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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 500,000
Max Cl/Cd: 141.69 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e62-il-500000-n5.txt
Download as CSV file: xf-e62-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3044   0.11164   0.10928  -0.0384   0.9936   0.0076
  -9.000  -0.2926   0.10830   0.10594  -0.0410   0.9919   0.0078
  -8.750  -0.2799   0.10494   0.10258  -0.0438   0.9902   0.0082
  -8.500  -0.2669   0.10157   0.09922  -0.0468   0.9886   0.0082
  -8.250  -0.2528   0.09825   0.09589  -0.0500   0.9871   0.0083
  -8.000  -0.2368   0.09483   0.09247  -0.0539   0.9857   0.0087
  -7.750  -0.2232   0.09174   0.08939  -0.0571   0.9836   0.0088
  -5.250   0.0015   0.03553   0.03327  -0.0981   0.9276   0.0093
  -5.000   0.0315   0.03068   0.02838  -0.1059   0.9244   0.0094
  -4.750   0.0674   0.02585   0.02347  -0.1146   0.9225   0.0094
  -4.500   0.0973   0.01955   0.01707  -0.1243   0.9160   0.0105
  -4.250   0.1318   0.01692   0.01436  -0.1299   0.9130   0.0120
  -4.000   0.1774   0.01297   0.01022  -0.1387   0.9114   0.0132
  -3.750   0.2257   0.00903   0.00598  -0.1472   0.9103   0.0132
  -3.250   0.2919   0.01785   0.01387  -0.1582   0.9138   0.0090
  -3.000   0.3370   0.01436   0.00982  -0.1628   0.9120   0.0084
  -2.750   0.3791   0.01231   0.00734  -0.1661   0.9101   0.0081
  -2.500   0.4160   0.01098   0.00571  -0.1681   0.9060   0.0081
  -2.250   0.4519   0.01001   0.00453  -0.1698   0.9010   0.0083
  -2.000   0.4898   0.00926   0.00363  -0.1720   0.8967   0.0088
  -1.750   0.5235   0.00883   0.00310  -0.1732   0.8897   0.0093
  -1.500   0.5601   0.00813   0.00230  -0.1752   0.8832   0.0117
  -1.250   0.5926   0.00786   0.00194  -0.1762   0.8741   0.0122
  -1.000   0.6249   0.00768   0.00165  -0.1771   0.8645   0.0128
  -0.750   0.6560   0.00757   0.00144  -0.1777   0.8528   0.0142
  -0.500   0.6857   0.00751   0.00130  -0.1780   0.8396   0.0200
  -0.250   0.7156   0.00719   0.00128  -0.1787   0.8266   0.1535
   0.000   0.7441   0.00702   0.00132  -0.1790   0.8131   0.2640
   0.250   0.7732   0.00651   0.00151  -0.1798   0.7991   0.5675
   0.500   0.7931   0.00598   0.00165  -0.1779   0.7856   0.8686
   0.750   0.8165   0.00594   0.00161  -0.1767   0.7718   1.0000
   1.000   0.8430   0.00608   0.00165  -0.1763   0.7569   1.0000
   1.250   0.8691   0.00622   0.00170  -0.1759   0.7413   1.0000
   1.500   0.8952   0.00636   0.00176  -0.1755   0.7262   1.0000
   1.750   0.9211   0.00651   0.00184  -0.1750   0.7100   1.0000
   2.000   0.9465   0.00668   0.00194  -0.1745   0.6918   1.0000
   2.250   0.9714   0.00687   0.00205  -0.1738   0.6715   1.0000
   2.500   0.9960   0.00708   0.00217  -0.1731   0.6478   1.0000
   2.750   1.0201   0.00732   0.00231  -0.1723   0.6212   1.0000
   3.000   1.0415   0.00773   0.00252  -0.1709   0.5748   1.0000
   3.250   1.0556   0.00869   0.00289  -0.1683   0.4627   1.0000
