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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 1,000,000
Max Cl/Cd: 164.57 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e62-il-1000000-n5.txt
Download as CSV file: xf-e62-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1861   0.08836   0.08661  -0.0696   0.9811   0.0054
  -7.750  -0.1750   0.08534   0.08360  -0.0718   0.9785   0.0054
  -7.500  -0.1613   0.08207   0.08033  -0.0749   0.9763   0.0054
  -7.250  -0.1457   0.07865   0.07692  -0.0786   0.9745   0.0054
  -7.000  -0.1267   0.07488   0.07315  -0.0835   0.9730   0.0054
  -6.750  -0.1218   0.07236   0.07065  -0.0839   0.9662   0.0054
  -6.500  -0.1011   0.06860   0.06688  -0.0891   0.9633   0.0054
  -6.250  -0.0759   0.06454   0.06281  -0.0955   0.9614   0.0054
  -6.000  -0.0626   0.06126   0.05952  -0.0985   0.9545   0.0054
  -5.750  -0.0370   0.05701   0.05525  -0.1049   0.9505   0.0054
  -5.500  -0.0078   0.05236   0.05058  -0.1126   0.9481   0.0052
  -5.250   0.0128   0.04847   0.04666  -0.1173   0.9390   0.0050
  -5.000   0.0600   0.04281   0.04093  -0.1282   0.9363   0.0055
  -3.500   0.3411   0.01171   0.00787  -0.1748   0.9116   0.0057
  -3.250   0.3762   0.01075   0.00667  -0.1766   0.9045   0.0056
  -3.000   0.4106   0.00985   0.00553  -0.1781   0.8960   0.0055
  -2.750   0.4424   0.00896   0.00443  -0.1791   0.8857   0.0055
  -2.500   0.4738   0.00788   0.00313  -0.1800   0.8752   0.0056
  -2.250   0.5042   0.00712   0.00219  -0.1806   0.8639   0.0061
  -2.000   0.5328   0.00686   0.00185  -0.1808   0.8517   0.0067
  -1.750   0.5606   0.00670   0.00160  -0.1808   0.8382   0.0074
  -1.500   0.5879   0.00658   0.00138  -0.1807   0.8231   0.0080
  -1.250   0.6147   0.00654   0.00125  -0.1804   0.8078   0.0088
  -1.000   0.6415   0.00649   0.00111  -0.1802   0.7936   0.0092
  -0.750   0.6682   0.00645   0.00097  -0.1799   0.7792   0.0093
  -0.500   0.6948   0.00644   0.00084  -0.1795   0.7645   0.0102
  -0.250   0.7213   0.00646   0.00078  -0.1792   0.7511   0.0139
   0.000   0.7482   0.00640   0.00079  -0.1790   0.7375   0.0620
   0.250   0.7752   0.00625   0.00085  -0.1791   0.7219   0.1777
   0.500   0.8024   0.00609   0.00096  -0.1792   0.7062   0.3261
   0.750   0.8298   0.00589   0.00110  -0.1794   0.6909   0.5042
   1.000   0.8565   0.00581   0.00122  -0.1793   0.6748   0.6243
   1.250   0.8815   0.00558   0.00139  -0.1788   0.6564   0.8272
   1.500   0.9002   0.00547   0.00142  -0.1766   0.6357   1.0000
   1.750   0.9253   0.00568   0.00151  -0.1760   0.6095   1.0000
   2.000   0.9500   0.00593   0.00164  -0.1754   0.5797   1.0000
   2.250   0.9742   0.00622   0.00177  -0.1747   0.5448   1.0000
   2.500   0.9962   0.00673   0.00198  -0.1736   0.4828   1.0000
   2.750   1.0139   0.00770   0.00238  -0.1718   0.3685   1.0000
   3.000   1.0335   0.00855   0.00275  -0.1704   0.2745   1.0000
   3.250   1.0512   0.00963   0.00326  -0.1688   0.1602   1.0000
   3.750   1.0927   0.01120   0.00414  -0.1664   0.0290   1.0000
