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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 1,000,000
Max Cl/Cd: 191.48 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e62-il-1000000.txt
Download as CSV file: xf-e62-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E62  (5.62%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3886   0.13923   0.13757  -0.0193   1.0000   0.0055
 -11.000  -0.3855   0.13653   0.13488  -0.0195   1.0000   0.0055
 -10.750  -0.3830   0.13386   0.13223  -0.0198   1.0000   0.0055
 -10.500  -0.3763   0.13074   0.12911  -0.0212   0.9997   0.0056
 -10.250  -0.3642   0.12707   0.12544  -0.0244   0.9989   0.0056
 -10.000  -0.3520   0.12337   0.12174  -0.0274   0.9979   0.0056
  -9.750  -0.3394   0.11974   0.11811  -0.0305   0.9969   0.0056
  -9.500  -0.3265   0.11617   0.11453  -0.0337   0.9960   0.0056
  -9.250  -0.3131   0.11245   0.11080  -0.0371   0.9953   0.0056
  -9.000  -0.3014   0.10903   0.10738  -0.0397   0.9938   0.0056
  -8.750  -0.2893   0.10553   0.10388  -0.0425   0.9920   0.0056
  -7.500  -0.2149   0.08625   0.08461  -0.0615   0.9851   0.0058
  -7.250  -0.2084   0.08349   0.08186  -0.0621   0.9803   0.0058
  -7.000  -0.1942   0.08036   0.07873  -0.0649   0.9772   0.0060
  -6.750  -0.1727   0.07681   0.07518  -0.0698   0.9752   0.0061
  -6.500  -0.1470   0.07285   0.07121  -0.0762   0.9738   0.0063
  -6.250  -0.1190   0.06885   0.06720  -0.0833   0.9727   0.0066
  -6.000  -0.1065   0.06577   0.06412  -0.0860   0.9657   0.0067
  -5.750  -0.0767   0.06155   0.05989  -0.0936   0.9633   0.0071
  -5.500  -0.0407   0.05692   0.05524  -0.1027   0.9618   0.0079
  -5.250   0.0112   0.05128   0.04954  -0.1159   0.9608   0.0089
  -5.000   0.0568   0.04589   0.04409  -0.1267   0.9600   0.0089
  -4.500   0.1311   0.03389   0.03188  -0.1441   0.9505   0.0096
  -4.250   0.1728   0.03022   0.02809  -0.1508   0.9496   0.0101
  -4.000   0.2184   0.02583   0.02350  -0.1577   0.9489   0.0105
  -3.750   0.2640   0.02163   0.01904  -0.1638   0.9482   0.0112
  -3.500   0.2961   0.01846   0.01561  -0.1657   0.9431   0.0119
  -3.250   0.3332   0.01600   0.01287  -0.1682   0.9402   0.0131
  -3.000   0.3700   0.01521   0.01186  -0.1698   0.9380   0.0141
  -2.750   0.4129   0.01135   0.00748  -0.1744   0.9366   0.0161
  -2.500   0.4505   0.01043   0.00645  -0.1767   0.9347   0.0182
  -2.250   0.4815   0.00867   0.00437  -0.1767   0.9275   0.0128
  -2.000   0.5197   0.00738   0.00290  -0.1788   0.9237   0.0122
  -1.750   0.5533   0.00689   0.00232  -0.1800   0.9166   0.0131
  -1.500   0.5887   0.00656   0.00192  -0.1817   0.9088   0.0139
  -1.250   0.6204   0.00627   0.00154  -0.1824   0.8973   0.0143
  -1.000   0.6513   0.00604   0.00120  -0.1830   0.8852   0.0143
  -0.750   0.6808   0.00592   0.00094  -0.1832   0.8720   0.0154
  -0.500   0.7099   0.00569   0.00083  -0.1835   0.8583   0.0913
  -0.250   0.7384   0.00540   0.00087  -0.1839   0.8450   0.2521
   0.000   0.7663   0.00519   0.00095  -0.1841   0.8314   0.4048
   0.250   0.7940   0.00466   0.00115  -0.1844   0.8175   0.7450
   0.500   0.8121   0.00432   0.00118  -0.1820   0.8035   1.0000
   0.750   0.8386   0.00443   0.00120  -0.1816   0.7902   1.0000
   1.000   0.8650   0.00454   0.00124  -0.1813   0.7770   1.0000
   1.250   0.8912   0.00467   0.00129  -0.1809   0.7630   1.0000
