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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.28 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e421-il-1000000-n5.txt
Download as CSV file: xf-e421-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -0.0453   0.16465   0.16288  -0.0728   0.9788   0.0084
 -19.000  -0.0362   0.16235   0.16058  -0.0750   0.9766   0.0084
 -18.500  -0.1880   0.19313   0.19117  -0.0565   0.9882   0.0084
 -11.000   0.0379   0.07426   0.07028  -0.1349   0.5849   0.0071
 -10.750  -0.0012   0.06555   0.06150  -0.1389   0.5833   0.0071
 -10.500  -0.0160   0.06083   0.05672  -0.1409   0.5789   0.0070
 -10.250  -0.0356   0.05604   0.05190  -0.1427   0.5746   0.0070
 -10.000  -0.0613   0.05178   0.04763  -0.1433   0.5712   0.0070
  -9.750  -0.0828   0.04535   0.04116  -0.1494   0.5680   0.0072
  -9.500  -0.0996   0.03489   0.03048  -0.1640   0.5648   0.0069
  -9.250  -0.0973   0.02120   0.01621  -0.1806   0.5611   0.0070
  -9.000  -0.0744   0.01860   0.01336  -0.1825   0.5550   0.0070
  -8.750  -0.0493   0.01740   0.01201  -0.1832   0.5497   0.0071
  -8.500  -0.0237   0.01652   0.01100  -0.1835   0.5437   0.0073
  -8.250   0.0019   0.01579   0.01013  -0.1836   0.5376   0.0074
  -8.000   0.0283   0.01518   0.00941  -0.1837   0.5329   0.0075
  -7.750   0.0549   0.01462   0.00874  -0.1838   0.5284   0.0077
  -7.500   0.0816   0.01414   0.00816  -0.1837   0.5235   0.0078
  -7.250   0.1082   0.01372   0.00764  -0.1836   0.5188   0.0080
  -7.000   0.1354   0.01335   0.00717  -0.1836   0.5151   0.0082
  -6.750   0.1627   0.01298   0.00672  -0.1835   0.5113   0.0083
  -6.500   0.1901   0.01269   0.00635  -0.1834   0.5069   0.0084
  -6.250   0.2171   0.01233   0.00590  -0.1832   0.5024   0.0087
  -6.000   0.2443   0.01203   0.00551  -0.1831   0.4984   0.0090
  -5.750   0.2721   0.01177   0.00521  -0.1830   0.4953   0.0093
  -5.500   0.2998   0.01154   0.00492  -0.1829   0.4919   0.0097
  -5.250   0.3274   0.01135   0.00466  -0.1827   0.4886   0.0101
  -5.000   0.3550   0.01118   0.00443  -0.1825   0.4852   0.0105
  -4.750   0.3824   0.01104   0.00422  -0.1823   0.4817   0.0110
  -4.500   0.4104   0.01085   0.00400  -0.1822   0.4795   0.0118
  -4.250   0.4383   0.01070   0.00382  -0.1821   0.4769   0.0127
  -4.000   0.4661   0.01057   0.00365  -0.1819   0.4737   0.0139
  -3.750   0.4938   0.01045   0.00350  -0.1818   0.4705   0.0158
  -3.500   0.5213   0.01035   0.00337  -0.1816   0.4675   0.0184
  -3.250   0.5488   0.01026   0.00325  -0.1813   0.4645   0.0218
  -3.000   0.5766   0.01014   0.00314  -0.1812   0.4626   0.0272
  -2.750   0.6045   0.01004   0.00305  -0.1811   0.4607   0.0336
  -2.500   0.6323   0.00994   0.00297  -0.1810   0.4585   0.0412
  -2.250   0.6600   0.00987   0.00291  -0.1808   0.4559   0.0496
  -2.000   0.6874   0.00982   0.00286  -0.1806   0.4533   0.0579
  -1.750   0.7148   0.00978   0.00283  -0.1804   0.4507   0.0667
  -1.500   0.7419   0.00976   0.00282  -0.1802   0.4481   0.0773
  -1.250   0.7693   0.00974   0.00281  -0.1800   0.4461   0.0873
  -1.000   0.7970   0.00972   0.00280  -0.1798   0.4446   0.0956
  -0.750   0.8245   0.00971   0.00280  -0.1796   0.4428   0.1044
  -0.500   0.8520   0.00970   0.00282  -0.1794   0.4408   0.1135
  -0.250   0.8792   0.00971   0.00283  -0.1792   0.4385   0.1211
   0.000   0.9062   0.00974   0.00286  -0.1790   0.4362   0.1293
   0.250   0.9331   0.00978   0.00290  -0.1787   0.4342   0.1375
   0.500   0.9597   0.00983   0.00295  -0.1784   0.4320   0.1452
   0.750   0.9860   0.00989   0.00301  -0.1780   0.4297   0.1539
   1.000   1.0133   0.00992   0.00306  -0.1778   0.4285   0.1614
   1.250   1.0403   0.00995   0.00311  -0.1776   0.4268   0.1688
   1.500   1.0671   0.00999   0.00316  -0.1773   0.4250   0.1767
   1.750   1.0937   0.01004   0.00322  -0.1770   0.4232   0.1833
   2.000   1.1201   0.01010   0.00330  -0.1767   0.4214   0.1919
