222   0.01290   0.00694  -0.1840   0.5457   0.0115
  -6.000   0.2490   0.01255   0.00649  -0.1838   0.5401   0.0119
  -5.750   0.2759   0.01227   0.00613  -0.1836   0.5348   0.0124
  -5.500   0.3037   0.01194   0.00573  -0.1835   0.5310   0.0128
  -5.250   0.3313   0.01169   0.00539  -0.1834   0.5267   0.0132
  -5.000   0.3584   0.01133   0.00494  -0.1832   0.5222   0.0139
  -4.750   0.3854   0.01111   0.00464  -0.1830   0.5172   0.0147
  -4.500   0.4137   0.01089   0.00437  -0.1829   0.5144   0.0157
  -4.250   0.4416   0.01064   0.00407  -0.1828   0.5109   0.0171
  -4.000   0.4692   0.01047   0.00385  -0.1826   0.5069   0.0194
  -3.750   0.4965   0.01028   0.00362  -0.1824   0.5030   0.0234
  -3.500   0.5236   0.01015   0.00346  -0.1821   0.4990   0.0296
  -3.250   0.5518   0.00999   0.00332  -0.1821   0.4968   0.0376
  -3.000   0.5798   0.00987   0.00322  -0.1820   0.4941   0.0458
  -2.750   0.6076   0.00978   0.00314  -0.1818   0.4912   0.0539
  -2.500   0.6350   0.00973   0.00308  -0.1816   0.4881   0.0625
  -2.250   0.6621   0.00972   0.00305  -0.1814   0.4846   0.0715
  -2.000   0.6892   0.00972   0.00304  -0.1811   0.4811   0.0807
  -1.750   0.7172   0.00965   0.00301  -0.1810   0.4793   0.0908
  -1.500   0.7451   0.00961   0.00300  -0.1809   0.4772   0.1016
  -1.250   0.7728   0.00958   0.00300  -0.1807   0.4749   0.1122
  -1.000   0.8002   0.00959   0.00300  -0.1805   0.4725   0.1213
  -0.750   0.8273   0.00962   0.00302  -0.1803   0.4698   0.1299
  -0.500   0.8541   0.00966   0.00306  -0.1799   0.4669   0.1398
  -0.250   0.8808   0.00977   0.00312  -0.1796   0.4637   0.1464
   0.000   0.9084   0.00975   0.00314  -0.1795   0.4623   0.1569
   0.250   0.9359   0.00978   0.00317  -0.1793   0.4606   0.1634
   0.500   0.9633   0.00978   0.00321  -0.1791   0.4587   0.1739
   0.750   0.9904   0.00983   0.00326  -0.1789   0.4566   0.1807
   1.000   1.0173   0.00987   0.00331  -0.1786   0.4545   0.1905
   1.250   1.0437   0.00994   0.00337  -0.1783   0.4521   0.1980
   1.500   1.0698   0.01003   0.00345  -0.1779   0.4495   0.2065
   1.750   1.0958   0.01018   0.00357  -0.1776   0.4466   0.2152
   2.000   1.1228   0.01020   0.00363  -0.1773   0.4455   0.2238
   2.250   1.1496   0.01023   0.00370  -0.1771   0.4441   0.2337
   2.500   1.1762   0.01028   0.00377  -0.1768   0.4424   0.2440
   2.750   1.2026   0.01032   0.00385  -0.1766   0.4404   0.2551
   3.000   1.2287   0.01038   0.00394  -0.1762   0.4385   0.2694
   3.250   1.2544   0.01045   0.00404  -0.1758   0.4365   0.2851
   3.500   1.2797   0.01054   0.00416  -0.1754   0.4345   0.3059
   3.750   1.3047   0.01066   0.00431  -0.1749   0.4321   0.3325
   4.000   1.3300   0.01081   0.00451  -0.1745   0.4296   0.3676
   4.250   1.3555   0.01077   0.00464  -0.1742   0.4284   0.4319
   4.500   1.3790   0.01005   0.00493  -0.1736   0.4270   1.0000
   4.750   1.4037   0.01015   0.00502  -0.1730   0.4252   1.0000
   5.000   1.4281   0.01027   0.00513  -0.1724   0.4235   1.0000
   5.250   1.4521   0.01039   0.00525  -0.1717   0.4217   1.0000
   5.500   1.4755   0.01053   0.00538  -0.1709   0.4197   1.0000
   5.750   1.4983   0.01070   0.00552  -0.1700   0.4175   1.0000