   3.500   1.0725   0.00966   0.00334  -0.1663   0.3652   1.0000
   3.750   1.0912   0.01056   0.00379  -0.1648   0.2797   1.0000
   4.000   1.1070   0.01182   0.00441  -0.1630   0.1634   1.0000
   4.250   1.1259   0.01278   0.00496  -0.1615   0.0905   1.0000
   4.500   1.1451   0.01372   0.00559  -0.1601   0.0322   1.0000
   4.750   1.1669   0.01438   0.00614  -0.1590   0.0096   1.0000
   5.000   1.1907   0.01477   0.00658  -0.1583   0.0084   1.0000
   5.250   1.2141   0.01520   0.00706  -0.1575   0.0077   1.0000
   5.500   1.2372   0.01566   0.00762  -0.1566   0.0073   1.0000
   5.750   1.2597   0.01618   0.00822  -0.1556   0.0070   1.0000
   6.000   1.2814   0.01679   0.00892  -0.1545   0.0064   1.0000
   6.250   1.3014   0.01761   0.00984  -0.1531   0.0057   1.0000
   6.500   1.3199   0.01858   0.01094  -0.1514   0.0055   1.0000
   6.750   1.3377   0.01960   0.01205  -0.1496   0.0053   1.0000
   7.000   1.3567   0.02043   0.01301  -0.1480   0.0052   1.0000
   7.250   1.3748   0.02136   0.01403  -0.1463   0.0050   1.0000
   7.500   1.3919   0.02240   0.01518  -0.1445   0.0049   1.0000
   7.750   1.4082   0.02357   0.01647  -0.1425   0.0047   1.0000
   8.000   1.4241   0.02488   0.01790  -0.1405   0.0046   1.0000
   8.250   1.4397   0.02631   0.01948  -0.1384   0.0045   1.0000
   8.500   1.4550   0.02790   0.02122  -0.1364   0.0044   1.0000
   8.750   1.4704   0.02965   0.02316  -0.1344   0.0043   1.0000
   9.000   1.4855   0.03159   0.02530  -0.1325   0.0043   1.0000
   9.250   1.4994   0.03369   0.02763  -0.1303   0.0043   1.0000
   9.500   1.5109   0.03606   0.03028  -0.1279   0.0043   1.0000
   9.750   1.5190   0.03854   0.03303  -0.1251   0.0043   1.0000
  10.000   1.5230   0.04119   0.03596  -0.1217   0.0043   1.0000
  10.250   1.5229   0.04404   0.03910  -0.1179   0.0043   1.0000
  10.500   1.5202   0.04684   0.04217  -0.1141   0.0043   1.0000
  10.750   1.5156   0.04965   0.04524  -0.1105   0.0042   1.0000
  11.000   1.5070   0.05301   0.04886  -0.1068   0.0042   1.0000
  11.250   1.4981   0.05630   0.05239  -0.1037   0.0041   1.0000
  11.500   1.4869   0.05999   0.05631  -0.1010   0.0040   1.0000
  11.750   1.4715   0.06448   0.06105  -0.0989   0.0040   1.0000
  12.000   1.4540   0.06953   0.06635  -0.0975   0.0040   1.0000
  12.250   1.4375   0.07470   0.07172  -0.0971   0.0040   1.0000
  12.500   1.4197   0.08050   0.07774  -0.0976   0.0040   1.0000
  12.750   1.4008   0.08700   0.08443  -0.0993   0.0039   1.0000
  13.000   1.3799   0.09450   0.09213  -0.1022   0.0039   1.0000
  13.250   1.3599   0.10274   0.10054  -0.1064   0.0039   1.0000
  13.500   1.3324   0.11405   0.11206  -0.1133   0.0041   1.0000
  13.750   1.3147   0.12429   0.12245  -0.1202   0.0041   1.0000
  14.000   1.2848   0.14057   0.13890  -0.1313   0.0044   1.0000
  14.250   1.2553   0.15998   0.15842  -0.1432   0.0046   1.0000
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