   4.000   1.1161   0.01168   0.00450  -0.1656   0.0085   1.0000
   4.250   1.1412   0.01196   0.00480  -0.1651   0.0063   1.0000
   4.500   1.1661   0.01226   0.00515  -0.1645   0.0054   1.0000
   4.750   1.1907   0.01257   0.00550  -0.1639   0.0052   1.0000
   5.000   1.2150   0.01291   0.00587  -0.1633   0.0051   1.0000
   5.250   1.2391   0.01326   0.00625  -0.1626   0.0049   1.0000
   5.500   1.2628   0.01364   0.00669  -0.1619   0.0046   1.0000
   5.750   1.2860   0.01408   0.00718  -0.1610   0.0044   1.0000
   6.000   1.3089   0.01456   0.00771  -0.1601   0.0042   1.0000
   6.250   1.3313   0.01508   0.00828  -0.1592   0.0040   1.0000
   6.500   1.3532   0.01564   0.00890  -0.1581   0.0038   1.0000
   6.750   1.3746   0.01624   0.00959  -0.1570   0.0036   1.0000
   7.000   1.3955   0.01688   0.01029  -0.1558   0.0034   1.0000
   7.250   1.4158   0.01758   0.01105  -0.1545   0.0032   1.0000
   7.500   1.4349   0.01839   0.01193  -0.1530   0.0031   1.0000
   7.750   1.4522   0.01940   0.01304  -0.1511   0.0029   1.0000
   8.000   1.4669   0.02074   0.01449  -0.1489   0.0028   1.0000
   8.250   1.4793   0.02246   0.01636  -0.1462   0.0027   1.0000
   8.500   1.4923   0.02434   0.01839  -0.1437   0.0027   1.0000
   8.750   1.5058   0.02652   0.02074  -0.1414   0.0026   1.0000
   9.000   1.5205   0.02860   0.02299  -0.1394   0.0026   1.0000
   9.250   1.5348   0.03060   0.02519  -0.1374   0.0026   1.0000
   9.500   1.5479   0.03229   0.02706  -0.1352   0.0026   1.0000
   9.750   1.5582   0.03342   0.02833  -0.1325   0.0026   1.0000
  10.000   1.5659   0.03475   0.02982  -0.1294   0.0025   1.0000
  10.250   1.5715   0.03637   0.03161  -0.1261   0.0025   1.0000
  10.500   1.5767   0.03784   0.03324  -0.1230   0.0025   1.0000
  10.750   1.5793   0.03975   0.03533  -0.1197   0.0024   1.0000
  11.000   1.5773   0.04233   0.03813  -0.1160   0.0024   1.0000
  11.250   1.5745   0.04489   0.04089  -0.1126   0.0024   1.0000
  11.500   1.5686   0.04783   0.04404  -0.1093   0.0024   1.0000
  11.750   1.5594   0.05124   0.04768  -0.1062   0.0024   1.0000
  12.000   1.5472   0.05514   0.05180  -0.1034   0.0024   1.0000
  12.250   1.5357   0.05907   0.05595  -0.1014   0.0024   1.0000
  12.500   1.5227   0.06345   0.06052  -0.1000   0.0024   1.0000
  12.750   1.5079   0.06837   0.06564  -0.0993   0.0023   1.0000
  13.000   1.4909   0.07400   0.07146  -0.0995   0.0023   1.0000
  13.250   1.4740   0.08010   0.07774  -0.1006   0.0023   1.0000
  13.500   1.4491   0.08825   0.08609  -0.1032   0.0024   1.0000
  13.750   1.4337   0.09531   0.09331  -0.1064   0.0023   1.0000
  14.000   1.4091   0.10530   0.10348  -0.1117   0.0024   1.0000
  14.250   1.3906   0.11492   0.11326  -0.1176   0.0024   1.0000
  14.500   1.3689   0.12656   0.12504  -0.1252   0.0024   1.0000
  14.750   1.3476   0.13930   0.13792  -0.1336   0.0024   1.0000
  15.000   1.3206   0.15531   0.15407  -0.1438   0.0025   1.0000
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