   6.000   1.5210   0.01092   0.00571  -0.1692   0.4149   1.0000
   6.250   1.5445   0.01112   0.00591  -0.1685   0.4127   1.0000
   6.500   1.5679   0.01122   0.00604  -0.1677   0.4112   1.0000
   6.750   1.5910   0.01133   0.00618  -0.1670   0.4093   1.0000
   7.000   1.6138   0.01146   0.00632  -0.1662   0.4070   1.0000
   7.250   1.6362   0.01160   0.00648  -0.1653   0.4046   1.0000
   7.500   1.6577   0.01179   0.00665  -0.1643   0.4018   1.0000
   7.750   1.6780   0.01205   0.00689  -0.1631   0.3989   1.0000
   8.000   1.6995   0.01227   0.00712  -0.1622   0.3963   1.0000
   8.250   1.7218   0.01240   0.00730  -0.1614   0.3944   1.0000
   8.500   1.7439   0.01256   0.00749  -0.1605   0.3920   1.0000
   8.750   1.7654   0.01274   0.00769  -0.1596   0.3894   1.0000
   9.000   1.7854   0.01297   0.00794  -0.1585   0.3868   1.0000
   9.250   1.8034   0.01328   0.00823  -0.1570   0.3835   1.0000
   9.500   1.8229   0.01356   0.00853  -0.1558   0.3805   1.0000
   9.750   1.8441   0.01374   0.00877  -0.1550   0.3778   1.0000
  10.000   1.8641   0.01397   0.00904  -0.1539   0.3747   1.0000
  10.250   1.8823   0.01428   0.00936  -0.1526   0.3712   1.0000
  10.500   1.8980   0.01469   0.00977  -0.1509   0.3676   1.0000
  10.750   1.9159   0.01503   0.01015  -0.1497   0.3645   1.0000
  11.000   1.9355   0.01531   0.01049  -0.1487   0.3612   1.0000
  11.250   1.9521   0.01570   0.01091  -0.1473   0.3571   1.0000
  11.500   1.9656   0.01624   0.01144  -0.1454   0.3530   1.0000
  11.750   1.9810   0.01672   0.01196  -0.1439   0.3492   1.0000
  12.000   1.9979   0.01715   0.01245  -0.1427   0.3452   1.0000
  12.250   2.0100   0.01780   0.01311  -0.1409   0.3399   1.0000
  12.500   2.0210   0.01855   0.01388  -0.1390   0.3349   1.0000
  12.750   2.0351   0.01917   0.01455  -0.1375   0.3298   1.0000
  13.000   2.0427   0.02015   0.01554  -0.1354   0.3236   1.0000
  13.250   2.0526   0.02107   0.01649  -0.1337   0.3173   1.0000
  13.500   2.0594   0.02221   0.01765  -0.1317   0.3106   1.0000
  13.750   2.0642   0.02354   0.01899  -0.1296   0.3032   1.0000
  14.000   2.0654   0.02519   0.02065  -0.1274   0.2947   1.0000
  14.250   2.0686   0.02679   0.02228  -0.1255   0.2871   1.0000
  14.500   2.0634   0.02911   0.02460  -0.1231   0.2784   1.0000
  14.750   2.0625   0.03123   0.02675  -0.1213   0.2693   1.0000
  15.000   2.0545   0.03405   0.02958  -0.1192   0.2603   1.0000
  15.500   2.0289   0.04101   0.03656  -0.1154   0.2398   1.0000
  15.750   2.0145   0.04491   0.04049  -0.1138   0.2311   1.0000
  16.000   1.9971   0.04926   0.04486  -0.1124   0.2228   1.0000
  16.250   1.9845   0.05326   0.04890  -0.1114   0.2149   1.0000
  16.500   1.9627   0.05843   0.05409  -0.1104   0.2067   1.0000
  16.750   1.9496   0.06275   0.05846  -0.1098   0.1993   1.0000
  17.000   1.9305   0.06793   0.06367  -0.1093   0.1919   1.0000
  17.250   1.9174   0.07246   0.06823  -0.1091   0.1849   1.0000
  17.500   1.9014   0.07747   0.07327  -0.1090   0.1782   1.0000
  17.750   1.8881   0.08225   0.07810  -0.1091   0.1715   1.0000
  18.000   1.8738   0.08725   0.08312  -0.1093   0.1652   1.0000
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