   1.500   0.9172   0.00479   0.00134  -0.1805   0.7482   1.0000
   1.750   0.9430   0.00493   0.00142  -0.1800   0.7329   1.0000
   2.000   0.9687   0.00507   0.00150  -0.1795   0.7172   1.0000
   2.250   0.9942   0.00523   0.00158  -0.1790   0.7006   1.0000
   2.500   1.0194   0.00539   0.00168  -0.1784   0.6799   1.0000
   2.750   1.0431   0.00563   0.00182  -0.1775   0.6489   1.0000
   3.000   1.0619   0.00619   0.00202  -0.1756   0.5746   1.0000
   3.250   1.0790   0.00703   0.00235  -0.1736   0.4700   1.0000
   3.500   1.0978   0.00787   0.00273  -0.1720   0.3791   1.0000
   3.750   1.1175   0.00866   0.00311  -0.1706   0.2966   1.0000
   4.000   1.1368   0.00952   0.00355  -0.1692   0.2139   1.0000
   4.250   1.1546   0.01057   0.00411  -0.1675   0.1204   1.0000
   4.500   1.1708   0.01185   0.00485  -0.1656   0.0254   1.0000
   4.750   1.1936   0.01239   0.00530  -0.1646   0.0096   1.0000
   5.000   1.2180   0.01272   0.00568  -0.1639   0.0090   1.0000
   5.250   1.2418   0.01311   0.00612  -0.1631   0.0085   1.0000
   5.500   1.2651   0.01356   0.00665  -0.1623   0.0078   1.0000
   5.750   1.2875   0.01412   0.00728  -0.1612   0.0071   1.0000
   6.000   1.3088   0.01482   0.00805  -0.1599   0.0067   1.0000
   6.250   1.3292   0.01561   0.00894  -0.1584   0.0064   1.0000
   6.500   1.3488   0.01646   0.00989  -0.1568   0.0064   1.0000
   6.750   1.3679   0.01736   0.01089  -0.1552   0.0064   1.0000
   7.000   1.3866   0.01831   0.01193  -0.1534   0.0065   1.0000
   7.250   1.4041   0.01941   0.01313  -0.1515   0.0065   1.0000
   7.500   1.4207   0.02071   0.01452  -0.1495   0.0064   1.0000
   7.750   1.4385   0.02201   0.01592  -0.1477   0.0064   1.0000
   8.000   1.4571   0.02338   0.01742  -0.1460   0.0065   1.0000
   8.250   1.4774   0.02587   0.02015  -0.1443   0.0072   1.0000
   8.500   1.4995   0.03047   0.02517  -0.1428   0.0084   1.0000
   8.750   1.5162   0.03355   0.02853  -0.1408   0.0084   1.0000
   9.000   1.5307   0.03586   0.03107  -0.1385   0.0079   1.0000
   9.250   1.5424   0.03817   0.03360  -0.1360   0.0075   1.0000
   9.500   1.5510   0.04064   0.03630  -0.1332   0.0072   1.0000
   9.750   1.5568   0.04311   0.03898  -0.1302   0.0069   1.0000
  10.000   1.5594   0.04562   0.04168  -0.1269   0.0068   1.0000
  10.250   1.5582   0.04812   0.04435  -0.1231   0.0066   1.0000
  10.500   1.5499   0.05056   0.04695  -0.1183   0.0065   1.0000
  10.750   1.5380   0.05340   0.04998  -0.1134   0.0064   1.0000
  11.000   1.5248   0.05657   0.05334  -0.1091   0.0064   1.0000
  11.250   1.5095   0.06014   0.05709  -0.1053   0.0063   1.0000
  11.500   1.4914   0.06433   0.06146  -0.1023   0.0062   1.0000
  11.750   1.4721   0.06896   0.06628  -0.1000   0.0062   1.0000
  12.000   1.4530   0.07387   0.07137  -0.0987   0.0062   1.0000
  12.250   1.4328   0.07938   0.07705  -0.0984   0.0062   1.0000
  12.500   1.4122   0.08548   0.08333  -0.0993   0.0062   1.0000
  12.750   1.3939   0.09173   0.08975  -0.1012   0.0062   1.0000
  13.000   1.3716   0.09949   0.09767  -0.1045   0.0062   1.0000
  13.250   1.3509   0.10793   0.10627  -0.1092   0.0062   1.0000
  13.500   1.3297   0.11781   0.11632  -0.1156   0.0063   1.0000
  13.750   1.3070   0.12987   0.12854  -0.1240   0.0064   1.0000
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