   2.250   1.1462   0.01017   0.00337  -0.1764   0.4195   0.1986
   2.500   1.1720   0.01025   0.00346  -0.1759   0.4176   0.2071
   2.750   1.1974   0.01034   0.00356  -0.1755   0.4153   0.2147
   3.000   1.2225   0.01045   0.00366  -0.1749   0.4131   0.2231
   3.250   1.2487   0.01049   0.00375  -0.1746   0.4118   0.2323
   3.500   1.2745   0.01056   0.00385  -0.1742   0.4104   0.2422
   3.750   1.2997   0.01062   0.00395  -0.1737   0.4089   0.2543
   4.000   1.3244   0.01069   0.00405  -0.1732   0.4072   0.2662
   4.250   1.3486   0.01076   0.00417  -0.1725   0.4052   0.2817
   4.500   1.3725   0.01084   0.00429  -0.1718   0.4033   0.3006
   4.750   1.3957   0.01095   0.00443  -0.1710   0.4011   0.3211
   5.000   1.4188   0.01106   0.00458  -0.1702   0.3991   0.3469
   5.250   1.4417   0.01118   0.00477  -0.1693   0.3970   0.3863
   5.500   1.4663   0.01120   0.00495  -0.1689   0.3958   0.4503
   6.000   1.5137   0.01073   0.00541  -0.1677   0.3921   1.0000
   6.250   1.5370   0.01088   0.00556  -0.1669   0.3900   1.0000
   6.500   1.5597   0.01104   0.00572  -0.1661   0.3876   1.0000
   6.750   1.5817   0.01123   0.00590  -0.1651   0.3849   1.0000
   7.000   1.6027   0.01145   0.00611  -0.1640   0.3819   1.0000
   7.250   1.6257   0.01161   0.00628  -0.1633   0.3796   1.0000
   7.500   1.6483   0.01177   0.00646  -0.1625   0.3767   1.0000
   7.750   1.6702   0.01196   0.00666  -0.1616   0.3736   1.0000
   8.000   1.6910   0.01219   0.00689  -0.1606   0.3704   1.0000
   8.250   1.7106   0.01246   0.00715  -0.1593   0.3669   1.0000
   8.500   1.7317   0.01268   0.00739  -0.1583   0.3642   1.0000
   8.750   1.7529   0.01289   0.00763  -0.1574   0.3611   1.0000
   9.000   1.7732   0.01314   0.00789  -0.1563   0.3579   1.0000
   9.250   1.7917   0.01346   0.00821  -0.1550   0.3539   1.0000
   9.500   1.8094   0.01380   0.00856  -0.1536   0.3502   1.0000
   9.750   1.8290   0.01408   0.00887  -0.1525   0.3459   1.0000
  10.000   1.8467   0.01444   0.00924  -0.1511   0.3412   1.0000
  10.250   1.8611   0.01493   0.00972  -0.1492   0.3361   1.0000
  10.500   1.8794   0.01528   0.01010  -0.1480   0.3319   1.0000
  10.750   1.8946   0.01576   0.01059  -0.1464   0.3265   1.0000
  11.000   1.9073   0.01637   0.01120  -0.1445   0.3212   1.0000
  11.250   1.9221   0.01690   0.01175  -0.1429   0.3153   1.0000
  11.500   1.9324   0.01766   0.01251  -0.1408   0.3085   1.0000
  11.750   1.9445   0.01837   0.01324  -0.1390   0.3026   1.0000
  12.000   1.9544   0.01922   0.01410  -0.1370   0.2962   1.0000
  12.250   1.9611   0.02029   0.01517  -0.1347   0.2880   1.0000
  12.500   1.9650   0.02158   0.01645  -0.1323   0.2793   1.0000
  12.750   1.9689   0.02295   0.01783  -0.1300   0.2698   1.0000
  13.000   1.9693   0.02465   0.01953  -0.1276   0.2609   1.0000
  13.250   1.9673   0.02663   0.02150  -0.1252   0.2510   1.0000
  13.500   1.9646   0.02879   0.02367  -0.1230   0.2410   1.0000
  13.750   1.9590   0.03132   0.02620  -0.1208   0.2323   1.0000
  14.000   1.9503   0.03426   0.02914  -0.1187   0.2228   1.0000
  14.250   1.9399   0.03749   0.03239  -0.1168   0.2124   1.0000
  14.500   1.9292   0.04093   0.03585  -0.1152   0.2048   1.0000
  14.750   1.9185   0.04452   0.03947  -0.1138   0.1971   1.0000
  15.000   1.9070   0.04829   0.04328  -0.1126   0.1900   1.0000
  15.250   1.8966   0.05210   0.04713  -0.1116   0.1837   1.0000
  15.500   1.8850   0.05616   0.05123  -0.1107   0.1778   1.0000
  15.750   1.8738   0.06027   0.05538  -0.1101   0.1714   1.0000
  16.000   1.8596   0.06484   0.05999  -0.1096   0.1651   1.0000
  16.250   1.8490   0.06911   0.06430  -0.1093   0.1590   1.0000
  16.500   1.8354   0.07381   0.06904  -0.1091   0.1534   1.0000
  16.750   1.8284   0.07776   0.07304  -0.1091   0.1478   1.0000
  17.000   1.8159   0.08250   0.07781  -0.1092   0.1421   1.0000
  17.250   1.8084   0.08669   0.08204  -0.1094   0.1369   1.0000
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